Relevant bibliographies by topics / Ram Air Turbine

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  1. Journal articles
  2. Dissertations / Theses
  3. Book chapters
  4. Conference papers

Academic literature on the topic 'Ram Air Turbine'

Author: Grafiati
Published: 4 June 2021
Last updated: 11 February 2022

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Journal articles on the topic "Ram Air Turbine"

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Wang, Jian, Yue Liang Lu, and Xiao Tian Zhai. "Research on Ram Air Turbine Blade Properties." Applied Mechanics and Materials 779 (July 2015): 117–24. http://dx.doi.org/10.4028/www.scientific.net/amm.779.117.

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The Ram Air Turbine system is the emergency power system of aircraft. As the key parts, the blades aerodynamic characteristic effects the system properties. In this article, CFD numerical method will be used to research four blades properties of ram air turbine. We compare the blades work properties of each working condition, so that we can get which design is better. We used the CFD numerical method to design the RAT blade, we hope this method will be used in our future products design.
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Sinaga, Jorfri Boike, Azhar Azhar, Novri Tanti, and Sugiman Sugiman. "Perancangan Model Pembangkit Listrik Dengan Menggunakan Teknologi Pompa Tanpa Motor (Hydraulic Ram Pump)." MECHANICAL 8, no. 2 (April 15, 2018): 57. http://dx.doi.org/10.23960/mech.v8.i2.201709.

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This paper presents the design of parameters of hydraulic ram pump and hydraulic turbine to use the energy of flowing water for water supply to generate electrical power and irrigation. Design of parameters of hydraulic ram pump with head of water supply of 1,5 m was obtained: 1,25 in. diameter and 8 m length of drive pipe, 200 gr and 4,6 cm of weight and diameter of impulse valve, 4.200 cm3 of air chamber volume. The testing results of the hydraulic ram pump model shown that water could be pumped as far as the height of 7 m and 8 m, with the volume flow rate of 2,755 lit/men and 1,73 lit/men. Design of geometric parameters of cross flow hydraulic turbine with head of water supply of 1,75 m was obtained: 12 cm and 8 cm of external and internal diameter, 25 cm of runner width, and 18 of runner number. The testing results of the cross flow hydraulic turbine shown that power could be generated 83,47 W with the volume flow rate of 0,01 lit/s and the efficiency of 71,05 % at 799 rpm. The testing result also shown that with using volume flow rate of 0,003 lit/s, this turbine could be generated 23,39 W with the efficiency of 46,64 %. Technically the technology of hydraulic ram pump can be developped and used to supply of water for irrigation and generating of electrical power.
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SHIROKOV, Anton A., Dmitriy S. DEZHIN, and Marina V. ZDOROVA. "Development of an Electromagnetic Brake for Stabilizing the Ram Air Turbine Rotation Frequency." Elektrichestvo 8, no. 8 (2020): 37–43. http://dx.doi.org/10.24160/0013-5380-2020-8-37-43.

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Arumugam, Arunachaleswaran, Shyni Thomas, Muralidhar Madhusudan, S. Elangovan, and M. Sundararaj. "Utilisation of Ram Air Turbine on a Fighter Platform for Energy Extraction Failure Mode Study." Defence Science Journal 70, no. 6 (October 12, 2020): 583–89. http://dx.doi.org/10.14429/dsj.70.15789.

