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Journal articles on the topic 'Compressed air propulsion'
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1
A. H. E., Gherouat, Khochemane L., and BENNIS O. "Marine Propulsion by the Injection of Compressed Air." International Journal of Engineering and Technology 8, no. 6 (2016): 3082–92. http://dx.doi.org/10.21817/ijet/2016/v8i6/160806406.
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Wyczalek, Floyd A., та Chung M. Suh. "AirСar CAES-Compressed Air Energy Source-Compendium". Advanced Materials Research 430-432 (січень 2012): 189–96. http://dx.doi.org/10.4028/www.scientific.net/amr.430-432.189.
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This paper is a re evaluation of CAES Compressed Air Energy Source. CAES is not new, experimental air car compressed air propulsion vehicles appeared in early 1900’s, and are currently exemplified by the India Tata Motors AirCar MiniCat based on the French MDI Motor Development International AirCar. (see Ulf Bossel, European Fuel Cell Forum) This study focuses on compressed air potential pressure specific energy density and specific power, ideal Global thermodynamic cycle efficiency, US EPA 23 cycle urban driving test schedule overall drive train ideal efficiency and vehicle ideal range. CAES analysis is unique because compression and expansion cycles are remotely linked solely by ambient atmosphere e.g., compression occurs in a stationary device while expansion takes place in a mobile vehicle. Therefore, ideal thermodynamic compression and/or expansion cycles can be treated independently and linked as isothermal entities e.g., both cycles are in fact separate ideal complete compression and/or complete expansion cycles without (TDC) top dead center piston clearance with isothermal ambient temperature compressed air storage. Further, CAES potential pressure energy density and power density are comparable to electro-chemical energy sources on a Ragone chart, e.g., CAES specific energy density and specific power based solely on stored pressure energy potential are similar to the Pb-Acid battery. However, modern forms of multi stage expansion air motors with heat exchangers between stages extract additional thermal energy directly from ambient air to increase vehicle range by a factor of ~ 6 with a four stage expansion motor. To minimize road-load energy consumption air powered vehicles are characterized by low curb (empty) vehicle mass and low speed urban traffic. Based on Tata AirCar design specifications, comparative theoretical driving range tests were simulated with the 23 cycle US EPA Urban (City) driving schedule and a modified low speed 23 cycle Urban schedule suitable for India. We concluded modern multi stage air car propulsion may find applications in temperate zones, particularly highly congested pedestrian trafficked city streets and retirement communities such as Sun City, AZ, India [5a-19a]
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Gasparini Croce, Rodrigo, Antônio Dariva, Emerson Pereira Trarbach, and Filipe Arthur Firmino Monhol. "Avaliação da eficiência na geração de energia elétrica de um motor híbrido (combustão + ar comprimido) a partir de testes em protótipo real." Latin American Journal of Energy Research 7, no. 1 (2020): 34–45. http://dx.doi.org/10.21712/lajer.2020.v7.n1.p34-45.
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The continuous research for high efficiency and low emission engines are the technological challenges nowadays. Internal combustion engines are widely used due to low-cost if compared to the electrical vehicles' propulsion systems. Unfortunately, internal combustion engines have low efficiency; about 20%-25% are converted to mechanical power. A new hybrid approach engine running on ethanol and compressed air is presented in this paper. As a result, the global engine efficiency is improved once a part of energy comes from compressed air stored in an external reservoir. By measuring the ethanol consumption and the compressed air flux is possible to calculate the global engine efficiency when it runs a stationary electric generator connected to a known load. This paper presents a conceptual working flow of an Internal Combustion Engine and a Hybrid Engine but focused to the prototype developed. The test procedures and results are shown and the potential to apply this new concept in a vehicle.
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UCHIMIYA, Takurou, and Masahiko SAKAMOTO. "G305 Ship Propulsion Equipment Directly Driven by Air Compressed by Self-Exited Vibration in Blower Piping System." Proceedings of the Fluids engineering conference 2012 (2012): 485–86. http://dx.doi.org/10.1299/jsmefed.2012.485.
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Balan, George Iulian, Octavian Narcis Volintiru, Ionut Cristian Scurtu, Florin Ioniță, Mirela Letitia Vasile, and Claudia Borzea. "Considerations regarding the anti-icing system for the ship propulsion plant with gas turbine." E3S Web of Conferences 286 (2021): 04013. http://dx.doi.org/10.1051/e3sconf/202128604013.
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Vessels that have navigation routes in areas with ambient temperatures that can drop below + 5 [°C], with a relative humidity of over 65%, will have implemented technical solutions for monitoring and combating ice accumulations in the intake routes of gas turbine power plants. Because gas turbines are not designed and built to allow the admission of foreign objects (in this case - ice), it is necessary to avoid the accumulation of ice through anti-icing systems and not to melt ice through defrost systems. Naval anti-icing systems may have as a source of energy flow compressed air, supersaturated steam, exhaust gases, electricity or a combination of those listed. The monitoring and optimization of the operation of the anti-icing system gives the gas turbine power plant an operation as close as possible to the normal regimes stipulated in the ship's construction or retrofit specification.
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SAKAMOTO, Masahiko, and Takurou Uchimiya. "121 A Ship Propulsion Equipment Driven by Air Compressed by Pressure Fluctuation in a Blower Piping System : Effect of Valve in Pipe." Proceedings of Conference of Kansai Branch 2013.88 (2013): _1–21_. http://dx.doi.org/10.1299/jsmekansai.2013.88._1-21_.
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UCHIMIYA, Takurou, and Masahiko SAKAMOTO. "G1001 Ship Propulsion Equipment Driven by Air Compressed by Self-Exited Vibration in Blower Piping System (Effect on Valve in Piping System)." Proceedings of the Fluids engineering conference 2013 (2013): _G1001–01_—_G1001–02_. http://dx.doi.org/10.1299/jsmefed.2013._g1001-01_.
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Korakianitis, T., L. Meyer, M. Boruta, and H. E. McCormick. "One-Disk Nutating-Engine Performance for Unmanned Aerial Vehicles." Journal of Engineering for Gas Turbines and Power 126, no. 3 (2004): 475–81. http://dx.doi.org/10.1115/1.1496770.
