Relevant bibliographies by topics / Jet engine inlet

Academic literature on the topic 'Jet engine inlet'

Author: Grafiati
Published: 10 December 2022
Last updated: 28 January 2023

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Journal articles on the topic "Jet engine inlet"

1

Langston, Lee S. "Jet Engine Fuel Burn Reduction Through Boundary Layer Ingestion." Mechanical Engineering 136, no. 04 (April 1, 2014): 54–58. http://dx.doi.org/10.1115/1.2014-apr-5.

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This article explains various technical aspects of the boundary layer ingestion (BLI) concept. Using BLI, airliner designs featuring close-coupled, rear-mounted turbofans are being considered, with a fuselage sculpted to sweep a large part of the fuselage boundary layer into engine inlets for reduced fuel consumption. With an engine array fuselage-centered, rather than splayed out on wings, reduced rudder control is needed in the event of a single engine outage. This reduces the size of a BLI tail assembly, saving weight and reducing drag. A near-future goal of the BLI studies is to determine if modern engine front-mounted fans can be designed to operate efficiently and stably under BLI inlet conditions. The D8 design is aimed at the huge single-aisle, narrow-body market, now dominated by the Boeing 737 and Airbus 320 families. Airframe and engine designers strive to achieve 'clean' inlet flow conditions for jet engines.
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Reddy, P. Nithish. "Hypersonic Scram-Jet Engine Inlet Design." International Journal for Research in Applied Science and Engineering Technology 7, no. 6 (June 30, 2019): 1619–35. http://dx.doi.org/10.22214/ijraset.2019.6273.

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Smith, Jerome P., Ricardo A. Burdisso, and Chris R. Fuller. "Active control of jet engine inlet noise." Journal of the Acoustical Society of America 101, no. 5 (May 1997): 3122. http://dx.doi.org/10.1121/1.418918.

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Biglarian, M., A. Najafi, and S. M. Negharchi. "Numerical Analysis of inlet vortex in the scaled engine." IOP Conference Series: Materials Science and Engineering 1196, no. 1 (October 1, 2021): 012033. http://dx.doi.org/10.1088/1757-899x/1196/1/012033.

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Abstract A jet engine that works near the ground and generates high thrust at low speed can experience the flow separation from the ground surface up to its inlet and, as a result, the formation of a famous vortex. This vortex extended from the ground surface to the fan inlet is known as the inlet vortex. In the present study, a jet engine model scaled down by 1/30 relative to the real jet engine with 3 million hexahedral elements is simulated using Computational Fluid Dynamics (CFD). The obtained results agree with empirical relationships, and the inlet vortex can be analyzed in scales much lower than the original prototype. Also, the inlet vortex gets weakened by increasing free stream velocity and completely degraded at higher velocities. By understanding how this phenomenon occurs and can be dealt with, the Foreign Object Damages (FOD) such as compressor surge, fan vibration, and particle ingestion into the engine core can be prevented.
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Tam, Christopher K. W., Sarah A. Parrish, Edmane Envia, and Eugene W. Chien. "Physical processes influencing acoustic radiation from jet engine inlets." Journal of Fluid Mechanics 725 (May 14, 2013): 152–94. http://dx.doi.org/10.1017/jfm.2013.181.

