Turbine engine analysis compressor code: TEACC - Part II: Multi-stage compressors and inlet distortion

17th Applied Aerodynamics Conference

Volumn , Issue , 1999, Pages

  Hale, Alan ^a   Chalk, Jacqueline ^a   Klepper, Jason ^a   Kneile, Karl ^a  

^a JACOBS TECHNOLOGY   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; COMPRESSORS;

APPROXIMATE METHODS; COMPRESSION SYSTEM; COMPUTATIONAL TOOLS; HIGH PRESSURE COMPRESSOR; INLET PERFORMANCE; MULTISTAGE COMPRESSOR; NUMERICAL APPROACHES; RADIAL TOTAL PRESSURE DISTORTIONS;

COMPUTATIONAL FLUID DYNAMICS;

EID: 84964306105     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

References (14)

1. SAE Aerospace Information Report, AIR-1419, "Inlet Total-Pressure Distortion Considerations for Gas Turbine Engines", May 1983.
2. Greitzer, E. M. and Strand, T. "Asymmetric Swirling Flows in Turbomachine Annuli." ASME- 78-GT-109. ASME Gas Turbine Conference, London, England, April 1978.
3. Hale, A. A., Davis, M. W„ Jr., and Kneile, K. R. ’Turbine Engine Analysis Compressor Code: TEACC, Part I: Technical Approach and Steady Results." AIAA-94-0148. 32nd Aerospace Sciences Meeting, Reno, NV, January 1994.
4. Hale, A. A., and W. F. O’Brien, "A Three- Dimensional Turbine Engine Analysis Compressor Code (TEACC) for Steady-State Inlet Distortion," Journal of Turbomachinery. Vol. 120, July 1998, pp. 422-430.
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7. Hearsey, R. M. "HT0300 - A Computer Program for the Design and Analysis of Axial Turbomachinery." Cambridge, MA, March 1970.
8. Gostelow, J. P., Krabacher, K. W, and Smith, L. H., Jr. "Performance Comparisons of High Mach Number Compressor Rotor Blading." NASA CR- 1256, December 1968.
9. Seyler, D. R. and Gostelow, J. P. "Single Stage Experimental Evaluation of High Mach Number j Compressor Rotor Blading: Part 2 - Performance of Rotor IB." NASA CR-54582, September 1967.
10. Reid, L. and Moore, R. D. "Design and Overall j Performance of Four Highly Loaded, High-Speed Inlet Stages for an Advanced High-Pressure-Ratio Core Compressor." NASA-TP-1337, 1978.
11. Lieblein, S. "Chapter VI: Experimental Flow in Two-Dimensional Cascades." Aerodynamic Design of Axial-Flow Compressors. NASA-SP-36, 1965, pp.183-226.
12. Robbins, W. H., Jackson, R. J. and Lieblein, S. “Chapter VII: Blade-Element Flow in Annular Cascades.” Aerodynamic Design of Axial-Flow Compressors, NASA-SP-36, 1965, pp. 227-254.
13. Cooper, K., Jones, R., and Kincade, B. “NPARC Porous Wall Boundary Conditions.” Private communication and notes, May 1991
14. Pinker, R. A. and Herbert, M. V. “Pressure Loss Associated with Compressible Flow through Square-Mesh Wire Gauzes." Journal of Mechanical Engineering Science, Vol. 9, No. 1, 1967, pp. 1-23.