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Aircraft electrical system needs to be robust enough to cater for electrical power requirements of all the systems of the aircraft and all the safety/degraded mission critical systems in failure modes. Designing such a robust electrical system for a developmental aircraft program is a challenge. A developmental aircraft during its various phases would involve integration of additional systems and new weapons (in case of fighter aircraft). Integration of newer systems imposes fresh challenges in managing the electrical system architecture especially in failure modes. Weapon integration in a prototype fighter program is dynamic as newer contemporary weapons are developed at faster pace and ever evolving. Power crisis through existing on-board power generation systems in failure mode was felt during an indigenous aircraft development program. A novel idea of introducing a Ram Air Turbine and utilize the power generated during main alternator failure for critical systems was studied. The intention of this paper is to cover the details of the study carried out towards utlisation of such a Ram Air Turbine in landing phase for extraction of energy in case of main alternator failure.
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Price, Donald C., and B. Elliott Short,. "Thermal Design of an Airborne Computer Chassis With Air-Cooled, Cast Pin Fin Coldwalls." Journal of Heat Transfer 127, no. 1 (January 1, 2005): 11–17. http://dx.doi.org/10.1115/1.1839583.

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This paper documents the thermal design process required to provide effective thermal management for an airborne computer, consisting of 24 modules (two P/S modules and 22 PWB modules), which are edge-cooled to two cast, pin fin coldwalls. The computer chassis is mounted in an electronics pod mounted underneath the centerline of an aircraft. The pod consists of several electronics bays and a self-contained, air-cycle, environmental control system (ECS). The computer chassis is mounted in the forward bay, and the ECS is mounted in the rear bay of the electronics pod. The ECS is an air-cycle refrigeration system, which operates on captured ram air directed by an inlet/diffuser to an expansion turbine. This turbine produces low-pressure, chilled air, which is then directed through an air-to-liquid, load heat exchanger to produce chilled liquid. The chilled liquid is piped through small liquid lines to the forward bay of the pod, where the air-cooled computer chassis is located. The chilled liquid is converted back to chilled air in an air-to-liquid heat exchanger. The chilled air is supplied to the forward bay volume and is drawn through the computer chassis coldwalls by a fan integral to the computer chassis. The temperature of the chilled air, produced in this manner, becomes a strong function of the altitude and flight speed of the aircraft, because of the effect of these two parameters on the ram air mass flow rate and temperature at the inlet to the expansion turbine. The mass flow of the air used to cool the chassis is also a variable, because the density of the air is a function of the flight altitude and the fan has altitude-dependent operating characteristics. This fan provides the flow of air through the chassis. Emphasis is placed in the design process on the effect of the operating characteristics of the fan at altitude and the determination of the system performance curve associated with the pin fin coldwalls. This performance curve is controlled by the pressure drop characteristics of the pin fin coldwalls, which are a function of the Fanning f-factor and Colburn j-factor characteristics of the cast pin fin design. Design examples are used to demonstrate the design process.
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Paek, Seungyun, Kyeongsu Kim, Sungsoon Park, and Sejin Kwon. "Ground Simulation of High Altitude Test of Turbo-Refrigeration Cycle." International Journal of Turbo & Jet-Engines 35, no. 3 (July 26, 2018): 281–90. http://dx.doi.org/10.1515/tjj-2016-0045.

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Abstract This study proposes a new test approach for a ram air-driven turbo-refrigeration system. The flight performance of the air cycle turbo-refrigerator is indirectly verified through ground tests under various flight conditions, and the actual altitude performance is predicted through dimensional analysis and similarity based on the ground test results. In addition, correction of the Reynolds number is also considered for adequate prediction of performance. This study develops a turbo-refrigerator that consists of a radial turbine and a centrifugal compressor. As this simple system drives the reverse Brayton cycle, it acts as a refrigerator that relieves the heat load. Although the ram air and exhaust conditions are usually simulated in high altitude test facilities, they are very costly and not suitable for prototype development, which often demands requirement and specification changes. The proposed system is designed to deliver a cooling capacity over 2 kW through the heat exchanger at a Mach number of 0.8 and altitude up to 10 km. As a result of current study, the proposed test approach predicts that air cycle turbo-refrigeration system yields sufficient cooling capacity to comply with the requirements for the primary mission flight envelope under the hot day condition, despite slight performance degradation at high altitudes.
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Arumugam, Arunachaleswaran, Anoop Kabadwal, Rajeev Joshi, Siddarth Singh, Malteesh Prabhu, Amar Preet Singh, Srinivasan Elangovan, and M. Sundararaj. "Innovative Method for the Estimation of Closure Velocity between RAT Driven Drogue and IFR Probe Air to Air refueling Flight Trials." Defence Science Journal 70, no. 2 (March 9, 2020): 140–44. http://dx.doi.org/10.14429/dsj.70.14100.