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AbstractNumerical simulations of acoustic radiation from a jet engine inlet are performed using advanced computational aeroacoustics algorithms and high-quality numerical boundary treatments. As a model of modern commercial jet engine inlets, the inlet geometry of the NASA Source Diagnostic Test is used. Fan noise consists of tones and broadband sound. This investigation considers the radiation of tones associated with upstream-propagating duct modes. The primary objective is to identify the dominant physical processes that determine the directivity of the radiated sound. Two such processes have been identified. They are acoustic diffraction and refraction. Diffraction is the natural tendency for an acoustic duct mode to follow a curved solid surface as it propagates. Refraction is the turning of the direction of propagation of a duct mode by mean flow gradients. Parametric studies on the changes in the directivity of radiated sound due to variations in forward flight Mach number, duct mode frequency, azimuthal mode number and radial mode number are carried out. It is found there is a significant difference in directivity for the radiation of the same duct mode from an engine inlet when operating in static condition versus one in forward flight. It will be shown that the large change in directivity is the result of the combined effects of diffraction and refraction.
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Pečinka, Jiří, Gabriel Thomas Bugajski, Petr Kmoch, and Adolf Jílek. "JET ENGINE INLET DISTORTION SCREEN AND DESCRIPTOR EVALUATION." Acta Polytechnica 57, no. 1 (February 28, 2017): 22–31. http://dx.doi.org/10.14311/ap.2017.57.0022.

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Total pressure distortion is one of the three basic flow distortions (total pressure, total temperature and swirl distortion) that might appear at the inlet of a gas turbine engine (GTE) during operation. Different numerical parameters are used for assessing the total pressure distortion intensity and extent. These summary descriptors are based on the distribution of total pressure in the aerodynamic interface plane. There are two descriptors largely spread around the world, however, three or four others are still in use and can be found in current references. The staff at the University of Defence decided to compare the most common descriptors using basic flow distortion patterns in order to select the most appropriate descriptor for future department research. The most common descriptors were identified based on their prevalence in widely accessible publications. The construction and use of these descriptors are reviewed in the paper. Subsequently, they are applied to radial, angular, and combined distortion patterns of different intensities and with varied mass flow rates. The tests were performed on a specially designed test bench using an electrically driven standalone industrial centrifugal compressor, sucking air through the inlet of a TJ100 small turbojet engine. Distortion screens were placed into the inlet channel to create the desired total pressure distortions. Of the three basic distortions, only the total pressure distortion descriptors were evaluated. However, both total and static pressures were collected using a multi probe rotational measurement system.
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Zhao, Xue Jun, Xiao Guo Guo, and Chang Zhao. "A New Support Structure in Waverider Force Measurement." Applied Mechanics and Materials 318 (May 2013): 96–99. http://dx.doi.org/10.4028/www.scientific.net/amm.318.96.

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In this paper a new support structure was given to solve the problem met in the force measurement with engine jet. The force measurements of waverider were undertaken in the hypersonic wind tunnel. The test condition was at Ma=6, angle of attack α=-6°-6°, at which we researched the effects on the vehicle aerodynamics of inlet cowl opening and closing, support system, engine jet, and pressure ratios. To decrease the effects of strut on the jet flow-field, we took sharp belly strut to support the model in the wind tunnel. The belly strut could support the waverider model, force measurement balance, and it could make the inlet flow set up, and provide the high pressure jet. The test results showed that the belly sharp strut had little effects on the flowfield and could inject the inlet flow, and could provide very high quality jet.
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Bazazzadeh, Mehrdad, and Ali Shahriari. "Enhancing the Performance of Jet Engine Fuel Controller Using Neural Networks." Applied Mechanics and Materials 390 (August 2013): 393–97. http://dx.doi.org/10.4028/www.scientific.net/amm.390.393.

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This paper proposes a fuzzy logic controller for a specific turbojet engine. The turbine engines require control systems to achieve the appropriate performance. The control systems typically featured loops to prevent engine flame out, over speeds, compressor surge, and check turbine inlet temperature limit, either by scheduling the fuel flow during accelerations and decelerations or by controlling the acceleration and deceleration rates of engine spool. This paper presents a successful approach in designing a Fuzzy Logic Controller for a specific Jet Engine. At first a suitable mathematical model for the jet engine is presented by the aid of SIMULINK simulation software. Then by applying different reasonable fuel flow functions via the engine model, some important engine continuous time operation parameters (such as: thrust, compressor surge margin, turbine inlet temperature and engine spool speed...) are obtained. These parameters provide a precious database which can be used by a neural network. At the second step, by designing and training a feedforward multilayer perceptron neural network according to this available database; a number of different reasonable fuel flow functions for various engine acceleration operations are determined. These functions are used to define the desired fuzzy fuel functions. Indeed, the neural networks are used as an effective method to define the optimum fuzzy fuel functions. At the next step we design a fuzzy logic controller by using the engine simulation model and the neural network results. The proposed control scheme is proved by computer simulation using the designed engine model. The simulation results of engine model with fuzzy controller in comparison with the engine testing operation illustrate that the proposed controller achieves the desired performance.
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Catana, Razvan Marius, and Grigore Cican. "Study of Air Excess in Relation with Engine Parameters for a Generalized Reaction Based on JET-A Fuel." Applied Mechanics and Materials 772 (July 2015): 395–400. http://dx.doi.org/10.4028/www.scientific.net/amm.772.395.