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The nutating engine is a new type of internal combustion engine. The engine has unique advantages over conventional piston engines and gas turbines in small power ranges suitable for unmanned aerial vehicles (UAV), and other applications. This publication is the original presentation of the performance potential of the simplest version of the engine, a one-disk engine operating at constant compression ratio, for light airframe propulsion. In its basic configuration the core of the engine is a nutating nonrotating disk, with the center of its hub mounted in the middle of a Z-shaped shaft. The two ends of the shaft rotate, while the disk “nutates,” performs a wobbling motion without rotating around its axis. The motion of the disk circumference prescribes a portion of a sphere. A portion of the area of the disk is used for intake and compression, a portion is used to seal against a center casing, and the remaining portion is used for expansion and exhaust. The compressed air is admitted to an external accumulator, and then into an external combustion chamber before it is admitted to the power side of the disk. The external combustion chamber enables the engine to use diesel fuel in small engine sizes, giving it unique capabilities for UAV propulsion. The performance of the one-disk engine configuration for flight Mach numbers from 0 to 1 and altitudes from 0 to 20 km is presented and discussed. The performance with equal compression and expansion volume is compared with the higher-efficiency version with expansion volume higher than compression volume. A companion paper examines multidisk alternative engine configurations and load control schemes.
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Tafti, Danesh K., Long He, and K. Nagendra. "Large eddy simulation for predicting turbulent heat transfer in gas turbines." Philosophical Transactions of the Royal Society A: Mathematical, Physical and Engineering Sciences 372, no. 2022 (2014): 20130322. http://dx.doi.org/10.1098/rsta.2013.0322.
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Blade cooling technology will play a critical role in the next generation of propulsion and power generation gas turbines. Accurate prediction of blade metal temperature can avoid the use of excessive compressed bypass air and allow higher turbine inlet temperature, increasing fuel efficiency and decreasing emissions. Large eddy simulation (LES) has been established to predict heat transfer coefficients with good accuracy under various non-canonical flows, but is still limited to relatively simple geometries and low Reynolds numbers. It is envisioned that the projected increase in computational power combined with a drop in price-to-performance ratio will make system-level simulations using LES in complex blade geometries at engine conditions accessible to the design process in the coming one to two decades. In making this possible, two key challenges are addressed in this paper: working with complex intricate blade geometries and simulating high-Reynolds-number ( Re ) flows. It is proposed to use the immersed boundary method (IBM) combined with LES wall functions. A ribbed duct at Re =20 000 is simulated using the IBM, and a two-pass ribbed duct is simulated at Re =100 000 with and without rotation (rotation number Ro =0.2) using LES with wall functions. The results validate that the IBM is a viable alternative to body-conforming grids and that LES with wall functions reproduces experimental results at a much lower computational cost.
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Gavrilescu, Ileana. "Effective business models for electric vehicles." Proceedings of the International Conference on Business Excellence 11, no. 1 (2017): 36–44. http://dx.doi.org/10.1515/picbe-2017-0004.
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Abstract The proposed study aims to use asyncretic and synthetic approach of two elements that have an intrinsic efficiency value: business models and electric vehicles. Our approach seeks to circumscribe more widespread concerns globally - on the one hand, to oil shortages and climate change - and on the other hand, economic efficiency to business models customized to new types of mobility. New “electric” cars projects besiege the traditional position of the conventional car. In the current economy context the concept of efficiency of business models is quite different from what it meant in a traditional sense, particularly because of new technological fields. The arguments put forward by us will be both factual and emotional. Therefore, we rely on interviews and questionnaires designed to fit significantly to the point of the study. Research in the field of new propulsion systems for vehicles has been exploring various possibilities lately, such as: electricity, hydrogen, compressed air, biogas, etc. Theoretically or in principle, it is possible for tomorrow’s vehicles to be driven by the widest variety if resources. A primary goal of our study would be to theoretically reconsider some of the contemporary entrepreneurship coordinates and secondly to provide minimum guidance for decision-making of businesses that will operate in the field of electric mobility. To achieve this, we shall specifically analyze an electric mobility system but in parallel we will address business models that lend themselves effectively on aspects of this field. With a methodology based on questionnaires that had to overcome the conventional mechanism using some of the most unusual ingredients, we hope that the results of our research will successfully constitute a contribution to the goals and especially as a means of managerial orientation for entrepreneurs in the Romanian market.
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Large, James, and Apostolos Pesyridis. "Investigation of Micro Gas Turbine Systems for High Speed Long Loiter Tactical Unmanned Air Systems." Aerospace 6, no. 5 (2019): 55. http://dx.doi.org/10.3390/aerospace6050055.
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In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.
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Idzikowski, Marek, and Wojciech Miksa. "Flight Tests of Turboprop Engine with Reverse Air Intake System." Transactions on Aerospace Research 2018, no. 3 (2018): 26–36. http://dx.doi.org/10.2478/tar-2018-0020.
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Abstract This work presents selected results of I-31T propulsion flight tests, obtained in the framework of ESPOSA (Efficient Systems and Propulsion for Small Aircraft) project. I-31T test platform was equipped with TP100, a 180 kW turboprop engine. Engine installation design include reverse flow inlet and separator, controlled from the cockpit, that limited ingestion of solid particulates during ground operations. The flight tests verified proper air feed to the engine with the separator turned on and off. The carried out investigation of the intake system excluded possibility of hazardous engine operation, such as compressor stall, surge or flameout and potential airflow disturbance causing damaging vibration of the engine body. Finally, we present evaluation of total power losses associated with engine integration with the airframe.
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OPARA, Tadeusz. "History and future of turbine aircraft engines." Combustion Engines 127, no. 4 (2006): 3–18. http://dx.doi.org/10.19206/ce-117335.
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This paper discusses stages of development of air propulsion from piston engines up to three-rotor turbine ones. Limitations in speed and altitude of flight, caused by traditional system of a piston engine and an airscrew, became an impulse to conduct research on jet propulsion. Accomplishments of the designers of the first jet-propelled engines: F. Whitle and H. von Ohain are a reflection of rivalry in this field. In the second half of the 20th centur y turbine propulsion (turbojet, turboprop and helicopter engines) dominated air force and civil aviation. In 1960 the age of turbofans began, owing to better operating properties and electronic and digital systems of automatic regulation. Further development of turbine engines is connected with application of qualitatively new materials (particularly composites), optimization of the shape of compressor and turbine blades and technologies of their production. The paper discusses design changes decreasing the destructive effects of foreign matter suction and indicates the possibility of increasing the maneuverability of airplanes by thrust vectoring. Finally, development prospects of turbine propulsion are analyzed.
