Relevant bibliographies by topics / Turbofan inlet

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

Academic literature on the topic 'Turbofan inlet'

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

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Journal articles on the topic "Turbofan inlet"

1

Lowe, K. Todd. "Laser velocimetry for turbofan inlet distortion applications." Aircraft Engineering and Aerospace Technology 92, no. 1 (2020): 20–26. http://dx.doi.org/10.1108/aeat-11-2018-0285.

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Purpose The purpose of this paper is to assess state-of-the-art techniques for quantifying flow distortion in the inlets of turbofan engines, particularly with respect to the prospects for future flight applications. Design/methodology/approach To adequately characterize the flow fields of complex aircraft inlet distortions, the author has incorporated laser velocimetry techniques, namely, stereoscopic particle image velocimetry (PIV) and Doppler velocimetry based on filtered Rayleigh scattering (FRS), into inlet distortion studies. Findings Overall, the results and experience indicate that th
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2

Prasad, Dilip, and Jinzhang Feng. "Propagation and Decay of Shock Waves in Turbofan Engine Inlets." Journal of Turbomachinery 127, no. 1 (2005): 118–27. http://dx.doi.org/10.1115/1.1811102.

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Numerical experiments are carried out to investigate the tone noise radiated from a turbofan engine inlet under conditions at which the relative flow past the rotor tip is supersonic. Under these conditions, the inlet tone noise is generated by the upstream-propagating rotor-locked shock wave field. The spatial evolution of this shock system is studied numerically for flows through two basic hard-walled configurations: a slender nacelle with large throat area and a thick nacelle with reduced throat area. With the flight Mach number set to 0.25, the spatial evolution of the acoustic power throu
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3

Eversman, Walter. "Broadband noise suppression for turbofan inlet applications." International Journal of Aeroacoustics 15, no. 4-5 (2016): 367–94. http://dx.doi.org/10.1177/1475472x16642131.

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4

Wang, Bin, Xi Wang, and Yue Liu. "Single Neuron PID Control of a Turbofan Engine with Inlet Pressure Distortion." Advanced Materials Research 753-755 (August 2013): 1534–38. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1534.

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In this paper, a preliminary exploration and research about the adaptive control law has been carried on for the turbofan engine with inlet pressure distortion. First, a real-time dynamic component-based model which contains the inlet distortion effects was established. Then, we select a single neuron PID controller with adaptive parameters to complete the dynamic acceleration process. The results illustrate that the single neuron control algorithm with gain adaptive has strong robustness, self-learning and anti-jamming capability and the performance of a turbofan engine can be effectively imp
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5

Schaut, Larry A. "Rotating acoustically lined inlet splitter for a turbofan engine." Journal of the Acoustical Society of America 103, no. 3 (1998): 1246. http://dx.doi.org/10.1121/1.423191.

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6

Kroeger, Jim. "Large and Small Turbofans." Mechanical Engineering 138, no. 09 (2016): 80–82. http://dx.doi.org/10.1115/1.2016-sep-7.

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This article presents a study on common design challenges of large and small turbofans. Turbofan engines powering large transport aircraft have demonstrated much different design objectives than business-jet turbofans including thrust, range, mission type, development cost, unit price, maintainability standards, and production quantities. Prolific use of ‘thermal barrier coating’ has helped turbine designers compensate for the inability to distribute a large quantity of small diameter film holes over the turbine blade surface. The historical trends in overall pressure ratio observed for both l
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7

Zhang, Jin Chuan, Yun Wang, and Can Zhang. "Basic Research of the Intercooled Turbofan Aero-Engine." Advanced Materials Research 516-517 (May 2012): 544–47. http://dx.doi.org/10.4028/www.scientific.net/amr.516-517.544.