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In this paperwork we are studying the performance of a combustion process into a jet engine combustion chamber, more specifically the relations between excess of air, overall pressure ratio and inlet turbine temperature for a combustion reaction based on a jet A fuel. The study present a method of calculating the excess of air for a generalized combustion reaction based on Jet A fuel indicated by the general formula , for different temperatures of air, different temperatures of fuel and different inlet turbine temperatures. The result of this study is to achieve diagrams in which are presented the variation of air excess with engine parameters who participate in combustion process and to performed a computing program in which it is calculated the exactly value of excess of air for any outlet compressor temperatures, any inlet turbine temperatures and different fuel temperatures.
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Fukuda, Masafumi, Hiroshi Harada, Tadaharu Yokokawa, and Tomonori Kitashima. "Virtual Jet Engine System." Materials Science Forum 638-642 (January 2010): 2239–44. http://dx.doi.org/10.4028/www.scientific.net/msf.638-642.2239.

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In 1999, we proposed the concept of a virtual gas turbine system which is a combination of turbine design and material design programs. Using this system, it has become possible to design a gas turbine engine and a combined cycle automatically, by inputting some basic information such as power output, turbine inlet temperature and material specifications. The derived outputs are turbine gas path dimensions, gas and cooling air flow rates, thermal efficiency, CO2 emissions, etc. We use the system to evaluate the potential improvement if a newly developed material is to be used in building the engine. Based on the virtual gas turbine system we have begun developing the virtual jet engine system, which can simulate the operation of a jet engine or a gas turbine engine to predict the degradation of materials used in the high temperature parts of the engine. The system consists of a thermal and aerodynamic analysis of the engine, a thermal and stress analysis of hot parts, and a material degradation analysis. Actual engine dimensions, operation data and material specifications are used to perform the analyses. In this paper, we will show some of the results of the use of the virtual gas turbine system, and then describe the development plan and the preliminary output of the virtual jet engine system.
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Dissertations / Theses on the topic "Jet engine inlet"

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Hoopes, Kevin M. "A New Method for Generating Swirl Inlet Distortion for Jet Engine Research." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/49545.

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Jet engines operate by ingesting incoming air, adding momentum to it, and exhausting it through a nozzle to produce thrust. Because of their reliance on an inlet stream, jet engines are very sensitive to inlet flow nonuniformities. This makes the study of the effects of inlet nonuniformities essential to improving jet engine performance. Swirl distortion is the presence of flow angle nonuniformity in the inlet stream of a jet engine. Although several attempts have been made to accurately reproduce swirl distortion profiles in a testing environment, there has yet to be a proven method to do so.

A new method capable of recreating any arbitrary swirl distortion profile is needed in order to expand the capabilities of inlet distortion testing. This will allow designers to explore how an engine would react to a particular engine airframe combination as well as methods for creating swirl distortion tolerant engines. The following material will present such a method as well as experimental validation of its effectiveness.
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Kumar, Abhinav. "Flow control optimization in a jet engine serpentine inlet duct." [College Station, Tex. : Texas A&M University, 2007. http://hdl.handle.net/1969.1/ETD-TAMU-1399.

