Relevant bibliographies by topics / Engine thrust

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'Engine thrust'

Author: Grafiati
Published: 4 June 2025
Last updated: 23 June 2025

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the lists of relevant articles, books, theses, conference reports, and other scholarly sources on the topic 'Engine thrust.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Journal articles on the topic "Engine thrust"

1

Rabeta, Bismil, Mohammad A.F Ulhaq, Aswan Tajuddin, and Agus Sugiharto. "Simulasi Graphical User Interface Analisis Termodinamika Mesin Turboprop Menggunakan Perangkat Lunak Matlab R2020a." Jurnal Teknologi Kedirgantaraan 6, no. 2 (2021): 31–50. http://dx.doi.org/10.35894/jtk.v6i2.44.

Full text
Abstract:
A turboprop engine is a hybrid engine that delivers thrust or jet thrust and also drives the propeller. This is basically similar to a turbojet except the turbine works through the main shaft which is connected to the reduction gear to rotate the propeller in front of the engine. This research was conducted to determine the development of engine performance in thermodynamic analysis so as to know the value of each parameter on a engine that has been developing for 20 to 50 years with different engine manufacturing. So that in this study a comparison of the thermodynamic analysis of the TPE-331, PT6A-42 and H85-200 engines was carried out. In the TPE331-10, PT6A-42, and H85-200 turboprop engines the value of fuel to air ratio and shaft work increases with increasing altitude while compressor work, fuel flow rate, shaft power, propeller thrust, jet thrust, total thrust, equivalent engine power and ESFC decrease with increasing altitude. Furthermore, the turbine's working value is relatively stable as the altitude increases. After that, the value of compressor work and turbine work on the PT6A-42 engine was greater than that of the TPE331-10, and H85-200 engines. However, the value of the fuel to air ratio, fuel flow rate, shaft power, jet thrust, equivalent engine power and ESFC on the H85-200 engine was greater than the TPE331-10 and PT6A engines. Furthermore, at sea level, the value of the axle, propeller thrust, and total thrust on the H85-200 engine is greater than that of the TPE331-10 and PT6A-42 engines but at an altitude of 25,000 ft, the PT6A-4 engine has a greater value than that of the TPE331-10 and PT6A-42 engines. TPE331-10, and H85-200 engines.
APA, Harvard, Vancouver, ISO, and other styles
2

Dolgopolov, S. I. "Determination of the effect of internal and external factors on the thrust spread of a cluster propulsion system." Technical mechanics 2022, no. 2 (2022): 47–58. http://dx.doi.org/10.15407/itm2022.02.047.

Full text
Abstract:
The thrust spread of a stand-alone rocket engine caused by external (the pressure and temperature of the propellant components at the engine inlet) and internal (spread in the geometry and operating conditions of the engine units and assemblies) factors is known from experimental tests or can be computed by a known procedure. As a rule, liquid-propellant propulsion systems (LPPSs) of launch vehicle lower stages include a cluster of several engines, whose thrust spread cannot often be determined from firing tests due to limited capabilities of bench equipment. The aim of this work is to develop an approach to determining the thrust spread of an LPPS comprising a cluster of two and more engines. For a multiengine propulsion system, this methodological approach also includes the development of a mathematical model of engine interaction in an LPPS and calculations of an LPPS startup at different combinations of spread in the external and internal factors in cases where the parameter spreads of all engines are both identical and different. For an LPPS with two engines and a common oxidizer feed pipeline, the paper gives an example of calculating the effect of external and internal factors on the thrust spread of each engine and the LPPS as a whole during an LPPS startup. . It is shown that the calculated spread of the 90 percent thrust (combustion chamber pressure) time lies in the range – 0.0917 s to +0.0792 s (engine 1) and –0.0941 s to +0.0618 s (engine 2). The calculated variations of the combustion chamber pressure (engine thrust) from its nominal value lie in the range –6.2 percent to +7.0 percent (engine 1) and -6.8 percent to +6.3 percent (engine 2). The calculated spreads of the 90 percent thrust time and the thrust for the LPPS as a whole are far smaller (about by 40 percent) and lie in the range – 0.0733 s to +0.0457 s for the time and – 4.8 percent to +4.8 percent for the thrust (about the nominal thrust). Using Pearson’s chi-squared test, an estimate is obtained for the goodness of fit of the anticipated theoretical distributions of the 90 percent thrust time spread and the steady thrust spread to the obtained statistical ones both for the two engines and for the LPPS as a whole.
APA, Harvard, Vancouver, ISO, and other styles
3

Setiyawati, Defi. "Analisis Perbandingan Performa Saat Takeoff Pada Engine CFM56-7b Dengan Konfigurasi Thrust Rating 26300 Lbs Dan 27300 Lbs." Jurnal Teknologi Kedirgantaraan 7, no. 1 (2022): 7–14. http://dx.doi.org/10.35894/jtk.v7i1.51.

Full text
Abstract:
The CFM 56-7B engine is manufactured by CFM International which is used on the B737-600/700/800/900 aircraft. This engine has several variations of the thrust rating with varying performance. Engine performance parameters include Thrust, Specific Fuel Consumption (SFC), Core Speed (N2), and Exhaust Gas Temperature (EGT). Performance testing can be done using the Engine Test Cell. However, the engine test cell is a calibrated tool, which allows deviation of the test results. Then the performance calculation is done using the formula in the Engine Shop Manual - Test 003 - Engine Acceptance Test to find out the engine performance during the takeoff phase at the highest thrust rating of 26300 lbs and 27300 lbs and compare the performance of the two engines. Comparison of the calculation results states that an engine with a thrust rating of 26300 lbs is superior to Exhaust Gas Temperature, while an engine with a thrust rating of 27300 lbs has advantages at Thrust, Specific Fuel Consumption and Core Speed (N2).
APA, Harvard, Vancouver, ISO, and other styles
4

Langston, Lee S. "For Jet Engine Wing Mounting." Mechanical Engineering 140, no. 09 (2018): S52—S53. http://dx.doi.org/10.1115/1.2018-sep4.