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Air-to-air refueling for a fighter platform is a force multiplier in terms of increasing its combat radius and payload carrying ability. Adapting for such a facility especially for an aircraft under design and development is a challenging task. It requires rigorous ground and flight testing to meet the certification standards. One of important flight test parameter that needs to be validated for structural impact load calculations and certification needs is the closure velocity. The air-to-air refueller was equipped with a Ram-air-turbine powered drogue and chute system. An innovative methodology of estimating the closure velocity between the drogue of the mother aircraft and the in-flight refueling probe of the receiving aircraft was evolved. The method was employed and validated during the air-to-air refueling trials of a prototype fighter platform. The intention of this paper is to explain the methodology employed and deliberate the results obtained with respect to the air-to-air refueling certification.
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Jacobs, E. W. "Research Results for the Tornado Wind Energy System: Analysis and Conclusions." Journal of Solar Energy Engineering 107, no. 1 (February 1, 1985): 78–87. http://dx.doi.org/10.1115/1.3267659.

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The Tornado Wind Energy System (TWES) concept utilizes a wind-driven vortex confined by a hollow tower to create a low-pressure core intended to serve as a turbine exhaust reservoir. The turbine inlet flow is provided by a separate ram air supply. Numerous experimental and analytical research efforts have investigated the potential of the TWES as a wind energy conversion system (WECS). The present paper summarizes and analyzes much of the research to date on the TWES. A simplified cost analysis incorporating these research results is also included. Based on these analyses, the TWES does not show any significant promise of improving on either the performance or the cost of energy attainable by conventional WECS. The prospects for achieving either a system power coefficient above 0.20 or a cost of energy less than $0.50/kWh (1979 dollars) appear to be poor.
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Matrosov, Aleksandr Anatolievich, Olga Viktorovna Pavlenko, Evgenii Sergeevich Perchenkov, Alina Yurievna Slitinskaya, and Vitalii Dmitrievich Chuban'. "THE INFLUENCE OF THE TRACK BEHIND THE UNDERCARRIAGE ON THE FIELD OF SPEED IN THE REGION OF A RAM AIR TURBINE." TsAGI Science Journal 47, no. 6 (2016): 623–37. http://dx.doi.org/10.1615/tsagiscij.2017019464.

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CHIESA, Sergio, Marco FIORITI, and Roberta FUSARO. "POSSIBLE HYBRID PROPULSION CONFIGURATION FOR TRANSPORT JET AIRCRAFT." Aviation 20, no. 3 (September 29, 2016): 145–54. http://dx.doi.org/10.3846/16487788.2016.1200849.

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This research is aimed at studying the possible advantages of installing, for a hybrid propulsion aircraft, electric motors and related propellers into the dedicated supplementary nacelles. This innovative solution is different from the configuration, already studied for a regional turboprop (Chiesa et al.2013), in which the electric motors are in the same nacelles of the internal combustion engines. As it has been expected, it offers the advantages of avoiding mechanical links between the two units and, more importantly, can also be applied to jet aircraft. In fact, the main contribution of electric motors is expected during ground operations, take-off and descent phases (i.e. at low speed), in which it can be useful to integrate the propellers or even substitute the jet engines with them. At high speed, the propellers, of course, are configured in order to reduce drag. When considering the design of a new airliner concept, a preliminary design study is necessary to optimize the location of the supplementary nacelles. The nacelles, which only hold the electrical motor, can also be considered retractable, as is usual for a RAT (Ram Air Turbine). Please note that in the hybrid propulsion context, the RAT function can be clearly allocated to the electric motor, with the advantages of optimizing drag at high speed, taking into account installation problems.
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Dissertations / Theses on the topic "Ram Air Turbine"

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Akagi, Raymond. "Ram Air-Turbine of Minimum Drag." DigitalCommons@CalPoly, 2021. https://digitalcommons.calpoly.edu/theses/2261.