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Tichenor, Nathan Ryan. "Particle image velocimetry in an advanced, serpentine jet engine inlet duct." Thesis, [College Station, Tex. : Texas A&M University, 2007. http://hdl.handle.net/1969.1/ETD-TAMU-1401.

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Kirk, Aaron Michael. "Active flow control in an advanced serpentine jet engine inlet duct." [College Station, Tex. : Texas A&M University, 2006. http://hdl.handle.net/1969.1/ETD-TAMU-1027.

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Reilly, Daniel. "An Investigation into Jet Engine Inlet Flow Characteristics for Turbine-Powered Helicopters." The Ohio State University, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=osu1429608968.

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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.

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Giuliani, James Edward. "Jet Engine Fan Response to Inlet Distortions Generated by Ingesting Boundary Layer Flow." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1468564279.

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Sivapragasam, M. "Numerical and experimental investigations on multiple air jets in counterflow for generating aircraft gas turbine engine inlet flow distortion patterns." Thesis, Coventry University, 2014. http://curve.coventry.ac.uk/open/items/0ad1d0c2-6693-4c6e-9224-5a2237862074/1.

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The performance of an aircraft gas turbine engine is adversely affected by the non-uniform or distorted flow in the inlet duct. Inlet flow distortion lowers the surge margin of the engine‟s compression system with surge occurring at much lower pressure ratios at all engine speeds. The compressor and/or engine are subjected to ground tests in the presence of inlet distortion to evaluate its performance. The simplest method of simulating inlet distortion during these tests is by installing a distortion screen ahead of the engine on the test bed. The uniform inlet flow to the compressor becomes nonuniform with total pressure loss after passing through the distortion screen. Though the distortion screens offer a number of significant advantages, they have some disadvantages. The air jet distortion system can alleviate many of the operational disadvantages encountered with the conventional distortion screens. The system consists of a number of air jets arranged in a circumferential array in a plane and issuing opposite to the primary air flow entering the engine. The jets interact with the primary stream and cause a local total pressure loss due to momentum exchange. The individual mass flow rates from the jets can be varied to obtain a required total pressure pattern ahead of the compressor at the Aerodynamic Interface Plane (AIP). A systematic study of the flow field of confined, turbulent, incompressible, axisymmetric jet issuing into counterflow is covered in this research programme. The jet penetration length and the jet width are reduced compared to unconfined counterflow and a linear relationship between the velocity ratio and the jet length ceases to be valid. The flow field of a circular compressible turbulent jet and then a system of four jets arranged circumferentially and issuing into a confined counterflow was studied experimentally and numerically. For the four jet system the mass flow rates in the four jets were equal in the first part of the study and in the second part they were unequal. The loss in total pressure due to the jet(s) interacting with the counterflow was quantified by a total pressure loss parameter λp0. The total pressure loss increased with increasing mass flow ratio. The total pressure loss distribution was evaluated at several locations behind the jet injector(s). The total pressure non-uniformity quantified by Distortion Index (DI) was found to be highest at a location just downstream of the jet injector and at far downstream locations low values of DI were observed. From the understanding gained with a single jet and four jets in counterflow a methodology was developed to generate a given total pressure distortion pattern at the AIP. The methodology employs computations to obtain the total pressure distortion at the AIP with quasi-one-dimensional inviscid analysis used as a starting point to estimate the mass flow rate in the jets. The inviscid analysis also provides a direction to the iterative procedure to vary the mass flow rate in the jets at the end of each computational step. The methodology is demonstrated to generate a given total pressure distortion pattern using four jets and is further extended to a larger number of jets, twelve and later twenty jets. The total pressure distortion patterns typical of use in aircraft gas turbine engine testing are generated accurately with a smaller number of jets than reported in the literature.
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Clark, Adam. "Predicting the Crosswind Performance of High Bypass Ratio Turbofan Engine Inlets." The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1476265135449178.

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Lambie, David. "Inlet distortion and turbofan engines." Thesis, University of Cambridge, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.305300.