Full text
Abstract:
The mounting of a jet engine under the wing of an airliner can be a daunting task for turbofan engineers. Thrust forces generated by gas path momentum flow changes in a jet engine are transmitted by pressure (and friction) forces on stators and struts attached to the engine case. Case engine mounts then transmit the thrust forces (as high as 100,000 pounds thrust on the largest engines) to the wing pylons to pull the plane forward. The mounts must also support the engine weight (as high as 20,000 pounds) and carry nacelle flight loads. Engine bypass ratios are increasing (12:1 on the new geared fan engines), with fan sizes ever growing (178 inch diameter fan on the new GE9X). Mounting these new engines under a wing can present new challenges. During the early days of its introduction in the late 1960’s, Boeing’s iconic 747 jumbo jet had engine mount problems. These are examined, together with their solution.
APA, Harvard, Vancouver, ISO, and other styles
5

S. Abdulhussain, Uzaldin, Taj Elssir Hassan, and Maisara Mohy Eldin Gasim. "Theoretical Performance Comparison between Inline, Offset and Twin Crankshaft Internal Combustion Engine Models." FES Journal of Engineering Sciences 2, no. 1 (2006): 26. http://dx.doi.org/10.52981/fjes.v2i1.91.

Full text
Abstract:
Twin crankshaft is a new engine arrangement introduced to overcome cylinder’s liner wear problems encountered in the conventional inline crankshaft engine due to the effect of the side thrust force. The offset crankshaft arrangement was also introduced to solve the same problem. In this work a computer programs was built to obtain the theoretical performance comparison between the three engines arrangements (inline, twin and offset crankshaft engines), and compared the theatrical performance with the experimental results, which done to the engine’s models. The study results show that the twin crankshaft engine model exhibited no thrust force, and that the thrust force in the offset crankshaft model is smaller than that in the inline crankshaft engine model. These agree with experimental results obtained from the same engine model.
APA, Harvard, Vancouver, ISO, and other styles
6

Chen, Ruiyang. "Advanced development and future of jet engines." Theoretical and Natural Science 12, no. 1 (2023): 162–66. http://dx.doi.org/10.54254/2753-8818/12/20230457.

Full text
Abstract:
An aerodynamic reaction engine, a jet engine, is an internal combustion engine that produces thrust through jet thrust. A jet engine is an important power unit used in aviation and spaceflight, which generates thrust by pushing air in reverse. In recent decades, various developments and improvements have significantly enhanced the efficiency and performance of jet engines. These engines are divided into turbojets, turbojets, turboprops, turboshafts, and ramjets. This article will begin with an introduction to the different types of jet engines and then detail the design, benefits, and issues of the CFM International CFM56/LEAP engine. Finally, there is some description of the future of jet engines, including materials, greater efficiency, and applications in space exploration. The development of the jet engine dates back to the 1930s. British inventor Frank Whittle and German inventor Hans von Ohain developed the first jet engines independently. Jet engines were widely used during World War II and have been continuously improved and developed. The modern jet engine has become the main power unit of commercial and military aviation, and its structure and performance have also been greatly improved.
APA, Harvard, Vancouver, ISO, and other styles
7

Sneha, Rachel Francis, and J. S. Mija. "Design of Fault Tolerant Control Laws for Jet Engines." Applied Mechanics and Materials 367 (August 2013): 96–100. http://dx.doi.org/10.4028/www.scientific.net/amm.367.96.

Full text
Abstract:
Full Authority Digital Electronic Control (FADEC) system is common in all modern jet engines. In jet engine, the simplest control system is to produce desired engine thrust by changing the fuel flow. Since in flight engine thrust measurement is practically not possible, engine low pressure shaft rotational speed (N1/NL), engine pressure ratio (EPR), or exhaust jet temperature (EJT) has been effectively used as an indicator of the engine thrust. In this paper, the model used is twin spool turbofan engine. If any fault occurs in N1 sensor, the entire engine operation will be affected. Since there exists a unique aerodynamic relationship among the spool speeds, if any fault occurs in N1 sensor, engine thrust can be controlled with a certain amount of degradation using high pressure spool speed (N2/NH).Both soft and hard failures are detected using kalman filter, range, rate and comparison techniques. The effectiveness of the proposed approach is demonstrated by means of simulations.
APA, Harvard, Vancouver, ISO, and other styles
8

Jačionis, Tomas, Vytautas Urbanavičius, Andrius Katkevičius, et al. "UAV Detection Using Thrust Engine Electromagnetic Spectra." Drones 6, no. 10 (2022): 306. http://dx.doi.org/10.3390/drones6100306.