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Knežević, Vlatko, Josip Orović, Ladislav Stazić, and Jelena Čulin. "Fault Tree Analysis and Failure Diagnosis of Marine Diesel Engine Turbocharger System." Journal of Marine Science and Engineering 8, no. 12 (2020): 1004. http://dx.doi.org/10.3390/jmse8121004.
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The reliability of marine propulsion systems depends on the reliability of several sub-systems of a diesel engine. The scavenge air system is one of the crucial sub-systems of the marine engine with a turbocharger as an essential component. In this paper, the failures of a turbocharger are analyzed through the fault tree analysis (FTA) method to estimate the reliability of the system and to predict the cause of failures. The quantitative method is used for assessing the probability of faults occurring in the turbocharger system. The main failures of a scavenge air sub-system, such as air filter blockage, compressor fouling, turbine fouling (exhaust side), cooler tube blockage and cooler air side blockage, are simulated on a Wärtsilä-Transas engine simulator for a marine two-stroke diesel engine. The results obtained through the simulation can provide improvement in the maintenance plan, reliability of the propulsion system and optimization of turbocharger operation during exploitation time.
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Calmon, J. "From Sir Frank Whittle to the year 2000 — what is new in propulsion?" Aeronautical Journal 92, no. 920 (1988): 397–408. http://dx.doi.org/10.1017/s0001924000016535.
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It is with great admiration and much humility that I am able to give this talk in front of Sir Frank Whittle, universally recognised as the genuine pioneer of turbojet propulsion in the formula that made a success of aviation. As a matter of fact, the patent request filed by Sir Frank Whittle in 1930 (Fig. 1) comprised all the components of today’s turbojets: multi-stage axial compressor followed by a centrifugal compressor, combustion chamber, turbine coupled direct to the compressor and propulsion nozzle. In April 1937, with the assistance of British Thomson Houston, Sir Frank Whittle ran his first turbojet on the bench at a thrust of 200 daN (Fig. 2). The year after saw the beginning of the Whittle Wl turbojet tests at a thrust of 380 daN. This engine was to receive consecration by a first flight in May 1941 in a Gloster E28/39 specially built for the purpose. Subsequently, this aircraft was fitted with a 650 daN version incorporating an air cooled turbine.
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Meier, E., and J. Czerwinski. "Turbocharging Systems With Control Intervention for Medium Speed Four-Stroke Diesel Engines." Journal of Engineering for Gas Turbines and Power 111, no. 3 (1989): 560–69. http://dx.doi.org/10.1115/1.3240291.
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The turbocharging systems of highly boosted four-stroke diesel engines (BMEP 25 bar/363 psi) have to cope with two basic problems: lack of air and compressor surge at reduced engine speed. In the case of medium speed engines for ship propulsion and stationary applications, the following three control interventions have proved to be successful solutions: (1) waste gating air or exhaust gas at full load and speed, (2) using a compounded or independent exhaust gas driven power turbine that can be shut off at part load and speed, and (3) blowing air from the compressor outlet to the turbine inlet through a controlled bypass. The effect of these control interventions on engine performance is shown by examples and analyzed by means of characteristic quantities for the efficiency of the turbocharging system and the engine. The definitions and meanings of these quantities are explained in the first part of the paper.
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Alhassani, Abdulla Khamis, Mohanad Tarek Mohamed, Mohammed Fares, and Sharul Sham Dol. "Shock Waves Analysis of the Novel Intake Design System for a Scramjet Propulsion." WSEAS TRANSACTIONS ON SYSTEMS 20 (April 15, 2021): 67–75. http://dx.doi.org/10.37394/23202.2021.20.9.
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The supersonic combustion scramjet in the inlet applies the shock waves compression mechanism tosubstitute the actual compressor from a gas turbine engine. The scramjet works with combustion of fuel throughthe air stream in supersonic condition at least with Mach 5. Novel design of a scramjet intake system was madewith variations in the angle of the fins and entrance width. The best combination of diameter and inclinationangle was 1.75 m and 15 degrees, respectively. The findings were able to increase the oblique shock waveinteractions and supplicate effective combustion and reduce pressure losses for the effective application ofscramjet system, which can be significant for aerospace industry.
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Mehta, U., J. Bowles, J. Melton, L. Huynh, and P. Hagseth. "Water injection pre-compressor cooling assist space access." Aeronautical Journal 119, no. 1212 (2015): 145–71. http://dx.doi.org/10.1017/s0001924000010319.
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AbstractAdvances in space activity are linked to reductions in launch cost. Air-breathing propulsion-assisted flight systems offer the potential for revolutionary change of the space operations paradigm. Horizontal launch of a space-access system provides mission flexibility, responsiveness, and affordability. One way to reduce launch cost is to increase the Mach number at which a launch vehicle is staged from a carrier aircraft. Without exceeding the engine and airframe design limits, the pre-compressor cooling technology allows an operational aircraft to operate at Mach numbers and altitudes beyond its basic operational limits. This is an essential, near-term technology for reducing launch cost to place small-weight payloads in low Earth orbit. The advantage of this technology is assessed with a modified McDonnell Douglas QF-4C aircraft. Payloads are unachievable or marginal with an unmodified QF-4C. However, payloads weighing around 150 pounds are plausible with this aircraft when incorporating the water injection pre-compressor cooling (WIPCC) technology.
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Lluesma-Rodríguez, Federico, Temoatzin González, and Sergio Hoyas. "CFD Simulation of a Hyperloop Capsule Inside a Low-Pressure Environment Using an Aerodynamic Compressor as Propulsion and Drag Reduction Method." Applied Sciences 11, no. 9 (2021): 3934. http://dx.doi.org/10.3390/app11093934.
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One of the most restrictive conditions in ground transportation at high speeds is aerodynamic drag. This is even more problematic when running inside a tunnel, where compressible phenomena such as wave propagation, shock waves, or flow blocking can happen. Considering Evacuated-Tube Trains (ETTs) or hyperloops, these effects appear during the whole route, as they always operate in a closed environment. Then, one of the concerns is the size of the tunnel, as it directly affects the cost of the infrastructure. When the tube size decreases with a constant section of the vehicle, the power consumption increases exponentially, as the Kantrowitz limit is surpassed. This can be mitigated when adding a compressor to the vehicle as a means of propulsion. The turbomachinery increases the pressure of part of the air faced by the vehicle, thus delaying the critical conditions on surrounding flow. With tunnels using a blockage ratio of 0.5 or higher, the reported reduction in the power consumption is 70%. Additionally, the induced pressure in front of the capsule became a negligible effect. The analysis of the flow shows that the compressor can remove the shock waves downstream and thus allows operation above the Kantrowitz limit. Actually, for a vehicle speed of 700 km/h, the case without a compressor reaches critical conditions at a blockage ratio of 0.18, which is a tunnel even smaller than those used for High-Speed Rails (0.23). When aerodynamic propulsion is used, sonic Mach numbers are reached above a blockage ratio of 0.5. A direct effect is that cases with turbomachinery can operate in tunnels with blockage ratios even 2.8 times higher than the non-compressor cases, enabling a considerable reduction in the size of the tunnel without affecting the performance. This work, after conducting bibliographic research, presents the geometry, mesh, and setup. Later, results for the flow without compressor are shown. Finally, it is discussed how the addition of the compressor improves the flow behavior and power consumption of the case.