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Books on the topic "Jet engine inlet"

1

Steenken, William G. An inlet distortion assessment during aircraft departures at high angle of attack for an F/A-18A aircraft. Edwards, Calif: NASA Dryden Flight Research Center, 1997.

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Trefny, Charles J. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. Cleveland, Ohio: Lewis Research Center, 1986.

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Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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Powell, A. G. Low-speed aerodynamic test of an axisymmetric supersonic inlet with variable cowl slot. [Washington, DC]: National Aeronautics and Space Administration, 1985.

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B, True, Holdeman J. D, and United States. National Aeronautics and Space Administration., eds. Effects of initial conditions on a single jet in crossflow. [Washington, DC]: National Aeronautics and Space Administration, 1995.

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E, Neumann Harvey, Shaw Robert J. 1946-, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Performance and surge limits of a TF30-P-3 turbofan engine/axisymmetric mixed-compression inlet propulsion system at Mach 2.5. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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P, Myers Lawrence, Mackall Karen G, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Effects of inlet distortion on a static pressure probe mounted on the engine hub in an F-15 airplane. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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NASA Dryden Flight Research Center., ed. An inlet distortion assessment during aircraft departures at high angle of attack for an F/A-18A aircraft. Edwards, Calif: NASA Dryden Flight Research Center, 1997.

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W, Wasserbauer Joseph, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch., eds. Low-speed performance of an axisymmetric, mixed-compression, supersonic inlet with auxiliary inlets. [Washington, D.C.]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1986.

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Book chapters on the topic "Jet engine inlet"

1

Decher, Reiner. "More Components: Inlets, Mixers, and Nozzles." In The Vortex and The Jet, 137–54. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_13.

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AbstractTheintegrationof a gas turbine engine into a functioning jet propulsion engine for an airplane requires more components: inlets and nozzles. For the inlet, the special care exercised to avoid ingestion of boundary layers air is described. The design features of nozzles are described and extended to include discussion of more extreme configurations such as those found on rocket engines.
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Theune, Marius, Dirk Schönweitz, and Rainer Schnell. "Sensitivity of a Low Pressure Ratio Jet Engine Fan to Inlet Distortion." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 63–73. Cham: Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-27279-5_6.

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Conference papers on the topic "Jet engine inlet"

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Al-Khalil, Kamel, Theo Keith, Jr., and Kenneth De Witt. "Icing calculations on a typical commercial jet engine inlet nacelle." In 32nd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-610.

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Balepin, Vladimir, and Glenn Liston. "The Steam Jet - Mach 6+ turbine engine with inlet air conditioning." In 37th Joint Propulsion Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2001. http://dx.doi.org/10.2514/6.2001-3238.

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BEALE, D., and M. S. COLLIER. "Validation of a free-jet technique for evaluating inlet-engine compatibility." In 25th Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-2325.

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Al-Khalil, Kamel, Richard Hitzigrath, Oliver Philippi, and Colin Bidwell. "Icing analysis and test of a business jet engine inlet duct." In 38th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-1040.

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Fujii, Akira, Shinichi Mizuno, Hironori Horiguchi, and Yoshinobu Tsujimoto. "Suppression of Cavitation Instabilities by Jet Injection at Inducer Inlet." In ASME 2005 Fluids Engineering Division Summer Meeting. ASMEDC, 2005. http://dx.doi.org/10.1115/fedsm2005-77380.

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Cavitation instabilities such as rotating cavitation and cavitation surge often occur in turbopump inducers for rocket engine. In the present study, a method for suppressing the cavitation instabilities in an inducer by jet injection is examined. Through eight nozzles placed at the upstream of the inducer, jets were injected in circumferential direction. The axial position of nozzles, speed of jet flow and direction of jet injection were changed. Through the experiments under various conditions, it was found that the occurrence regions of cavitation instabilities are decreased significantly with the injection in the same direction as shaft rotation with the jet flow rate about 10% of total flow. The flow field was also examined to clarify the mechanism for the suppression by injection. It was found that the incidence angle and cavity length were reduced by the injection, which decreases the occurrence region of instabilities.
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Naseri, A., M. Boroomand, A. M. Tousi, and A. R. Alihosseini. "The Effect of Inlet Flow Distortion on Performance of a Micro-Jet Engine: Part 2 — Engine Tests." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-86803.

