Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes Nasa Tm 1998 208839 Mar 1 1999
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Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes Nasa Tm 1998 208839 Mar 1 1999
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Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 1999*
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes Nasa Tm 1998 208839 Mar 1 1999 written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1999* with categories.
Unsteady Analysis Of Inlet Compressor Acoustic Interactions Using Coupled 3 D And 1 D Cfd Codes
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Author :
language : en
Publisher:
Release Date : 2000
Unsteady Analysis Of Inlet Compressor Acoustic Interactions Using Coupled 3 D And 1 D Cfd Codes written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2000 with categories.
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-08-16
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-08-16 with categories.
A problem that arises in the numerical simulation of supersonic inlets is the lack of a suitable boundary condition at the engine face. In this paper, a coupled approach, in which the inlet computation is coupled dynamically to a turbomachinery computation, is proposed as a means to overcome this problem. The specific application chosen for validation of this approach is the collapsing bump experiment performed at the University of Cincinnati. The computed results are found to be in reasonable agreement with experimental results. The coupled simulation results could also be used to aid development of a simplified boundary condition. Suresh, A. and Townsend, S. E. and Cole, G. L. and Slater, J. W. and Chima, R. Glenn Research Center NASA/TM-1998-208839, NAS 1.15:208839, AIAA Paper 98-0749, E-11451 NAS3-98008; RTOP 509-10-11...
Unsteady Analysis Of Inlet Compressor Acoustic Interactions Using Coupled 3 D And 1 D Cfd Codes
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-06-16
Unsteady Analysis Of Inlet Compressor Acoustic Interactions Using Coupled 3 D And 1 D Cfd Codes written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-06-16 with categories.
It is well known that the dynamic response of a mixed compression supersonic inlet is very sensitive to the boundary condition imposed at the subsonic exit (engine face) of the inlet. In previous work, a 3-D computational fluid dynamics (CFD) inlet code (NPARC) was coupled at the engine face to a 3-D turbomachinery code (ADPAC) simulating an isolated rotor and the coupled simulation used to study the unsteady response of the inlet. The main problem with this approach is that the high fidelity turbomachinery simulation becomes prohibitively expensive as more stages are included in the simulation. In this paper, an alternative approach is explored, wherein the inlet code is coupled to a lesser fidelity 1-D transient compressor code (DYNTECC) which simulates the whole compressor. The specific application chosen for this evaluation is the collapsing bump experiment performed at the University of Cincinnati, wherein reflections of a large-amplitude acoustic pulse from a compressor were measured. The metrics for comparison are the pulse strength (time integral of the pulse amplitude) and wave form (shape). When the compressor is modeled by stage characteristics the computed strength is about ten percent greater than that for the experiment, but the wave shapes are in poor agreement. An alternate approach that uses a fixed rise in duct total pressure and temperature (so-called 'lossy' duct) to simulate a compressor gives good pulse shapes but the strength is about 30 percent low. Suresh, A. and Cole, G. L. Glenn Research Center NASA/TM-2000-210247, E-12367, NAS 1.15:210247
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes
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Author : A. Suresh
language : en
Publisher:
Release Date : 1998
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes written by A. Suresh and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with categories.
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes
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Author :
language : en
Publisher:
Release Date : 1998
Analysis Of Inlet Compressor Acoustic Interactions Using Coupled Cfd Codes written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1998 with categories.
Experimental Investigation Of Rapid Flow Transients In An Inlet Compressor System Induced By Short Duration Acoustic And Entropy Disturbances
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Author : Anthony Benedict Opalski
language : en
Publisher:
Release Date : 2002
Experimental Investigation Of Rapid Flow Transients In An Inlet Compressor System Induced By Short Duration Acoustic And Entropy Disturbances written by Anthony Benedict Opalski and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 2002 with categories.
Highly sophisticated and extensively tested computational fluid dynamics codes are available to simulate the operation of inlet and compressor systems in high-speed air-breathing propulsion devices. In contrast, the methods used to couple these codes during the simulation of an unsteady flow transient are in a significantly less advanced state. In engineering practice the computations are typically performed separately for each device, while representing the adjacent component through a boundary condition. Unfortunately, the lack of experimentally validated compressor face boundary conditions leaves the accuracy of these models open to doubt. From the viewpoint of inlet computations, the compressor face boundary condition amounts to an approximate description of the manner in which upstream moving acoustic waves are induced by the arrival of downstream moving acoustic and entropy (temperature) disturbances to the compressor. This dissertation presents the results of an experimental investigation involving such rapid flow transients in a facility that combined a constant area circular inlet with a single-stage axial-flow compressor. Inlet Mach numbers ranged from 0.15 to 0.45. The experiment employed an impulse method, in which short-duration, large amplitude acoustic and entropy pulses were generated within the inlet utilizing an exploding wire technique. The incident acoustic pulse, its reflection from the compressor and the acoustic wave transmitted across the compressor were tracked by fast response pressure transducers, while entropy pulses were detected by dual-element hotfilm probes. Frequency domain analysis of the data yielded transfer functions that may be thought of as non-dimensional frequency-resolved reflection, transmission and induction coefficients. Transfer functions have been demonstrated to be suitable for the prediction of transients induced by small amplitude, incident acoustic and entropy pulses, thereby representing a powerful method for extending the results of the single experiment to a wide array of situations. The experimental results show that the amplitudes of both the reflections, and the upstream-moving acoustic waves induced by the incident entropy waves, increase with increasing axial Mach numbers. None of the currently customary compressor-face boundary conditions can predict the data obtained in this study, strongly suggesting that conventional practices concerning outflow boundary conditions during unsteady flow transients are in need of reassessment.
A Simplified Model For The Investigation Of Acoustically Driven Combustion Instabilities Nasa Tm 1998 208488 Mar 1 1999
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Author : United States. National Aeronautics and Space Administration
language : en
Publisher:
Release Date : 1999*
A Simplified Model For The Investigation Of Acoustically Driven Combustion Instabilities Nasa Tm 1998 208488 Mar 1 1999 written by United States. National Aeronautics and Space Administration and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1999* with categories.
Analytical And Experimental Studies Of Acoustic Performance Of Segmented Liners In A Compressor Inlet
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Author :
language : en
Publisher:
Release Date : 1977
Analytical And Experimental Studies Of Acoustic Performance Of Segmented Liners In A Compressor Inlet written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1977 with Airplanes categories.