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In conventional turbofan aero-engine designs, the effective way of improvement of engine efficiency is through the increasing of overall pressure ratio and improving of combustor inlet gas temperature, but the further incresement of compressor overall pressor ratio is constricted by high pressure compressor outlet allowed temperature. The improvement of combustor outlet temperature is limited by turbine allowed inlet temperature during take-off and climbing. An intercooled core can be designed with a significantly higher overall pressure ratio also with reduced cooling air requirements, provid
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8

Verma, Vishwas, Gursharanjit Singh, and AM Pradeep. "The effect of inlet distortion on low bypass ratio turbofan engines." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 8 (2020): 1395–413. http://dx.doi.org/10.1177/0954410020909190.

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Inlet flow non-uniformity, commonly known as inflow distortion, has been a long-standing problem in the history of gas turbine engines. Distortion can be present in the form of total pressure, total temperature or inflow incidence or any combinations of these. The search for better and robust performance requires engines that can sustain a large amount of inlet distortion without considerable loss in the thrust. In the present paper, the effect of total pressure distortion on a single-stage compressor and low bypass ratio fans are studied. Distortion near hub and tip in the form of step radial
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9

Joppa, P. D. "Acoustic mode measurements in the inlet of a turbofan engine." Journal of Aircraft 24, no. 9 (1987): 587–93. http://dx.doi.org/10.2514/3.45482.

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10

Bae, Kyoungwook, Chanoh Min, Bongkyu Cheon, Changyong Lee, and Daewoo Lee. "Control System of Turbofan Engine with Variable Inlet Guide Vane." Journal of the Korean Society for Aeronautical & Space Sciences 42, no. 3 (2014): 237–42. http://dx.doi.org/10.5139/jksas.2014.42.3.237.

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Dissertations / Theses on the topic "Turbofan inlet"

1

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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2

Hall, Zachary Mitchel Ahmed Anwar. "Experimental and computational investigation of a turbofan inlet duct." Auburn, Ala., 2009. http://hdl.handle.net/10415/1958.

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3

Guimaraes, Bucalo Tamara. "Fluid Dynamics of Inlet Swirl Distortions for Turbofan Engine Research." Diss., Virginia Tech, 2018. http://hdl.handle.net/10919/82921.

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Significant effort in the current technological development of aircraft is aimed at improving engine efficiency, while reducing fuel burn, emissions, and noise levels. One way to achieve these is to better integrate airframe and propulsion system. Tighter integration, however, may also cause adverse effects to the flow entering the engines, such as total pressure, total temperature, and swirl distortions. Swirl distortions are angular non-uniformities in the flow that may alter the functioning of specific components of the turbomachinery systems. To investigate the physics involved in the inge
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4

Lucas, James Redmond. "Effect of BLI-Type Inlet Distortion on Turbofan Engine Performance." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23272.

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Boundary Layer Ingestion (BLI) is currently being researched as a potential method to improve efficiency and decrease emissions for the next generation of commercial aircraft.  While re-energizing the boundary layer formed over the fuselage of an aircraft has many system level benefits, ingesting the low velocity boundary layer flow through a serpentine inlet into a turbofan engine adversely affects the performance of the engine.  The available literature has only yielded studies of the effects of this specific type of inlet distortion on engine performance in the form of numerical simulations
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5

Risi, John D. "Analytical investigation of active control of radiated inlet noise from turbofan engines." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-08222009-040623/.

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6

Frohnapfel, Dustin Joseph. "Experimental Investigation of Fan Rotor Response to Inlet Swirl Distortion." Thesis, Virginia Tech, 2016. http://hdl.handle.net/10919/71323.

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Next generation aircraft design focuses on highly integrated airframe/engine architectures that exploit advantages in system level efficiency and performance. One such design concept incorporates boundary layer ingestion which locates the turbofan engine inlet near enough to the lifting surface of the aircraft skin that the boundary layer is ingested and reenergized. This process reduces overall aircraft drag and associated required thrust, resulting in fuel savings and decreased emissions; however, boundary layer ingestion also creates unique challenges for the turbofan engines operating in
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7

Dungan, Mary Elizabeth. "Development of a compact sound source for the active control of turbofan inlet noise /." This resource online, 1992. http://scholar.lib.vt.edu/theses/available/etd-03302010-020615/.