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Sohail, M. U., M. Hassan, S. H. R. Hamdani, and K. Pervez. "Effects of Ambient Temperature on the Performance of Turbofan Transonic Compressor by CFD Analysis and Artificial Neural Networks." Engineering, Technology & Applied Science Research 9, no. 5 (2019): 4640–48. http://dx.doi.org/10.48084/etasr.2998.
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The unfavorable effects of non-uniform temperature inlet flow on gas turbine engine operations have always been a hindrance on the performance of turbo-fan engines. The propulsive efficiency is a function of the overall efficiency of turbofan engine which itself is dependent on other ambient parameters. Variation of inlet compressor temperature due to increase or decrease of aircraft altitude, air density, relative humidity, and geographical climate conditions affects the compressor performance. This research focuses on the turbofan transonic compressor performance due to ambient temperature distortion. A novel predictive approach based on neural network model has been implemented to predict the compressor performance and behavior at different ambient temperature conditions. The model produces substantially accurate results when compared to the results of CFD analysis. Computational results from CFD analysis show that engine thrust decreases at higher altitude, lower density and lower pressure regions.
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Schmid, Norbert R., Dirk C. Leinhos, and Leonhard Fottner. "Steady Performance Measurements of a Turbofan Engine With Inlet Distortions Containing Co- and Counterrotating Swirl From an Intake Diffuser for Hypersonic Flight." Journal of Turbomachinery 123, no. 2 (2000): 379–85. http://dx.doi.org/10.1115/1.1343466.
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The influence of distorted inlet flow on the steady and unsteady performance of a turbofan engine, which is a component of an air-breathing combined propulsion system for a hypersonic transport aircraft, is reported in this paper. The performance and stability of this propulsion system depend on the behavior of the turbofan engine. The complex shape of the intake duct causes inhomogeneous flow at the engine inlet plane, where total pressure and swirl distortions are present. The S-bend intakes are installed axisymmetrically left and right into the hypersonic aircraft, generating axisymmetric mirror-inverted flow patterns. Since all turbo engines of the propulsion system have the same direction of rotation, one distortion corresponds to a corotating swirl at the low pressure compressor (LPC) inlet while the mirror-inverted image counterpart represents a counterrotating swirl. Therefore the influence of the distortions on the performance and stability of the ‘CO’ and ‘COUNTER’ rotating turbo engine are different. The distortions were generated separately by an appropriate simulator at the inlet plane of a LARZAC 04 engine. The results of low-frequency measurements at different engine planes yield the relative variations of thrust and specific fuel consumption and hence the steady engine performance. High-frequency measurements were used to investigate the different influence of CO and COUNTER inlet distortions on the development of LPC instabilities.
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Донець, О. Д., та В. П. Іщук. "КОНЦЕПЦІЯ СТВОРЕННЯ СИЛОВОЇ УСТАНОВКИ СІМЕЙСТВА РЕГІОНАЛЬНИХ ПАСАЖИРСЬКИХ ЛІТАКІВ АН-148/АН-158". Open Information and Computer Integrated Technologies, № 84 (2 липня 2019): 50–63. http://dx.doi.org/10.32620/oikit.2019.84.02.
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The basic results of calculation and research works carried out in the process of creation of power unit of regional passenger airplanes’ family are given. The design features of the propulsion engines and engine of the auxiliary power plant are described. The aforementioned propulsion system includes propulsion engines D-436-148 and engine AI-450-MS of auxiliary power plant. In order to comply with the requirements of Section 4 of the ICAO standard (noise reduction of the aircraft in site), in part of ensuring the noise reduction of engines, when creating the power plant of the An-148/An-158 aircraft family, a single- and double-layer acoustic filler was used in the structure of the engine nacelle and air intake. The use of electronic system for automatic control of propulsion engines such as FADEC and its integration into the digital airborne aircraft complex ensured the operation of engines, included in the power plant provided with high specific fuel consumption, as well as increased the level of automation of the power plant control and monitoring, and ensured aircraft automation landing in ICAO category 3A. In addition, the use of the aforementioned electronic system, allowed to operate the power plant of the aircraft in accordance with technical status. The use of the AI-450-MS auxiliary power plant with an electronic control system such as FADEC, and the drive of the service compressor from a free turbine, eliminated the effect of changes in power and air takeoff, on the deviation of the engine from optimal mode, which also minimized the fuel consumption. The use of fuel metering system TIS-158, allowed to ensure control of its condition and assemblies, without the use of auxiliary devices, built-in control means. In the fire protection system, the use of the electronic control and monitor unit, as well as the use of digital serial code for the exchange of information between the elements of the system and the aircraft systems, has reduced the number of connections, which increased the reliability of the system and reduced its weight characteristics.
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Wang, Yu, and Zhen Luo. "Computational Investigation on Centrifugal Compressor Performance at Various Altitudes." Advanced Materials Research 230-232 (May 2011): 1123–28. http://dx.doi.org/10.4028/www.scientific.net/amr.230-232.1123.
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Small gas turbine engines have been considered as a potential and popular mean of propulsion for Unmanned Aerial Vehicles (UAV). With the advantage of high thrust/power-to-weight-ratio from these engines, small aircraft can have larger payload allowance and higher altitude capability. However, at present, these gas turbine engines are not mature enough to perform critical mission for UAV. To be used for such critical mission, these gas turbine engines need a better reliability, efficiency and endurance. The capability of the engine to work efficiently in conditions at different altitude with the variant of air density is a critical factor related to higher operational ceiling. Hence this work aims to present a Computational Fluid Dynamics (CFD) simulation approach focusing on centrifugal compressors which are applied to turbo machines. A computational method is developed for studying the performance of small gas turbine engines over a range of altitude and ambient temperatures under different engine rates, and a centrifugal compressor simulation model is generated by using CFD techniques. Through numerical solutions obtained for different mesh sets the finest mesh of the model was determined. The performance curves obtained by the CFD simulation has been compared with the results obtained from the analytical method.