Full text
Abstract:
Artificial intelligence used in unmanned aerial vehicle (UAV) flight control systems tends to leave UAV control systems without any radio communication emissions, whose signatures in an electromagnetic spectrum (ES) are widely used to detect UAVs. There will be problems in the near future in detecting any dangerous threats associated with UAV swarms, kamikaze unmanned aerial vehicles (UAVs), or any other UAVs with electrically powered thrust engines because of the UAV’s flight capabilities in full radio silence mode. This article presents a different approach to the detection of electrically powered multi-rotor UAVs. The main idea is to register the electromagnetic spectrum of the electric thrust engines of the UAV, which varies because of the changing flight conditions. An experiment on a UAV’s electric thrust engine-produced electromagnetic spectrum is carried out, presenting the results of the flight-dependent characteristics, which were observed in the electromagnetic spectrum. The electromagnetic signature of the UAV’s electric thrust engines is analyzed, discussed, and compared with the most similar behaving electric engine, which was used on the ground as a domestic electric appliance. A precision tunable magnetic antenna is designed, manufactured, and tested in this article. The physical experiments have shown that the ES of the electric thrust engines of multi-rotor UAVs can be detected and recorded for recognition. The unique signatures of the ES of the multi rotor UAV electric engine are recorded and presented as a result of the carried-out experiments. A precision tunable magnetic antenna is evaluated for the reception of the UAV’s signature. Moreover, results were obtained during the performed experiments and discussions about the development of the future techniques for the identification of the ES fingerprints of the UAV’s electric thrust engine are carried out.
APA, Harvard, Vancouver, ISO, and other styles
9

Ravi, Teja Cheepuri, Y. S. Prudhviraj Oruganti, and Rama Priya Raavi Sai. "Study of Small Gas Turbine Engines of Thrust 1-5KN." International Journal of Innovative Science and Research Technology 8, no. 1 (2023): 2114–19. https://doi.org/10.5281/zenodo.7634395.

Full text
Abstract:
Small gas turbine engines present a significantlylower performance when compared to large ones. The major reasons for that are the lower component efficiencies and size effects. The present work accomplishes an investigation of data available in the open literature for small turbojet and turbofan engines, covering a range from 1 to 5 kN of thrust, to find the most important parameters for these engine configurations. This study aims to evaluate the parameters used in engines in this thrust range, for the possible development of an engine for a specific application. This overview relies on a correlation between some of the major parameters of the engine, namely thrust, specific fuel consumption, pressure ratio, turbine inlet temperature, weight, length, diameter, and mass flow.
APA, Harvard, Vancouver, ISO, and other styles
10

ANDREI, Irina-Carmen, Mihai Victor PRICOP, Mihai Leonida NICULESCU, et al. "COMPARATIVE ANALYSIS FOR PERFORMANCE PREDICTION IN CASE OF IAR 99 AIRCRAFT PROPULSION SYSTEMS." SCIENTIFIC RESEARCH AND EDUCATION IN THE AIR FORCE 25 (July 31, 2024): 152–67. http://dx.doi.org/10.19062/2247-3173.2024.25.18.

Full text
Abstract:
This paper presents a comparative analysis regarding Performance Prediction at Design and Off-Design Regimes, applied for two distinct constructions of Jet Engines as Propulsion Systems solutions for the IAR 99 Aircraft. Case Study #1 is represented by Turbojet Engine Rolls Royce VIPER MK 632-41 and Case Study #2 is represented by a Mixed Flows Turbofan Engine. The thorough study is based on appropriate Applicable Theory, which is detailed in the bibliographic references and can be accessed. Applicable Theory includes a part dedicated to Engine Parameter Identification, which is necessary to calculate Brayton Diagram and the performances of the jet engines, expressed as Thrust and Specific Fuel Consumption (TSFC). Applicable Theory includes detailed Mathematical Modeling, Developments and Numerical Simulations for Turbojet Engine and Mixed Flows Turbofan Engine. Performance Prediction results from aero-thermo-gas dynamics analysis of the studied engines. The accuracy of the numerical results depends on the assumptions used for mathematical modeling, which in this case have been considered: real gas, adiabatic flow, the variation with static temperature of the specific heat, losses due to pressure drop and friction, the conditions for full expansion in the exhaust nozzle are met such that the engine can generate maximum of Thrust. Results from Numerical Simulations express Performance Prediction for the Turbojet Engine and the Mixed Flows Turbofan Engine, for the Design and Off-Design Regimes. Comparative diagrams illustrating the variation of Thrust and Specific Fuel Consumption (TSFC) with Mach number and altitude, for the studied jet engines, conclude the analysis. As final remark, the Mixed Flows Turbofan Engine represents a better option than the Turbojet Engine, from the standpoint of greater Thrust and lower TSFC
APA, Harvard, Vancouver, ISO, and other styles
More sources

Dissertations / Theses on the topic "Engine thrust"

1

Hackaday, Gary L. "Thrust augmentation for a small turbojet engine." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA362981.

Full text
Abstract:
Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1999.<br>Thesis advisor(s): Garth V. Hobson. "March 1999". Includes bibliographical references (p. 75). Also available online.
APA, Harvard, Vancouver, ISO, and other styles
2

MEDICI, GIOVANNI. "Thrust vectoring on an UCAV airplane (thrust vectoring engine model): advanced control system." Doctoral thesis, Politecnico di Torino, 2013. http://hdl.handle.net/11583/2508286.