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Dungan, Mary E. "Development of a compact sound source for the active control of turbofan inlet noise." Thesis, Virginia Tech, 1992. http://hdl.handle.net/10919/41872.

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The concept of a compact sound source driven by piezoactuators is experimentally investigated, and analytical design tools are developed. The sound source, consisting of a thin, cylindrically curved aluminum panel and a pair of collocated, surface-bonded piezoceramic actuators, was developed with the objective of employing it as a secondary sound source in the active control of turbofan bladeinteraction inlet noise. The sound source was fitted in an experimental duct representative of an aircraft engine inlet, and the interior and exterior sound pressure levels generated by the source were
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9

Nelson, Michael Allan. "Stereoscopic Particle Image Velocimetry Measurements of Swirl Distortion on a Full-Scale Turbofan Engine Inlet." Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/64993.

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There is a present need for simulation and measuring the inlet swirl distortion generated by airframe/engine system interactions to identify potential degradation in fan performance and operability in a full-scale, ground testing environment. Efforts are described to address this need by developing and characterizing methods for complex, prescribed distortion patterns. A relevant inlet swirl distortion profile that mimics boundary layer ingesting inlets was generated by a novel new method, dubbed the StreamVane method, and measured in a sub scale tunnel using stereoscopic particle image veloci
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Weston, David Bruce. "High Fidelity Time Accurate CFD Analysis of a Multi-stage Turbofan at Various Operating Points in Distorted Inflow." BYU ScholarsArchive, 2014. https://scholarsarchive.byu.edu/etd/5604.

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Inlet distortion is an important consideration in fan performance. Distortion can be caused through flight conditions and airframe-engine interfaces. The focus of this paper is a series of high-fidelity time accurate Computational Fluid Dynamics (CFD) simulations of a multistage fan. These investigate distortion transfer and generation as well as the underlying flow physics of these phenomena under different operating conditions. The simulations are performed on the full annulus of a 3 stage fan. The code used to carry out these simulations is a modified version of OVERFLOW 2.2 developed as
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Books on the topic "Turbofan inlet"

1

Clark, L. R. Inlet shape effects on the far-field sound of a model fan. American Institute of Aeronautics and Astronautics, 1997.

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2

G, Williams J. Estimating engine airflow in gas-turbine powered aircraft with clean and distorted inlet flows. National Aeronautics and Space Administration, Dryden Flight Research Center, 1996.

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3

Walter, Eversman, Meyer H. D, and United States. National Aeronautics and Space Administration., eds. Improved finite element modeling of the turbofan engine inlet radiation problem. National Aeronautics and Space Administration, 1993.

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4

Effect of spatial inlet temperature and pressure distortion on turbofan engine stability. National Aeronautics and Space Administration, 1988.

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5

M, Mehalic Charles, Stancik Kevin, and Lewis Research Center, eds. Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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6

Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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7

M, Mehalic Charles, Stancik Kevin, and Lewis Research Center, eds. Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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M, Mehalic Charles, Stancik Kevin, and Lewis Research Center, eds. Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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M, Mehalic Charles, Stancik Kevin, and Lewis Research Center, eds. Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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M, Mehalic Charles, Stancik Kevin, and Lewis Research Center, eds. Effect of steady-state temperature distortion on inlet flow to a high-bypass-ratio turbofan engine. Lewis Research Center, 1985.

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Conference papers on the topic "Turbofan inlet"

1

Godard, Benjamin, Nabil Ben Nasr, Raphaël Barrier, Julien Marty, Nicolas Gourdain, and Edouard De Jaeghere. "Methodologies for Turbofan Inlet Aerodynamics Prediction." In 35th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3413.

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2

Frohnapfel, Dustin J., Elizabeth Mack, Alexandrina Untaroiu, Walter F. O’Brien, and K. Todd Lowe. "Turbofan Nose Cone Interactions With Inlet Swirl." In ASME Turbo Expo 2018: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/gt2018-76616.