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The primary motivation for this work was to predict the conditions that would yield minimum drag for a small Ram-Air Turbine used to provide a specified power requirement for a small flight test instrument called the Boundary Layer Data System. Actuator Disk Theory was used to provide an analytical model for this work. Classic Actuator Disk Theory (CADT) or Froude’s Momentum Theory was initially established for quasi-one-dimensional flows and inviscid fluids to predict the power output, drag, and efficiency of energy-extracting devices as a function of wake and freestream velocities using the laws of Conservations of Mass, Momentum, and Energy. Because swirl and losses due to the effects of viscosity have real and significant impacts on existing turbines, there is a strong motivation to develop models which can provide generalized results about the performance of an energy-extractor, such as a turbine, with the inclusion of these effects. A model with swirl and a model with losses due to the effects of viscosity were incorporated into CADT which yielded equations that predicted the performance of an energy-extractor for both un-ducted and ducted cases. In both of these models, for this application, additional performance parameters were analyzed including the drag, drag coefficient, power output, power coefficient, force coefficient, and relative efficiency. For the un-ducted CADT, it is well known that the wake-to-freestream velocity ratio of 1/3 will give the maximum power extraction efficiency of 59.3%; this result is called the Betz limit. However, the present analysis shows that reduced drag for a desired power extraction will occur for wake-to-freestream velocity ratios higher than the value of 1/3 which results in maximum power extraction efficiency. This in turn means that a turbine with a larger area than the smallest possible turbine for a specified power extraction will actually experience a lower drag. The model with the inclusion of swirl made use of the Moment of Momentum Theorem applied to a single-rotor actuator disk with no stators, in addition to the laws of Conservation of Mass, Momentum, and Energy from the CADT. The results from the model w/swirl showed that drag remains unchanged while power extracted decreases with the addition of swirl, with swirl effects becoming more severe for tip speed ratios below about 5. As for CADT, reduced drag for a specified power extraction can be achieved when the wake-to-freestream velocity ratio is higher that than which provides maximum power extraction efficiency. The model w/losses due to viscosity incorporated the losses into the Conservation of Energy relationship. The results from the model w/losses showed that there is a distinct wake-to-freestream velocity ratio at which minimum drag for a specified power output is achieved, and that this velocity ratio is usually—but not always—higher than that for which the power extraction efficiency is a maximum. It was concluded that a lower drag for a specified power output of an energy-extractor can usually be achieved at a wake-to-freestream velocity ratio higher than that which produces the v maximum power extraction efficiency. The latter condition, known as the Betz limit for CADT, and which defines the minimum size for a turbine to provide a specified power extraction, is therefore not the correct target design condition to achieve lowest drag for a small Ram-Air Turbine to power BLDS.
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Villa, Victor Fidel. "EVALUATION OF DESIGN TOOLS FOR THE MICRO-RAM AIR TURBINE." DigitalCommons@CalPoly, 2015. https://digitalcommons.calpoly.edu/theses/1446.