Full text
Abstract:
Since the early development of the Sky-X UAV demonstra- tor, Alenia Aermacchi has been studying a thrust vectored version of that airplane. For this reason, in 2010, Alenia Aermacchi offered a three years PhD funding to the Depart- ment of Aerospace Engineering of Politecnico di Torino. In particular a vane based thrust vectoring system had to be studied, the development of open and flexible software tools was a priority in the project. The tools had to be cus- tomizable and a general estimation model of the system had to be developed. The research analysis took place during three years and involved several areas of the company and of aerospace en- gineering. In particular three main areas were covered in the study: propulsion, aerodynamics , flight dynamics.
APA, Harvard, Vancouver, ISO, and other styles
3

Yarlagadda, Santosh. "Performance Analysis of J85 Turbojet Engine Matching Thrust with Reduced Inlet Pressure to the Compressor." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271367584.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Bartosh, Brady J. "Thrust measurement of a split-path, valveless pulse detonation engine." Thesis, Monterey, Calif. : Naval Postgraduate School, 2007. http://bosun.nps.edu/uhtbin/hyperion-image.exe/07Dec%5FBartosh.pdf.

Full text
Abstract:
Thesis (M.S. in Astronautical Engineering)--Naval Postgraduate School, December 2007.<br>Thesis Advisor(s): Brophy, Christopher M. "December 2007." Description based on title screen as viewed on January 17, 2008. Includes bibliographical references (p. 95-96). Also available in print.
APA, Harvard, Vancouver, ISO, and other styles
5

Boggs, George Lemuel IV. "Turbine Engine Thrust Measurements Using a Non-Intrusive Acoustic Technique." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/90299.

Full text
Abstract:
Experiments were conducted to measure the thrust generated from a commercial jet engine. This thrust estimation was done using a pneumatic horn as the sound source with two arrays of microphones directly across the exhaust stream. The two arrays were separated by an axial distance downstream. Exhaust centerline measurements were taken at varying engine conditions, specifically; 30%, 50%, 60%, 70%, 80% and 100% engine power. An acoustic thrust estimation showed good agreement with measured thrust during the test campaign. In addition, a full traverse of the acoustic rig through the exhaust stream was completed for the purpose of tomography reconstruction. This reconstruction technique was able to pick up key features of the flow field.<br>Master of Science
APA, Harvard, Vancouver, ISO, and other styles
6

Schaefermeyer, M. Ryan. "Aerodynamic Thrust Vectoring For Attitude Control Of A Vertically Thrusting Jet Engine." DigitalCommons@USU, 2011. https://digitalcommons.usu.edu/etd/1237.

Full text
Abstract:
NASA’s long range vision for space exploration includes human and robotic missions to extraterrestrial bodies including the moon, asteroids and the martian surface. All feasible extraterrestrial landing sites in the solar system are smaller and have gravitational fields of lesser strength than Earth’s gravity field. Thus, a need exists for evaluating autonomous and human-piloted landing techniques in these reduced-gravity situations. A small-scale, free-flying, reduced-gravity simulation vehicle was designed by a group of senior mechanical engineering students with the help of faculty and graduate student advisors at Utah State University during the 2009-2010 academic year. The design reproduces many of the capabilities of NASA’s 1960s era lunar landing research vehicle using small, inexpensive modern digital avionics instead of the large, expensive analog technology available at that time. The final vehicle design consists of an outer maneuvering platform and an inner gravity offset platform. The two platforms are connected through a set of concentric gimbals which allow them to move in tandem through lateral, vertical, and yawing motions, while remaining independent of each other in rolling and pitching motions. A small radio-controlled jet engine was used on the inner platform to offset a fraction of Earth’s gravity (5/6th for lunar simulations), allowing the outer platform to act as though it is flying in a reduced-gravity environment. Imperative to the stability of the vehicle and fidelity of the simulation, the jet engine must remain in a vertical orientation to not contribute to lateral motions. To this end, a thrust vectoring mechanism was designed and built that, together with a suite of sensors and a closed loop control algorithm, enables precise orientation control of the jet engine. Detailed designs for the thrust vectoring mechanisms and control avionics are presented. The thrust vectoring mechanism uses thin airfoils, mounted directly behind the nozzle, to deflect the engine’s exhaust plume. Both pitch and yaw control can be generated. The thrust vectoring airfoil sections were sized using the two-dimensional airfoil section compressible-flow CFD code, XFOIL, developed at the Massachusetts Institute of Technology. Because of the high exhaust temperatures of the nozzle plume, viscous calculations derived from XFOIL were considered to be inaccurate. XFOIL was run in inviscid flow mode and viscosity adjustments were calculated using a Utah State University-developed compressible skin friction code. A series of ground tests were conducted to demonstrate the thrust vectoring system’s ability to control the orientation of the jet engine. Detailed test results are presented.
APA, Harvard, Vancouver, ISO, and other styles
7

Dunn, Francis X. "Thrust modulated multivariable control of the GE21 engine using the LQG/LTR method." Thesis, Massachusetts Institute of Technology, 1986. http://hdl.handle.net/1721.1/15000.

Full text
Abstract:
Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science, 1986.<br>MICROFICHE COPY AVAILABLE IN ARCHIVES AND ENGINEERING<br>Bibliography: leaves 173-175.<br>by Francis X. Dunn.<br>M.S.
APA, Harvard, Vancouver, ISO, and other styles
8

Alves, Wilton Fernandes. "Development of experimental firing test stand to study the rocket engine thrust characteristics." Instituto Tecnológico de Aeronáutica, 2008. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=2324.

