Implementation of a compressor face boundary condition based on small disturbances

Proceedings of the ASME Turbo Expo

Volumn 1, Issue , 2000, Pages

  Slater, John W ^a   Paynter, Gerald C ^b  

^a NASA GLENN RESEARCH CENTER   (United States)

^b BOEING COMPANY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AIRCRAFT ENGINES; COMPRESSORS; COMPUTATIONAL FLUID DYNAMICS; DUCTS; ONE DIMENSIONAL; SUPERSONIC AIRCRAFT;

ACOUSTIC DISTURBANCES; ACOUSTIC RESPONSE; CONVECTIVE VELOCITY; LOCALLY ONE-DIMENSIONAL; SMALL DISTURBANCE MODELS; SMALL DISTURBANCES; THREE DIMENSIONAL COMPUTATIONAL FLUID DYNAMICS; UNSTEADY INTERACTION;

BOUNDARY CONDITIONS;

EID: 84955327574     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: 10.1115/1.1344884     Document Type: Conference Paper

References (11)

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8. Sajben, M. 1999, "Prediction of Acoustic, Vorticity, and Entropy Waves Generated by Short-Duration Acoustic Pulses Incident on a Blade Row," 1999-GT-148.
9. Shapiro, A.H., 1954, The Dynamics and Thermodynamics of Compressible Fluid Flow, Ronald Press Company, New York.
10. Suresh, A., Townsend, S.E., Cole, G.L., Slater, J.W., and Chima, R., 1999, "Analysis of Inlet-Compressor Acoustic Interactions Using Coupled CFD Codes", AIAA 99-0749.
11. Wasserbauer, J.F., Shaw, R.J., and Neumann, H.E., 1975, "Design of a Very-Low-Bleed Mach 2.5 Mixed-Compression Inlet with 45 Percent Internal Contraction", NASA TM X-3135.