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Filsinger, Dietmar, Gen Kuwata, and Nobuyuki Ikeya. "Tailored Centrifugal Turbomachinery for Electric Fuel Cell Turbocharger." International Journal of Rotating Machinery 2021 (September 27, 2021): 1–14. http://dx.doi.org/10.1155/2021/3972387.
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Hydrogen fuel cell technology is identified as one option for allowing efficient vehicular propulsion with the least environmental impact on the path to a carbon-free society. Since more than 20 years, IHI is providing charging systems for stationary fuel cell applications and since 2004 for mobile fuel cell applications. The power density of fuel cells substantially increases if the system is pressurized. However, contaminants from fuel cell system components like structural materials, lubricants, adhesives, sealants, and hoses have been shown to affect the performance and durability of fuel cells. Therefore, the charging system that increases the pressure and the power density of the stacks inevitably needs to be oil-free. For this reason, gas bearings are applied to support the rotor of a fuel cell turbocharger. It furthermore comprises a turbine, a compressor, and, on the same shaft, an electric motor. The turbine utilizes the exhaust energy of the stack to support the compressor and hence lower the required electric power of the air supply system. The presented paper provides an overview of the fuel cell turbocharger technology. Detailed performance investigations show that a single-stage compressor with turbine is more efficient compared to a two-stage compressor system with intercooler. The turbine can provide more than 30% of the required compressor power. Hence, it substantially increases the system efficiency. It is also shown that a fixed geometry turbine design is appropriate for most applications. The compressor is of a low specific speed type with a vaneless diffuser. It is optimized for operating conditions of fuel cell systems, which typically require pressure ratios in the range of 3.0.
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Cican, Grigore, Marius Deaconu, and Daniel-Eugeniu Crunteanu. "Impact of Using Chevrons Nozzle on the Acoustics and Performances of a Micro Turbojet Engine." Applied Sciences 11, no. 11 (2021): 5158. http://dx.doi.org/10.3390/app11115158.
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This paper presents a study regarding the noise reduction of the turbojet engine, in particular the jet noise of a micro turbojet engine. The results of the measurement campaign are presented followed by a performances analysis which is based on the measured data by the test bench. Within the tests, beside the baseline nozzle other two nozzles with chevrons were tested and evaluated. First type of nozzle is foreseen with eight triangular chevrons, the length of the chevrons being L = 10 percentages from the equivalent diameter and an immersion angle of I = 0 deg. For the second nozzle the length and the immersion angle were maintained, only the chevrons number were increased at 16. The micro turbojet engine has been tested at four different regimes of speed. The engine performances were monitored by measuring the fuel flow, the temperature in front of the turbine, the intake air flow, the compression ratio, the propulsion force and the temperature before the compressor. In addition, during the testing, the vibrations were measured on axial and radial direction which indicate a normal functioning of the engine during the chevron nozzles testing. Regarding the noise, it was concluded that at low regimes the noise doesn’t presents any reduction when using the chevron nozzles, while at high regimes an overall noise reduction of 2–3 dB(A) was achieved. Regarding the engine performances, a decrease in the temperature in front of the turbine, compression ratio and the intake air and fuel flow was achieved and also a drop of few percent of the propulsion force.
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Schmidt, T., V. Gümmer, and M. Konle. "Potential of surrogate modelling in compressor casing design focussing on rapid tip clearance assessments." Aeronautical Journal 125, no. 1291 (2021): 1587–610. http://dx.doi.org/10.1017/aer.2021.39.
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ABSTRACTLosses induced by tip clearance limit decisive improvements in the system efficiency and aerodynamic operational stability of aero-engine axial compressors. The tendency towards even lower blade heights to compensate for higher fluid densities aggravates their influence. Generally, it is emphasised that the tip clearance should be minimised but remain large enough to prevent collisions between the blade tip and the casing throughout the entire mission. The present work concentrates on the development of a preliminary aero-engine axial compressor casing design methodology involving meta-modelling techniques. Previous research work at the Institute for Turbomachinery and Flight Propulsion resulted in a Two-Dimensional (2D) axisymmetric finite element model for a generic multi-stage high-pressure axial compressor casing. Subsequent sensitivity studies led to the identification of significant parameters that are important for fine-tuning the tip clearance via specific flange design. This work is devoted to an exploration of the potential of surrogate modelling in preliminary compressor casing design with respect to rapid tip clearance assessments and its corresponding precision in comparison with finite element results. Reputed as data-driven mathematical approximation models and conceived for inexpensive numerical simulation result reproduction, surrogate models show even greater capacity when linked with extensive design space exploration and optimisation algorithms.Compared with high-fidelity finite element simulations, the reductions obtained in computational time when using surrogate models amount to 99.9%. Validated via statistical methods and dependent on the size of the training database, the precision of surrogate models can reach down to the range of manufacturing tolerances. Subsequent inclusion of such surrogate models in a parametric optimisation process for tip clearance minimisation rapidly returned adaptions of the geometric design variables.
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Délery, J. M. "Shock phenomena in high speed aerodynamics: still a source of major concern." Aeronautical Journal 103, no. 1019 (1999): 19–34. http://dx.doi.org/10.1017/s0001924000065076.
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Abstract Shockwaves are present in a flow as soon as the Mach number becomes supersonic. Being viscous phenomena, Shockwaves are a source of drag which can be predominant when the Mach number is significantly higher than one. In supersonic air intakes, the production of entropy by shocks is felt as a loss in efficiency. At high Mach numbers, Shockwaves produce a considerable temperature rise leading to severe heating problems, complicated by real gas effects. The intersection - or interference - of two shocks gives rise to complex wave patterns containing slip-lines and associated shear layers whose impingement on a nearby surface can cause detrimental pressure and heat transfer loads. The impact of a Shockwave on a boundary layer is the origin of strong viscous interactions which remain a limiting factor in the design of transonic wings, supersonic air intakes, propulsive nozzles and compressor cascades. More effort is needed to improve prediction of these interactions and to devise new techniques to control such phenomena.
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Işık, Gültekin, Selçuk Ekici, and Gökhan Şahin. "A neural network model for UAV propulsion system." Aircraft Engineering and Aerospace Technology 92, no. 8 (2020): 1177–84. http://dx.doi.org/10.1108/aeat-04-2020-0064.