Full text
Abstract:
The main aim of this work is to present the specification of an experimental firing test stand of liquid rocket engine (LRE), comprising the main design, the instrumentation of measurement system, the data acquisition system, the operating manual, as well as the methodology to perform laboratory work for determination of a LRE thrust characteristics in atmospheric conditions. Initially it is presented a theoretical basement of LRE in general and concerning the laboratory work. After that it is proposed a methodology for execution of laboratory work using resources of information technology, which will allow the automatic and remote functioning of the test stand, and it will give to the users the inputs necessaries to realization of tests and attainment of reliable results. The specification of the test stand is result of calculations implemented in MathCAD program in way of algorithms presented in appendix of this work. The control of mass flow rates of propellant by automatic pressure regulators and valves, as well as the data acquisition of test stand is carried out by Labview program in a NI PXI platform. The instrumentation of measurement system will make possible online measurements of temperatures, pressures, mass flow rates and thrust force related to the tests. It is presented also a preliminary analysis of type B uncertainties of test stand system, and a comparative analysis between designed LRE with similar rocket engine of a test stand in operation.
APA, Harvard, Vancouver, ISO, and other styles
9

MacLeod, James D. (James Donald) Carleton University Dissertation Engineering Aeronautical. "A derivation of gross thrust for a sea-level jet engine test cell." Ottawa, 1988.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
10

Gullia, Alessandro. "Thrust and Flow Prediction in Gas Turbine Engine Indoor Sea-Level Test Cell Facilities." Thesis, Cranfield University, 2006. http://dspace.lib.cranfield.ac.uk/handle/1826/7496.

Full text
Abstract:
The principal aim of this research was to provide a detailed understanding of the performance of gas turbine engines inside indoor sea-level test beds. In particular the evaluation of both thrust correction factors and the estimation of the mass flow entering the test cell were at the core of the research. The project has been fully sponsored by Rolls-Royce pIc. Initially, their principal objective was to assess the relevance and accuracy of CFD when applied to thrust measurement inside indoor test beds with an intended outcome of minimising the use of expensive experimental measurements. The different system interfaces and accounting systems for in-flight conditions, available in the open literature have been developed and adapted for indoor environments. This has led to the definition of three different thrust correction equations using alternative definitions of thrust correction factor. Aero-dynamic principles have been applied for the derivation of one-dimensional relationships for the calculation of each thrust correction factor using generic engine-cell performance and dimensions. A one-dimensional analytical model has been developed to represent the enginedetuner ejector pump. This is able to characterise the engine-cell system performance and is used as the main tool for providing a matching procedure capable of predicting the cell entrainment ratio. By processing experimental data relevant to different engine-cell configurations through the ejector pump analytical model, a method for achieving the entrainment ratio control inside the cell has been identified. The CFD work has been concentrated into three main activities: • A quantitative extrapolation of the thrust correction factors including, the pre-entry force, the external and the total bellmouth force, the throat stream force, the intake momentum drag and the base drag. • The representation of the engine-detuner ejector performance for a variety of engine-cell configurations. • The modelling of the generic test cell components including the inlet stack, the cascade elbow, the exhaust stack & the blast basket. The outcomes of this research have been very successful in enhancing the validity of the thrust correction equations developed .. In particular, the use of a one-dimensional approach in their estimation has been shown to be fully justified. The work has also emphasised the value of CFD in supporting the derivation of the matching procedure for predicting and controlling cell entrainment ratio. Indeed, one of the strongest outcomes of this work has been the conclusion that both the engine-cell characteristic lines computed with the one-dimensional model and those computed with CFD for different cell configurations are almost identical. In addition, the use of CFD as a tool for the quantitative evaluation of the thrust correction factors has been established. Finally, the CFD results have facilitated an enhanced understanding of the complex flow structure inside indoor test cells
APA, Harvard, Vancouver, ISO, and other styles
More sources

Books on the topic "Engine thrust"

1

United States. National Aeronautics and Space Administration., ed. PPT thrust stand. National Aeronautics and Space Administration, 1995.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
2

United States. National Aeronautics and Space Administration., ed. PPT thrust stand. National Aeronautics and Space Administration, 1995.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
3

Gatlin, Gregory M. Thrust-reverser flow investigation on a twin-engine transport. Langley Research Center, 1988.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
4

Frank, Quinto P., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Thrust-reverser flow investigation on a twin-engine transport. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
5

Frank, Quinto P., and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Thrust-reverser flow investigation on a twin-engine transport. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
6

Sibtosh, Pal, and NASA Glenn Research Center, eds. Thrust augmentation measurements using a pulse detonation engine ejector. National Aeronautics and Space Administration, Glenn Research Center, 2003.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
7

Ray, Ronald J. Evaluation of various thrust calibration techniques on an F404 engine. Ames Research Center, Dryden Flight Research Facility, 1990.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
8

Nardi Rezende, Rene, ed. Liquid Rocket Engine Thrust Chamber Parametric Modeling. SAE International, 2018. http://dx.doi.org/10.4271/0768093333.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Nardi Rezende, Rene. Liquid Rocket Engine Thrust Chamber: Parametrical Modeling. SAE International, 2018. http://dx.doi.org/10.4271/r-465.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Hackaday, Gary L. Thrust augmentation for a small turbojet engine. Naval Postgraduate School, 1999.

Find full text
APA, Harvard, Vancouver, ISO, and other styles
More sources

Book chapters on the topic "Engine thrust"

1

Decher, Reiner. "Propulsion for Flight: Power or Thrust?" In The Vortex and The Jet. Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_9.