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The development and evaluation of the design of a Micro-Ram Air Turbine (µRAT), a device being developed to provide power for an autonomous boundary layer measurement system, has been undertaken. The design tools consist of a rotor model and a generator model. The primary focus was on developing and evaluating the generator model for the prediction of generator brake power and output electrical power with and without rectification as a function of shaft speed and electrical load, with only basic manufacturer specifications given as inputs. A series of motored generator evaluation test were conducted at speeds ranging from 9,000 to 25,000 rpm for loads varying between 1 and 3.02 Ohms with output power of up to 80 Watts. Results demonstrated that predicted generated power was at or below 3% error when compared to measured results with about 1% uncertainty. A rotor model was also developed using basic blade element theory. This model neglected induced flow effects and was therefore expected to over predict rotor torque and power. A second rotor model that includes induced flow effects, the open source program X-Rotor, was also used to predict rotor power and for comparison to the blade element rotor model results. Both rotor models were evaluated through wind tunnel validation tests conducted on a turbine generator with two different 3.25 in diameter rotors, rotor-1 (untwisted blades) and rotor-2 (twisted blades). Wind tunnel validation test airspeeds varied between 71-110 mph with electrical loads ranging from 1-20 ohms. Results indicated power predictions to be 50-75% higher for the blade element model and 20-30% for X-Rotor results. The blade element rotor model was modified by applying the Prandtl tip-loss factor to approximately account for the induced flow effects; this addition brought predictions much closer to X-Rotor results. Based on the motor-driven generator test results, it is believed that most of the discrepancy in baseline rotor/generator validation test between predicted and observed power generated is due to inaccuracy in the rotor performance modelling with likely contributors to error being induced flow effects, crude section lift/drag modelling, and aero-elastic deformation. It is concluded that the proposed generator model is sufficient although direct torque measurements may be desired and further development of the µRAT design tools should focus on an improved rotor performance model.
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Book chapters on the topic "Ram Air Turbine"

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Aboutalebi, Payam, Fares M’zoughi, Izaskun Garrido, and Aitor J. Garrido. "Nueva estrategia de control para la reducción de oscilaciones en turbinas eólicas flotantes." In XLII JORNADAS DE AUTOMÁTICA : LIBRO DE ACTAS, 37–44. Servizo de Publicacións da UDC, 2021. http://dx.doi.org/10.17979/spudc.9788497498043.037.

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En este trabajo se ha propuesto una nueva estrategia de control para mejorar la estabilidad de turbinas eólicas flotantes (FWT). Al objeto de estudiar la reducción de oscilaciones no deseadas en el sistema, y en particular en los movimientos de cabeceo de la plataforma y de proa-popa de la nacelle, se ha considerado una plataforma tipo barcaza de forma cuadrada y equipada con cuatro columnas de agua oscilantes (OWC) colocadas de manera simétrica. De esta forma, las válvulas de control de flujo de aire de las cámaras de captura permiten operar las citadas columnas de aire para controlar los movimientos de la barcaza causados por la dinámica oscilatoria de la ola incidente. Para ello, se ha efectuado un análisis de los operadores de amplitud de respuesta (RAO) que permite implementar una nueva estrategia de control de conmutación para regular adecuadamente la transición apertura/cierre de las válvulas de control de flujo. Los resultados obtenidos muestran que la topología de plataforma híbrida propuesta, dotada de sistemas controlados OWC, presenta un mejor rendimiento que una plataforma análoga tradicional.
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Conference papers on the topic "Ram Air Turbine"

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Haid, Daniel, and John Justak. "Innovative Ram Air Turbine for Airborne Power Generation." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43437.

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An innovative high power density and low drag ram air turbine for airborne power generation has been developed. Future systems on military and commercial aircraft will require greater electrical power. Unfortunately, expanding the capacity of the electrical systems on current aircraft and ones in development can result in costly design changes, require recertification, and significantly impact performance. Powering these systems locally with batteries is often considered. However, operation time is limited by the battery and the additional weight can limit aircraft range. The innovative ram air turbine design configuration described here has a power density that can be significantly higher than batteries and a lower drag and greater integration flexibility than conventional ram air turbines. Unlike batteries, which have a finite specific energy, the ram air turbine is only limited by the flight time of the vehicle. This system has a ducted turbine located in a pod or fuselage interior, unlike current ram air turbines that are externally mounted and require direct exposure to the free-stream flow. The internally mounted ram air turbine contributes less to overall aerodynamic drag than current ram air turbines, allows for more power to be extracted in an equivalent design space, and offers reduced radar signature compared to present externally-bladed turbines. Computational analyses along with wind tunnel testing have been conducted in support of this design. A 25-inch (0.635 m) diameter turbine demonstrated 110 kW of electrical power over a wide range of Mach numbers and simulated altitudes.
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Walter, Miguel, and Dimitri Mavris. "Sequential Robust Design of a Ram Air Turbine." In 17th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-4408.