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Purpose Determining the performance parameters of the propulsion systems of the aircraft, which is the key product of the aviation industry, plays a critical role in reducing adverse environmental impacts. Therefore, the purpose of this paper is to present a temperature performance template for turbojet engines at the design stage using a neural network model that defines the relationship between the performance parameters obtained from ground tests of a turbojet engine used in unmanned aerial vehicles (UAV). Design/methodology/approach The main parameters of the flow passing through the engine of the UAV propulsion system, where ground tests were performed, were obtained through the data acquisition system and injected into a neural network model created. Fifteen sensors were mounted on the engine – six temperature sensors, six pressure sensors, two flow meters and one load cell were connected to the data acquisition system to make sense of this physical environment. Subsequently, the artificial neural network (ANN) model as a complement to the approach was used. Thus, the predicted model relationship with the experimental data was created. Findings Fuel flow and thrust parameters were estimated using these components as inputs in the feed-forward neural network. In the network experiments to estimate fuel flow parameter, r-square and mean absolute error were calculated as 0.994 and 0.02, respectively. Similarly, for thrust parameter, these metrics were calculated as 0.994 and 1.42, respectively. In addition, the correlation between fuel flow, thrust parameters and each input parameters was examined. According to this, air compressor inlet (ACinlet,temp) and outlet (ACoutlet,temp) temperatures and combustion chamber (CCinlet,temp, CCoutlet,temp) temperature parameters were determined to affect the output the most. The proposed ANN model is applicable to any turbojet engines to model its behavior. Practical implications Today, deep neural networks are the driving force of artificial intelligence studies. In this study, the behavior of a UAV is modeled with neural networks. Neural networks are used here as a regressor. A neural network model has been developed that predicts fuel flow and thrust parameters using the real parameters of a UAV turbojet engine. As a result, satisfactory findings were obtained. In this regard, fuel flow and thrust values of any turbojet engine can be estimated using the neural network hyperparameters proposed in this study. Python codes of the study can be accessed from https://github.com/tekinonlayn/turbojet. Originality/value The originality of the study is that it reports the relationships between turbojet engine performance parameters obtained from ground tests using the neural network application with open source Python code. Thus, small-scale unmanned aerial propulsion system provides designers with a template showing the relationship between engine performance parameters.
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Choi, Dong-Woon, Cho-Won Lee, Duk-Yeon Lee, Dong-Wook Lee, and Han-Ul Yoon. "A Hybrid Soft Actuator Inspired by Grass-Spike: Design Approach, Dynamic Model, and Applications." Applied Sciences 10, no. 23 (2020): 8525. http://dx.doi.org/10.3390/app10238525.
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This paper presents the bio-mimetic design approach, the dynamic model, and potential applications for a hybrid soft actuator. The proposed hybrid soft actuator consists of two main parts: a cylinder-shaped rigid core and soft silicone spikes wrapped around the core’s surface. The key idea of the proposed design approach is to mimic the movement of a grass-spike at a functional level by converting the vibration force generated by a small electric motor with a counterweight in the rigid core into a propulsion force produced by the elastic restoration of the spikes. One advantage of this design approach is that the hybrid soft actuator does not need to be tethered by a tube line from an air compressor and is more amenable to fine control. In addition, the hybrid soft actuator can be modularized with a wire and a tubular passage, which in turn work as a linear actuator. The dynamic model of the hybrid soft actuator can be derived by applying Lagrangian mechanics, and unknown system parameters can be identified by the optimization process based on the empirical data. Two applications—an elbow manipulator and a robotic hand grasper—demonstrate the feasibility of the proposed actuator to perform a muscle-tendon action successfully.
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Kolios, Vasileios, Ioannis Templalexis, Ioannis Lionis, Emmanouil Antonogiannakis, and Petros Kotsiopoulos. "F100-PW-229 Engine Fault Detection Based on Real Time Data." MATEC Web of Conferences 304 (2019): 03006. http://dx.doi.org/10.1051/matecconf/201930403006.
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Gas turbine engines exhibit very high maintenance costs. Moreover, in the case of aero applications an in-flight engine incidence, shall, by all means, be avoided, a condition that drives total maintenance costs even higher. A measure in favor of balancing these costs is to monitor continuously the variation of engine performance data recorded during flight, establish methods to deduce useful information regarding the engine “health” status and, as a result, take appropriate actions to maintain a good engine operating condition. The current work presents such a method tailored on the “F100-PW-229” engine that is operated by the ellenic Air Force as the propulsion system of the “F-16 block 52M” aircraft [3]. CEDATS and MS Excel were the computational tools used for the current engine performance study. CEDATS is a software developed for the engine users. It provides basic data trend monitoring functions and engine fault warnings. It is well known that there is always space for improvement for such health monitoring tools since there are cases where engine operating faults are not captured. Within the frame of the current work, a data post – processing method on the engine performance data time series was applied using MS Excel, in order to raise early warnings of an uncaptured compressor operating fault.
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Elmahmodi, Aiman, Nikola Davidovic, and Ramadan A. Al-Madani. "Propulsion system based on compressed air due to rotor blade rotation." International Journal of Smart Grid and Clean Energy, 2014. http://dx.doi.org/10.12720/sgce.3.3.263-269.
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Gowing, S., T. Mori, and S. Neely. "Research on Two Phase Waterjet Nozzles." Journal of Fluids Engineering 132, no. 12 (2010). http://dx.doi.org/10.1115/1.4002999.
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Air-augmented waterjets derive their propulsion from compressed gas mixed directly into the main flow. The gas bubbles expand as the mixture passes through the pressure gradient of the convergent nozzle, and energy is imparted to the water from the air in a complex fashion. This experiment measures the exchange of air and water energy for three nozzles over a range of flowrates and void fractions using compressed air injected and mixed upstream of the nozzle entrance. Pressures and nozzle thrust are measured to examine flow changes. The results are compared with predictions from a one-dimensional bubbly flow model. The measured efficiencies are lower than or comparable to predicted values.
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Ji, Zhixing, Jiang Qin, Kunlin Cheng, He Liu, Silong Zhang, and Peng Dong. "Design and Performance of a Compact Air-Breathing Jet Hybrid-Electric Engine Coupled With Solid Oxide Fuel Cells." Frontiers in Energy Research 8 (February 15, 2021). http://dx.doi.org/10.3389/fenrg.2020.613205.