Full text
Abstract:
AbstractAn engine is required to provide the power necessary for overcoming the drag of flight. There are not many engine types available to perform that important function: they all have advantages and limitations. They share common features and are different in fundamental ways. The histories of their development paced the history of man’s ability to fly and the modern gas turbine engine is the climax of that progression toward today’s state of aviation. In this chapter we focus on the salient features of engines as they relate to flight.
APA, Harvard, Vancouver, ISO, and other styles
2

Huang, Minchao, Yuqiang Cheng, Jia Dai, and Jian Li. "Analysis of the Response Characteristics of the Tank Pressurization System and a Single Thruster." In Performance Analysis of a Liquid/Gel Rocket Engine During Operation. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-6485-3_3.

Full text
Abstract:
AbstractBased on the mathematical models of the operation of the space propulsion system components established in Chap. 2 and the Modelica programs for the startup, steady-state and shutdown processes of the components, the thruster simulation system for each type of thrust can be conveniently assembled. By inputting known parameters of the thruster, such as the gas cylinder and pressure-reducing valve structural parameters, propellant density, pipeline diameter and length, and thrust chamber structural parameters, into the simulation system, the response of a single thruster can be analyzed in terms of pipeline pressure, flow rate, combustion chamber pressure, temperature, component ratio, thrust and other parameters, on which basis in this book it discussed the effects of the gas cylinder pressure, pressure-reducing valve characteristics, filling and shutdown characteristics, thruster response time, the effects of the combustion chamber volume and the inner diameter of the nozzle throat.
APA, Harvard, Vancouver, ISO, and other styles
3

Rakesh, R. B., and Sijo Varghese. "Fluidic Thrust Vectoring of Engine Nozzle." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-10-5849-3_5.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

Petr, Fomichev, Zarutskiy Anatoliy, and Lyovin Anatoliy. "Improving Method for Measuring Engine Thrust with Tensometry Data." In Systems, Decision and Control in Energy I. Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-48583-2_4.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Yue, Chun-guo, Xin-Long Chang, Shu-jun Yang, and You-hong Zhang. "Numerical Simulation of a Pintle Variable Thrust Rocket Engine." In Computer Science for Environmental Engineering and EcoInformatics. Springer Berlin Heidelberg, 2011. http://dx.doi.org/10.1007/978-3-642-22691-5_84.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Huang, Minchao, Yuqiang Cheng, Jia Dai, and Jian Li. "Mathematical Model of the Operation of the Space Propulsion System." In Performance Analysis of a Liquid/Gel Rocket Engine During Operation. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-6485-3_2.

Full text
Abstract:
AbstractThe space propulsion system is composed of 17 thrusters, including one large thruster (numbered 0), eight medium thrusters (numbered 1–4 and 9–12), and 8 small thrusters (numbered 5–8 and 13–16). Seventeen thrusters share one propellant supply system. The system includes components such as a gas cylinder, electric explosion valve, pressure-reducing valve, storage tank, liquid pipeline, filter, orifice plate, solenoid valve, filling pipeline, and thrust chamber, as shown in Fig. 2.1.
APA, Harvard, Vancouver, ISO, and other styles
7

Srinivas, R. Siva, S. E. Muthu, and Girish K. Degaonkar. "Rotordynamic Design Studies of Medium Thrust Class Twin Spool Engine." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-5701-9_43.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Panigrahi, Sridhar, P. Rijish Kumar, B. Prejil Kumar, et al. "The Development of Turbopumps for Low-Thrust Cryogenic Rocket Engine." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9057-0_16.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Novichkov, V. M., та A. Yu Burova. "Digital Algorithms for Compensation of Airliner Turbojet Engine Thrust Asymmetry". У Proceeding of the International Science and Technology Conference "FarEastСon 2021". Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8829-4_84.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Wang, Xiuqi, Jie Shen, and Zhongzhi Hu. "An EEC Dual Channel Switching Algorithm Based on Engine Thrust Sensitivity." In Proceedings of the 11th International Conference on Modelling, Identification and Control (ICMIC2019). Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-15-0474-7_98.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Conference papers on the topic "Engine thrust"

1

Oberschwendtner, Sebastian, and Mirko Hornung. "Impact of Engine Failure on the Wiring Harness Design of Electric VTOL Aircraft." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1052.

Full text
Abstract:
This paper deals with the influence of engine failure during hover on the wiring harness mass of electrical Vertical Take-Off and Landing (eVTOL) aircraft. It starts by presenting possible strategies which can be used to distribute the additional thrust needed during an engine failure among the remaining engines. The most efficient strategy is selected and the impact of different single engine failures on the overall thrust share, while using this strategy, is discussed. The paper proceeds by applying the selected thrust compensation strategy to the mission simulation of three common reference models, which are representative of current eVTOL aircraft configurations. This simulation is used to determine the worst flight phase for the One Engine Inoperative (OEI) condition to occur. The main purpose of the simulation is to optimize the wire sizes of the wiring harness of each configuration while satisfying different design objectives. The results of these optimizations are used to discuss the criticality of each engine failure and its influence on the wiring harness design, especially its mass. It concludes with design recommendations for the wiring harness of eVTOL aircraft.
APA, Harvard, Vancouver, ISO, and other styles
2

Hua, Zuohao, Zhuang Fu, Lu Niu, Bang Liu, and Jiazheng Zhang. "Thrust Allocation Method for Solid Attitude and Divert Control Engine." In 2024 7th International Conference on Robotics, Control and Automation Engineering (RCAE). IEEE, 2024. https://doi.org/10.1109/rcae62637.2024.10834209.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Lonchard, Jean-Marie, Isabelle Jeaugey, Justin Montheiller, et al. "High Thrust Engine Demonstrations." In 46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-6970.