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This paper concerns investigating effect of inlet flow distortion on performance of a micro-jet engine. An experimental study has been carried out to determine how the steady state inlet total-pressure distortion affects the performance of a micro gas turbine engine. An inlet simulator is designed and developed to produce and measure distortion patterns at the engine inlet. An Air Jet Distortion Generator is used to produce non-uniform flow patterns and total pressure probes are implemented to measure steady state total pressure distribution at the engine face. A set of wind tunnel tests has been performed to confirm the fidelity of distortion generator and measuring devices. The engine got exposed to inlet flow with 60-degree, 120-degree, and 180-degree circumferential distortion patterns with different distortion intensities and the engine performance have been measured and compared with that of clean inlet flow. Results indicate that engine performance can be affected significantly facing with intense inlet distortions.
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Krasheninnikov, S. Yu, and D. E. Pudovikov. "Analysis of the reverse jet influence on particle ingestion at the engine inlet." In Progress in Flight Physics – Volume 7, edited by D. Knight, I. Lipatov, and P. Reijasse. Les Ulis, France: EDP Sciences, 2015. http://dx.doi.org/10.1051/eucass/201507283.

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Tasic, Miodrag, Branko Kolundzija, and Tomislav Milosevic. "Domain decomposition method for scattering from an aircraft with jet engine inlet cavity." In 2018 International Applied Computational Electromagnetics Society Symposium (ACES). IEEE, 2018. http://dx.doi.org/10.23919/ropaces.2018.8364325.

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Naseri, A., M. Boroomand, and A. M. Tousi. "The Effect of Inlet Flow Distortion on Performance of a Micro-Jet Engine: Part 1 — Development of an Inlet Simulator." In ASME 2012 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/imece2012-86865.

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This paper represents the development of an inlet simulator to produce and measure steady state total-pressure distortion at the inlet of a micro-jet engine. Different methods of distortion generation and engine testing are discussed and the developed system is described. The developed inlet simulator device consists of a direct connecting air supply duct, a distortion generator unit inside the duct ahead of the engine inlet, and a matrix of total pressure probes at the end of the duct and close to engine entry. An Air Jet Distortion Generator is designed and developed to produce desired distortion patterns at the engine face. A series of wind tunnel tests has been carried out to verify the ability of the system to simulate various inlet flow conditions. Circumferential patterns with 60, 120 and 180 degree distorted zones with different distortion intensities were produced during wind tunnel tests. Measured distortion patterns are represented and the proper operation of the system in wind tunnel is discussed and proved. The inlet simulator then get installed on a micro gas turbine engine and distortion patterns has been produced and measured at the engine inlet during engine performance tests. Measured patterns at the engine inlet and the engine responses are represented.
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Morton, Wayne K., Glen R. Lazalier, C. Dennis Rose, and R. F. (Pete) Lauer. "On-Line Distortion Analysis System for Inlet-Engine Testing." In ASME 1991 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1991. http://dx.doi.org/10.1115/91-gt-166.

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A system for “near-real-time” distortion analysis support of aircraft turbine engine-inlet altitude testing is described. Target applications include both subscale and full-scale inlet-engine compatibility testing in wind tunnel, direct-connect, and free-jet configurations. The system digitizes analog-format, time-dependent data and combines it with digital-format, steady-state data. A high-speed data bus and multiple array processors provide for on-line execution of complex distortion analysis algorithms to compute and display distortion indices, histograms, isobar plots, and surge margin consumption. Analysis algorithms are programmed using a high-level language (FORTRAN 77).
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