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A compact air-breathing jet hybrid-electric engine coupled with solid oxide fuel cells (SOFC) is proposed to develop the propulsion system with high power-weight ratios and specific thrust. The heat exchanger for preheating air is integrated with nozzles. Therefore, the exhaust in the nozzle expands during the heat exchange with compressed air. The nozzle inlet temperature is obviously improved. SOFCs can directly utilize the fuel of liquid natural gas after being heated. The performance parameters of the engine are acquired according to the built thermodynamic and mass models. The main conclusions are as follows. 1) The specific thrust of the engine is improved by 20.25% compared with that of the traditional jet engine. As pressure ratios rise, the specific thrust increases up to 1.7 kN/(kg·s−1). Meanwhile, the nozzle inlet temperature decreases. However, the temperature increases for the traditional combustion engine. 2) The power-weight ratio of the engine is superior to that of internal combustion engines and inferior to that of turbine engines when the power density of SOFC would be assumed to be that predicted for 2030. 3) The total pressure recovery coefficients of SOFCs, combustors, and preheaters have an obvious influence on the specific thrust of the engine, and the power-weight ratio of the engine is strongly affected by the power density of SOFCs.
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Roberts, Rory A., and Daniel D. Decker. "Control Architecture Study Focused on Energy Savings of an Aircraft Thermal Management System." Journal of Dynamic Systems, Measurement, and Control 136, no. 4 (2014). http://dx.doi.org/10.1115/1.4026412.
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The next generation of aircraft will face more challenging demands in both electrical and thermal loads. The larger thermal loads reduce the propulsion system efficiency by demanding bleed air from the main engine compressor or imposing a shaft load on the high or low pressure shaft. The approach adopted to power the thermal management system influences the overall fuel burn of the aircraft for a given mission. To assess these demands and to explore conceptual designs for the electrical and thermal management system, a dynamic vehicle level tip-to-tail (T2T) model has been developed. The T2T model captures and quantifies the energy exchanges throughout the aircraft. The following subsystems of the aircraft are simulated in the T2T model: air vehicle system, propulsion system, adaptive power thermal management system, fuel thermal management system, electrical system, and actuator system. This paper presents trade studies evaluating the impact of various approaches in power take-off from the main engine and approaches in control strategy. The trade studies identify different control strategies resulting in significant fuel savings for a given mission profile.
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"Design of Multi-Stage Axial Flow Compressor and Validation using Numerical Simulations." International Journal of Innovative Technology and Exploring Engineering 9, no. 2 (2019): 2320–25. http://dx.doi.org/10.35940/ijitee.b7455.129219.
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The optimum yield of gas turbine engines has so far been driven on and around the operational efficiency of the compressor and in essence around the efficiency of the compressor blade. The efficacy of a compressor is ascertained substantially by the smoothness of the air flowing through it. In this present work, a multi-stage axial compressor in the Turbojet engine with an application for propulsion is designed based on thermodynamic calculations. The calculations were carried out employing the principles of thermodynamics, and aerodynamics along the mean streamline based on the technique of a velocity triangle in the lack of inlet guide vanes. The coordinates for the blade profile has been calculated on and around the premise of the calibrated blade base profile. The model for the seven-stage axial flow compressors based on thermodynamic calculations was devised and analyzed utilizing computational fluid dynamics methodology. The multiple reference frame approach was used to represent the impact of both rotating and stationary components and the simulation for the first stage was conducted using a periodic approach. For the intent of the verification, a comparison was made between the analytical values and the simulated values and the variation between these values was found to be 16.7%. Validation results demonstrate that the proposed method is valid and can be used for multi-stage axial compressor design and performance evaluation.
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Ali, Fakhre, Ioannis Goulos, and Vassilios Pachidis. "A Preliminary Design Tradeoff Study for an Advanced Propulsion Technology Rotorcraft at Mission Level." Journal of Engineering for Gas Turbines and Power 138, no. 1 (2015). http://dx.doi.org/10.1115/1.4031204.
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This paper aims to present an integrated rotorcraft (RC) multidisciplinary simulation framework, deployed for the comprehensive assessment of combined RC–powerplant systems at mission level. The proposed methodology comprises a wide-range of individual modeling theories applicable to RC performance and flight dynamics, as well as the gas turbine engine performance. The overall methodology has been deployed to conduct a preliminary tradeoff study for a reference simple cycle (SC) and conceptual regenerative twin-engine-light (TEL) and twin-engine-medium (TEM) RC configurations, modeled after the Airbus Helicopters Bo105 and Aérospatiale SA330 models, simulated under the representative mission scenarios. The installed engines corresponding to both reference RC are notionally modified by incorporating a heat exchanger (HE), enabling heat transfer between the exhaust gas and the compressor delivery air to the combustion chamber. This process of preheating the compressor delivery air prior to combustion chamber leads to a lower fuel input requirements compared to the reference SC engine. The benefits arising from the adoption of the on-board HE are first presented by conducting part-load performance analysis against the reference SC engine. The acquired results suggest substantial reduction in specific fuel consumption (SFC) for a major part of the operating power range with respect to both RC configurations. The study is further extended to quantify mission fuel burn (MFB) saving limit by conducting an extensive HE tradeoff analyses at mission level. The optimum fuel burn saving limit resulting from the incorporation of on-board HEs is identified within realistically defined missions, corresponding to modern RC operations. The acquired results from the mission analyses tradeoff study suggest that the suboptimum regenerated RC configurations are capable of achieving significant reduction in MFB, while simultaneously maintaining the respective airworthiness requirements in terms of one-engine-inoperative. The proposed methodology can effectively be regarded as an enabling technology for the comprehensive assessment of conventional and conceptual RC–powerplant systems at mission level.
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Han, Je-Chin. "Fundamental Gas Turbine Heat Transfer." Journal of Thermal Science and Engineering Applications 5, no. 2 (2013). http://dx.doi.org/10.1115/1.4023826.
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Gas turbines are used for aircraft propulsion and land-based power generation or industrial applications. Thermal efficiency and power output of gas turbines increase with increasing turbine rotor inlet temperatures (RIT). Current advanced gas turbine engines operate at turbine RIT (1700 °C) far higher than the melting point of the blade material (1000 °C); therefore, turbine blades are cooled by compressor discharge air (700 °C). To design an efficient cooling system, it is a great need to increase the understanding of gas turbine heat transfer behaviors within complex 3D high-turbulence unsteady engine-flow environments. Moreover, recent research focuses on aircraft gas turbines operating at even higher RIT with limited cooling air and land-based gas turbines burn coal-gasified fuels with a higher heat load. It is important to understand and solve gas turbine heat transfer problems under new harsh working environments. The advanced cooling technology and durable thermal barrier coatings play critical roles for the development of advanced gas turbines with near zero emissions for safe and long-life operation. This paper reviews fundamental gas turbine heat transfer research topics and documents important relevant papers for future research.