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With highly integrated airframe architectures emerging as the leading concept of next generation aviation vehicles, research is needed to understand the interactions between inlet swirl distortions and turbofan engines. To meet these research demands, a computational fluid dynamics investigation was conducted to monitor the streamwise development of a complex swirling velocity field in the inlet duct of a turbofan engine with and without the presence of the turbofan nose cone component. By modeling the two geometric setups, natural fluid development and forced fluid/nose cone interactions were
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3

Zheng, Shi, and Mei Zhuang. "Liner Layout Optimization for Turbofan Engine Inlet Ducts." In 11th AIAA/CEAS Aeroacoustics Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-2898.

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4

Smith, J., and R. Burdisso. "Active control of inlet noise from a turbofan engine using inlet wavenumber sensors." In 5th AIAA/CEAS Aeroacoustics Conference and Exhibit. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-1808.

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5

ZUMWALT, G. "Electro-impulse de-icing of a turbofan engine inlet." In 21st Joint Propulsion Conference. American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1118.

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6

Burdisso, Ricardo A., Russell H. Thomas, Chris R. Fuller, and Walter F. O'Brien. "Active Control of Radiated Inlet Noise from Turbofan Engines." In Noise & Vibration Conference & Exposition. SAE International, 1993. http://dx.doi.org/10.4271/931285.

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7

Wang, Zhonglin, Jingjing Chen, and Yong Chen. "Inlet Compatibility and Fan Aeromechanics of HBP Turbofan Engine." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63427.

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As an integrated system, turbofan engine airworthiness certification is a complex network because design, operating conditions and multi-disciplines are interlaced. Inlet compatibility specified in FAR regulations is to demonstrate satisfactory of engine operating characteristics throughout the flight envelope, which can be affected by engine installation and operation conditions. One limited operating condition is the high crosswind on the ground. Flow separated at engine inlet, unsteady and non-uniform, passing through the diffuser to the fan face, stimulated the fan blade at a broad frequen
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8

Zipkin, David, and Lance Shappell. "Air Cushion Vehicle Turbofan Propulsion Feasibility Analysis." In ASME Turbo Expo 2008: Power for Land, Sea, and Air. ASMEDC, 2008. http://dx.doi.org/10.1115/gt2008-50645.

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This paper explores the feasibility of utilizing turbofan gas turbines for combined propulsion and lift on an amphibious air cushion vehicle (ACV). The required thrust and bleed flow were identified, and employed to select possible COTS turbofans for this application. In addition, the turbofan cycle was evaluated for ACV applicability. The investigation revealed that a turbofan configuration would require a new inlet filtration system, which was categorized as high risk. Furthermore, fuel comparisons showed that the turbofan arrangement would require significantly more fuel when compared to th
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9

Lucas, James R., Walter F. O’Brien, and Anthony M. Ferrar. "Effect of BLI–Type Inlet Distortion on Turbofan Engine Performance." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26666.

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Boundary Layer Ingestion (BLI) is currently being researched as a potential method to improve efficiency and decrease emissions for the next generation of commercial aircraft. While re-energizing the boundary layer formed over the fuselage of an aircraft has many system level benefits, ingesting the low velocity boundary layer flow through a serpentine inlet into a turbofan engine adversely affects the performance of the engine. This work reports an experimental investigation of the effects of a BLI-type distortion on a turbofan engine’s performance. A modified JT15D-1 turbofan engine was used
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10

Godard, Benjamin, Edouard De Jaeghere, and Nicolas Gourdain. "Efficient Design Investigation of a Turbofan in Distorted Inlet Conditions." In ASME Turbo Expo 2019: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/gt2019-90471.

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Abstract Designing a turbofan to operate in distorted inlet conditions is an issue of growing interest. In such conditions however, fan design can be computationally challenging. Indeed, subject to neither axi-symmetrical nor periodic inlet conditions, computations must be carried out throughout the whole circumferential domain i.e. 360°. Besides, the classical CFD approach implies the use of URANS computations so as to capture the distortion transfer across the fan stage. Eventually, computations are too onerous to be used in design loops. In this context, this paper presents a methodology to
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