Full text
APA, Harvard, Vancouver, ISO, and other styles
4

ROBERTS, J., J. LEWIS, D. GLICKEN, R. MORIN, J. MANCINI, and D. HAAS. "Engine thrust measurement uncertainty." In 21st Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1404.

Full text
APA, Harvard, Vancouver, ISO, and other styles
5

Viot, Xavier, Francois Lassoudiere, Alain Souchier, and Gilles Dantu. "High Thrust Engine Demonstrations." In 45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-5132.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Balaji, Ashwin, Sangam Laxman Kute, T. Sreenivasulu, and Rod Giles. "Piston Durability Analysis including Side-Thrust Loads." In Small Engine Technology Conference & Exposition. Society of Automotive Engineers of Japan, 2020. http://dx.doi.org/10.4271/2019-32-0585.

Full text
Abstract:
&lt;div class="section abstract"&gt;&lt;div class="htmlview paragraph"&gt;The Piston is one of the most arduously loaded components in an IC engine. It is subjected to multiple loads simultaneously such as cylinder pressure, temperature loads, inertial loads &amp;amp; side-thrust loads. The durability of the Piston can be modelled accurately, only by accounting all the loads acting on the Piston. The challenge is, this approach requires information from multiple disciplines such as temperatures from CFD, Piston secondary forces from Multi-Body Dynamics (MBD) analysis and P-theta (Pressure vs Crank angle) curve from the experimental measurements. In this study, the life of the Piston and the damage location is predicted by using temperature dependent material properties and the above-mentioned loads.&lt;/div&gt;&lt;/div&gt;
APA, Harvard, Vancouver, ISO, and other styles
7

SCHNEIDER, BARBARA, ROY MICHEL, and JOHN GIBB. "Low thrust cryogenic engine technology." In 23rd Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-1932.

Full text
APA, Harvard, Vancouver, ISO, and other styles
8

Hiers, Robert, H. MacKinnon, R. Whitney, and N. Nugent. "Validation of Stream Thrust Probes for Rocket Engine Thrust Measurement." In 39th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit. American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5183.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Hiers, Robert, Heather MacKinnon, and Ryan Whitney. "Validation of Stream Thrust Probes for Turbine Engine Thrust Measurement." In 42nd AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-1297.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Zvegintsev, V. I. "DETERMINATION OF AIR-JET ENGINE THRUst." In ХХI International Conference on the Methods of Aerophysical Research (ICMAR 2022). Федеральное государственное бюджетное учреждение «Сибирское отделение Российской академии наук», 2022. http://dx.doi.org/10.53954/9785604788967_224.

Full text
APA, Harvard, Vancouver, ISO, and other styles

Reports on the topic "Engine thrust"

1

Shkurupiy, Valeria, and Nikita Budnyi. A priori estimation of instrumental error of energy characteristics of an electric rocket engine. Baltic State Technical University “VOENMEH” named after D.F.Ustinov, 2023. http://dx.doi.org/10.12731/edn:dkwobv.

Full text
Abstract:
In this work, the power of the calculated electric rocket engine (ERE) requires thrust, specific impulse, and efficiency. ERE thrust measurement is interesting enough to achieve smallness of rapid growth. Specific impulse and efficiency are measured using laboratory methods. For this reason, one should naturally approach the choice of design parameters and the composition of the measuring system. One of the synthesis products can be the minimization of measurement errors. The paper approaches an approach to a priori instrumental estimation of the error determination, which may be useful in the synthesis of a system measurement of the ERE characteristics.
APA, Harvard, Vancouver, ISO, and other styles
2

Shkurupiy, V. A., and N. L. Budnyi. Simulation of the dynamics of the stand for measuring the thrust of an electric rocket engine. Baltic State Technical University “VOENMEH” named after D.F.Ustinov, 2022. http://dx.doi.org/10.12731/edn:jmtccs.

Full text
APA, Harvard, Vancouver, ISO, and other styles
3

Taylor. L51755 Development and Testing of an Advanced Technology Vibration Transmission. Pipeline Research Council International, Inc. (PRCI), 1996. http://dx.doi.org/10.55274/r0010124.

Full text
Abstract:
Fiber optic sensors have been under development in industrial and government laboratories around the world for over a decade. The commercial market for fiber sensors for measuring parameters such as temperature, displacement, and liquid level is now estimated to exceed $100 M/year. Aside from the commercial interest, the U. S. Department of Defense has vigorously pursued the development of fiber gyroscopes and hydrophones. In spite of the high level of research and development activity, however, until recently fiber sensors had not been successfully applied in high-temperature engine environments. The goal of this effort is to develop and test high-temperature fiber optic sensors and show that they are suitable for monitoring vibration and other instabilities in gas turbine engines. The underlying technology developed during the course of PRCI projects PR- 219-9120 and PR-219-9225 during 1991-94 serves as the foundation for PR-240-9416. Transducers with the fiber optic Fabry-Perot interferometer (FFPI) configuration have been adapted for use in the turbomachinery environment.To ensure the survival of the FFPI sensors at high temperatures, two techniques for coating the fibers with metal have been developed: electroplating and vacuum deposition. Coated sensors have subsequently been embedded in aluminum and brass alloys. Experiments on a small Sargent Welch turbine engine have shown the high sensitivity of embedded FFPI strain sensors to vibration in rolling bearings. Data have been collected in both the time and frequency domain. A new accelerometer design in which a metal-coated fiber containing the FFPI element is soldered directly to a diaphragm in a stainless steel housing shows response similar to a piezoelectric accelerometer in shaker table tests. The high sensitivity of the FFPI accelerometer has been demonstrated in field tests in a Solar Centaur turbine engine, and the design has survived temperatures greater than 500�C in a test oven. A magnetometer with a physical configuration similar to that of the accelerometer has been used to measure the distance from the sensor head to a rotating shaft made of ferromagnetic material. This device, which functions as a proximity probe, has been used to monitor shaft rotation rate (keyphasor application) and as a shaft thrust position sensor. These results indicate the potential for performing critical measurements in turbine engines with FFPI sensors. They can measure acceleration, distance (proximity), strain (as it relates to bearing defect diagnosis), and gas pressure, and can operate at higher temperatures than conventional transducers.
APA, Harvard, Vancouver, ISO, and other styles
4