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"The early history of the aircraft gas turbine in Britain." Notes and Records of the Royal Society of London 45, no. 1 (1991): 79–108. http://dx.doi.org/10.1098/rsnr.1991.0004.
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There are two strands to the history of the aircraft gas turbine engine and jet propulsion in Britain. One strand has been told by Sir Frank Whittle (figure 1), the inventor of the turbojet engine, in Jet - the story of a pioneer (1953). 1 The other, less well known, was started by Dr Alan Arnold Griffith 2 (figure 2) of the Royal Aircraft Establishment (RAE). In 1926, in a report entitled ‘An aerodynamic theory of turbine design’ 3 , he proposed the use of a gas turbine as an aircraft power plant. In October of that year he put his proposals to a small committee from the Air Ministry and the Aeronautical Research Committee, which expressed itself unanimously in favour of prelim inary experiments. Accordingly, two sets of experiments were started. The first was on a stationary cascade of aerofoils and was reported by R.G. Harris and R.A. Fairthorne in September 1928 (figure 3).4 The other was on a model comprising a row of turbine and compressor blades of 4 inches outside diameter, mounted on one shaft and tested by sucking air through the blading (figure 4). From measurements of the losses, the efficiencies of stages could be deduced. The results, reported by W.C. Clothier in December 19295, showed that a maximum efficiency of 90% was obtained and an efficiency of 88.3% at a pressure ratio of 1.16.
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Staton, Bennett M., Brian T. Bohan, Marc D. Polanka, and Larry P. Goss. "Design, Analysis, and Manufacture of an Axial Length-Saving Disk-Oriented Engine." Journal of Engineering for Gas Turbines and Power 143, no. 1 (2020). http://dx.doi.org/10.1115/1.4048085.
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Abstract A disk-oriented engine was designed to reduce the overall length of a gas turbine engine, combining a single-stage centrifugal compressor and radial in-flow turbine (RIT) in a back-to-back configuration. The focus of this research was to understand how this unique flow path impacted the combustion process. Computational analysis was accomplished to determine the feasibility of reducing the axial length of a gas turbine engine utilizing circumferential combustion. The desire was to maintain circumferential swirl from the compressor through a U-bend combustion path. The U-bend reverses the outboard flow from the compressor into an integrated turbine guide vane in preparation for power extraction by the RIT. The computational targets for this design were a turbine inlet temperature of 1300 K, operating with a 3% total pressure drop across the combustor, and a turbine inlet pattern factor (PF) of 0.24 to produce a cycle capable of creating 668 N of thrust. By wrapping the combustion chamber about the circumference of the turbomachinery, the axial length of the entire engine was reduced. Reallocating the combustor volume from the axial to radial orientation reduced the overall length of the system up to 40%, improving the mobility and modularity of gas turbine power in specific applications. This reduction in axial length could be applied to electric power generation for both ground power and airborne distributive electric propulsion. Computational results were further compared to experimental velocity measurements on custom fuel–air swirl injectors at mass flow conditions representative of 668 N of thrust, providing qualitative and quantitative insight into the stability of the flame anchoring system. From this design, a full-scale physical model of the disk-oriented engine was designed for combustion analysis.
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Han, Je-Chin. "Advanced Cooling in Gas Turbines 2016 Max Jakob Memorial Award Paper." Journal of Heat Transfer 140, no. 11 (2018). http://dx.doi.org/10.1115/1.4039644.
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Gas turbines have been extensively used for aircraft engine propulsion, land-based power generation, and industrial applications. Power output and thermal efficiency of gas turbines increase with increasing turbine rotor inlet temperatures (RIT). Currently, advanced gas turbines operate at turbine RIT around 1700 °C far higher than the yielding point of the blade material temperature about 1200 °C. Therefore, turbine rotor blades need to be cooled by 3–5% of high-pressure compressor air around 700 °C. To design an efficient turbine blade cooling system, it is critical to have a thorough understanding of gas turbine heat transfer characteristics within complex three-dimensional (3D) unsteady high-turbulence flow conditions. Moreover, recent research trend focuses on aircraft gas turbines that operate at even higher RIT up to 2000 °C with a limited amount of cooling air, and land-based power generation gas turbines (including 300–400 MW combined cycles with 60% efficiency) burn alternative syngas fuels with higher heat load to turbine components. It is important to understand gas turbine heat transfer problems with efficient cooling strategies under new harsh working environments. Advanced cooling technology and durable thermal barrier coatings (TBCs) play most critical roles for development of new-generation high-efficiency gas turbines with near-zero emissions for safe and long-life operation. This paper reviews basic gas turbine heat transfer issues with advanced cooling technologies and documents important relevant papers for future research references.
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Kaiser, Sascha, Oliver Schmitz, and Hermann Klingels. "Aero Engine Concepts Beyond 2030: Part 2 - The Free-Piston Composite Cycle Engine." Journal of Engineering for Gas Turbines and Power, November 3, 2020. http://dx.doi.org/10.1115/1.4048993.
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Abstract Recognizing the attention currently devoted to the environmental impact of aviation, this three-part publication series introduces two new aircraft propulsion concepts for the timeframe beyond 2030. This second part presents the free-piston composite cycle engine concept. It is composed of a gas turbine topped with a free-piston system. The latter is a self-powered gas generator in which the internal combustion process drives an integrated air compressor. Here, several free-piston engines replace the high-pressure core of the gas turbine. Through the ability to work at much higher temperatures and pressures, the overall system efficiency can be increased significantly, and fuel burn as well as CO2 emissions reduce. The proposed free-piston composite cycle engine design is described in detail, and the sources of thermodynamic benefits are stated. Concrete engineering solutions consider the implementation into an aircraft. The free-piston design enables lower weight and size compared to a crankshaft-bound piston engine, as no mechanical transmission and lubrication system is required. The absence of a crankshaft and connecting rods eliminates reactive forces, reduces mechanical losses, and allows higher mean piston velocities. Facilitated through air lubrication, higher cylinder temperatures are viable. The reduction of heat losses enables cooling of the piston-cylinder with core fluid. The use of a sequential combustion chamber can enhance operability and tailor the production of NOx in low-altitude operation. A discussion of emissions affecting the environment shows the potential to reduce the climate impact of aviation.