Boundary layer development in axial compressors and turbines. Part 2 of 4: Compressors
- GE Aircraft Engines, Cincinnati, OH (United States)
- Iowa State Univ., Ames, IA (United States)
- Univ. of Tasmania, Hobart (Australia)
- Univ. of Cambridge (United Kingdom)
This is Part Two of a four-part paper. It begins with Section 6.0 and continues to describe the comprehensive experiments and computational analyses that have led to a detailed picture of boundary layer development on airfoil surfaces in multistage turbomachinery. In this part, the authors present the experimental evidence used to construct the composite picture for compressors given in the discussion in Section 5.0 of Part 1. They show the data from the surface hot-film gages and the boundary layer surveys, give a thorough interpretation for the baseline operating condition, and then show how this picture changes with variations in Reynolds number, airfoil loading, frequency of occurrence of wakes and wake turbulence intensity. Detailed flow features are described using raw time traces. The use of rods to simulate airfoil wakes is also evaluated.
- Sponsoring Organization:
- USDOE
- OSTI ID:
- 516712
- Report Number(s):
- CONF-950629-; ISSN 0889-504X; TRN: IM9738%%21
- Journal Information:
- Journal of Turbomachinery, Vol. 119, Issue 3; Conference: 40. International gas turbine and aeroengine congress and exposition, Houston, TX (United States), 5-8 Jun 1995; Other Information: PBD: Jul 1997
- Country of Publication:
- United States
- Language:
- English
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