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Sanchez-Flores, J. A., J. Y. Gonzalez-Valdes, J. U. Liceaga-Castro, E. Liceaga-Castro, L. A. Amezquita-Brooks, O. Garcia-Salazar, and D. L. Martinez-Vazquez. "Experimental workbench for aircraft ram air micro-turbine generators." In 2017 IEEE International Autumn Meeting on Power, Electronics and Computing (ROPEC). IEEE, 2017. http://dx.doi.org/10.1109/ropec.2017.8261673.

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Saad, Magedi Moh M., Sofian Bin Mohd, and Mohd Fadhli Zulkafli. "A survey on the use of ram air turbine in aircraft." In 7TH INTERNATIONAL CONFERENCE ON MECHANICAL AND MANUFACTURING ENGINEERING: Proceedings of the 7th International Conference on Mechanical and Manufacturing Engineering, Sustainable Energy Towards Global Synergy. Author(s), 2017. http://dx.doi.org/10.1063/1.4981189.

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Steele, Robert F., Dale C. Paul, and Torgeir Rui. "Expectations and Recent Experience for Gas Turbine Reliability, Availability, and Maintainability (RAM)." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27655.

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Since the early 1990’s there have been significant changes in the gas turbine, and power generation market place. The ‘F-Class’ Gas Turbines, with higher firing temperatures, single crystal materials, increased compressor pressure ratios and low emission combustion systems that were introduced in the early 1990’s have gained significant field experience. Many of the issues experienced by these new product introductions have been addressed. The actual reliability growth and current performance of these advanced technology machines will be examined. Additionally, the operating profiles anticipated for many of the units installed during this period has been impacted by both changes in the anticipated demand and increases in fuel costs, especially the cost of natural gas. This paper will review how these changes have impacted the Reliability, Availability, and Maintainability performance of gas turbines. Data from the ORAP® System, maintained by Strategic Power Systems, Inc, will be utilized to examine the actual RAM performance over the past 10 to 15 years in relation to goals and expectations. Specifically, this paper will examine the reliability growth of the F-Class turbines since the 1990’s and examine the reliability impact of duty cycle on RAM performance.
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Xia Tianxiang, Lu Yueliang, and Zhang Dongyu. "Study on the rotation speed control method for Ram Air Turbine System." In CSAA/IET International Conference on Aircraft Utility Systems (AUS 2018). Institution of Engineering and Technology, 2018. http://dx.doi.org/10.1049/cp.2018.0298.

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Zhang, Xiangbo, Shuiting Ding, Farong Du, Fenzhu Ji, and Shengrong Guo. "Numerical Simulation on Aerodynamic Performance of Ram Air Turbine Based on Mixed Flow Field." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-88304.