Tossey, Brett, and Ramgopal Thodla. PR-180-094506-R01 Challenges for Safe and Reliable On-Shore Pipeline Transport of Supercritical CO2. Pipeline Research Council International, Inc. (PRCI), 2010. http://dx.doi.org/10.55274/r0010712.

Full text
Abstract:
There is interest within the pipeline industry in transporting supercritical CO2 in pipelines. A significant issue is the lack of an independent industry standard for supercritical CO2 pipelines. Existing industry standard for liquid and gas transmission are used for mechanical design requirements, but selected properties of supercritical CO2 make it a unique product. Impurities in the gas steam, materials selection, and leak detection in supercritical CO2 require special consideration. The objective of this project is to engage the supercritical CO2 industry in a workshop and use their knowledge to complete a gap analysis. The project is divided into two main thrusts; survey of knowledge and gaps by conducting an industry workshop (Thrust 1) and to outline what efforts and work is needed to close these gaps in a limited way (Thrust 2). This report summarizes the results of both thrusts. This report summarizes the results of the gaps analysis. The primary finding is that the supercritical CO2 pipeline operators in the United States are confident that the designs of their transmission systems are safe and adequate. Another important finding was the need for improvement in the equation of state (EOS). Currently, most models fail to accurately predict the affects of coal combustion impurities on the phase behavior of supercritical CO2. Improvements in metering technology, materials selection criteria, and leak detection were also identified as gaps. The final gap that was identified was the need for a standardized �blow-down� procedure during system startup and shutdown. An industry standard specific to supercritical CO2 transportation should include sound engineering guidance covering each of these gaps. See the associated linked documents for appendices to this report.
APA, Harvard, Vancouver, ISO, and other styles
5

Detulio, Kenneth, and David Skipper. Digital Integrated Collection Environment (DICE)/Cognitive Reasoning Engine (CORE) Intelligent Threat Architecture Study. Defense Technical Information Center, 2003. http://dx.doi.org/10.21236/ada473159.

Full text
APA, Harvard, Vancouver, ISO, and other styles
6

Katers, Nicholas W. Shaping the Engineer Force for the Asymmetric Threat. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada403790.

Full text
APA, Harvard, Vancouver, ISO, and other styles
7

Beurlot, Kyle, and Timothy Jacobs. PR457-23203-R01 Investigation of Supersonic Prechamber Jets. Pipeline Research Council International, Inc. (PRCI), 2025. https://doi.org/10.55274/r0000116.

Full text
Abstract:
Lean-burning, large-bore two-stroke natural gas engines have long been essential elements of the North American natural gas pipeline system and will continue to play a crucial role in natural gas transportation for the foreseeable future. However, with increasing pressure to reduce emissions, improving the performance of this aging engine fleet has become more critical than ever. Pre-Combustion Chambers (PCCs) are frequently implemented on these engines to improve ignition stability, extend the lean limit of operation, and significantly reduce harmful emissions such as nitrogen oxides (NOx) and hydrocarbons (HC). While PCCs help reduce the carbon footprint of pipeline compressor stations, ongoing research into the pathway toward reduced emissions re-mains essential, as many avenues are still to be explored. This study aims to further research into novel subsonic converging and supersonic converging-diverging PCC nozzle designs that could potentially reduce methane emissions. A computational fluid dynamics (CFD) model of Texas A and M's Cooper Ajax E-565 large-bore natural gas lean burn two-stroke was utilized in a prechambered configuration for the study. Several converging nozzles of decreasing size and converging-diverging nozzles of various throat diameter, area expansion ratio, and shape were explored to produce PCC jets of different shape, spread, and level of penetration into the main combustion chamber (MCC). The resultant jet effects were then heavily analyzed for impacts to general cycle performance, such as main chamber pressure, temperature, NOx emissions, and methane emissions.
APA, Harvard, Vancouver, ISO, and other styles
8

Perez-Vergara, Eliezer, and Jr. The Diesel-Electric Submarine Threat: Ignore, Engage or Avoid? Defense Technical Information Center, 1999. http://dx.doi.org/10.21236/ada370653.

Full text
APA, Harvard, Vancouver, ISO, and other styles
9

Pence, James B. Military Engineer Contribution to Operational Art: The Hybrid Threat Environment. Defense Technical Information Center, 2015. http://dx.doi.org/10.21236/ad1001763.

Full text
APA, Harvard, Vancouver, ISO, and other styles
10

Harding, D. C., and J. D. Pierce. A methodology for the evaluation of the turbine jet engine fragment threat to generic air transportable containers. Office of Scientific and Technical Information (OSTI), 1993. http://dx.doi.org/10.2172/10177710.

Full text
APA, Harvard, Vancouver, ISO, and other styles
You might also be interested in the extended bibliographies on the topic 'Engine thrust' for particular source types:
Journal articles Dissertations / Theses Books
We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!

To the bibliography