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Ram air turbine (RAT) is an emergency power source to supply power in case of the main engine and auxiliary engine lost power. Which can extract energy from airflow through rotating turbine. So it is important to investigate turbine aerodynamic performances. According to some type of RAT, we established a numerical model based on Navier–Stokes equation in rotating frames of reference. Calculation domain is divided into three fluid domains. All three regions are linked in the form of interface. Aerodynamic performance of RAT is simulated with computational fluid dynamics (CFD) soft. The extracted power and rotor power coefficient are analyzed under different running conditions. Next, we also investigate RAT aerodynamic performance at different pitch angle and turbine speed. The pressure and velocity distribution on the blade surface are studied. Besides, the method of multiple rotation frame (MRF) is used to simulate mixed flow field of the RAT which pitch angle is adjustable. The simulation results show that: turbine output power and rotor power coefficient can meet the needs of aircraft by adjusting the pitch angle under various operation conditions. The optimal operating point could be obtained by calculating RAT aerodynamic performance. The distribution of blade surface pressure and velocity could provide an important reference for the optimization of turbine blade designing. MRF can be used to calculate turbine aerodynamic performance.
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von Rappard, Axel W., and Salvatore Della Villa. "Gas Turbine Performance of Mature, F- and Advanced Technologies 2000." In ASME Turbo Expo 2001: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2001. http://dx.doi.org/10.1115/2001-gt-0394.

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The contribution of the gas turbine in simple and combined cycle systems to power production in the United States has been steadily rising over the past 25 years. In 1998 their contribution to power production was approximately 15% and it increased over the past 5 years by 1.5 to 2%, annually. In parallel, the United States Department of Energy (DOE) has financially supported Advanced Technology development with good formulated goals for overall performance of plants including reliability, availability and maintainability (RAM). In this paper the authors evaluate RAM performance data from power plants over the past five years. This evaluation can be used as baseline or benchmark for further improvements. It takes into account the mode of operation being base load, cycling or peaking application and analyses the power plant on a year-by-year evaluation. All RAM-data came from the same source and are collected and analyzed according to standardized procedures. Availability will be reviewed for machines of different sizes and technologies. Maintainability will be analyzed as function of the size of units, energy production, and the mode of operation. Gas turbine simple and combined cycle power plants have been operated in peaking, cycling, base and continuous load operation. The flexibility is shown in different “Service Hours per Successful Start” and a correlation with the RAM parameters. To analyze and explain these differences will be the main result of this evaluation. The contribution shall help to evaluate the best solution for individual sites because efficiency and availability cannot always be increased in parallel.
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Altoma, Ahmed S., and Mohammed Ridha H. Alhakeem. "Design and Simulation of Electrical Emergency System in Aircraft using Ram Air Turbine." In 2018 IEEE International Conference on Electrical Systems for Aircraft, Railway, Ship Propulsion and Road Vehicles & International Transportation Electrification Conference (ESARS-ITEC). IEEE, 2018. http://dx.doi.org/10.1109/esars-itec.2018.8607299.

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Sakata, Kimio, Ryoji Yanagi, Akira Murakami, Shigemi Shindo, Shinji Honami, Atsushige Tanaka, and Ksazuo Shiraishi. "Experimental Study of Mixed Compression Air-Intake for Hypersonic Airbreathing Engines." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-349.

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Supersonic air-intake for Mach number higher than 2.5 is being investigated with experimental, analytical and computational methods. The study is performed in a part of the joint research program led by National Aerospace Laboratory (NAL) on the hypersonic airbreathing turbo-engines with subsonic ram combustion. The wind tunnel models are designed in two-dimensional mixed compression type with multi-shock system and tested in NAL’s Mach 4 supersonic wind tunnel. Pressure measurements and flow visualization by schlieren method, oil-flow and vapor screen techniques are being done. Here, the test results of Mach 4 and Mach 5 models are discussed. The Mach 4 model is fixed geometry with 5-shock system and the Mach 5 one is variable geometry with 6-shock and an isentropic compression surface. An expansion fore-plate was installed at the Mach 5 model inlet to accelerate the air-speed at the entry. The bleed systems at throat, ramp and cowl are adopted and evaluated in terms of pressure recovery and stability. Importance of establishment of the internal shock wave system, reduction of upstream Mach number of terminal shock wave and suppression of flow separation at diffusers are found. It is also found that ramp bleed is effective to confirm intake start and to minimize shock/boundary layer interaction.
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