Three-dimensional flow phenomena in a transonic, high-throughflow, axial-flow compressor stage

Journal Article · Thu Apr 01 00:00:00 EST 1993 · Journal of Turbomachinery; (United States)

DOI:https://doi.org/10.1115/1.2929228· OSTI ID:6474386

Copenhaver, W W; Puterbaugh, S L ^[1]; Hah, C ^[2]

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1. Wright Lab., Wright-Patterson AFB, OH (United States)
2. NASA Lewis Research Center, Cleveland, OH (United States)

A detailed aerodynamic study of a transonic, high-throughflow, single-stage compressor is presented. The compressor stage was comprised of a low-aspect-ratio rotor combined alternately with two different stator designs. Both experimental and numerical studies are conducted to understand the details of the complex flow field present in this stage. Aerodynamic measurements using high-frequency, Kulite pressure transducers and conventional probes are compared with results from a three-dimensional viscous flow analysis. A steady multiple blade row approach is used in the numerical technique to examine the detailed flow structure inside the rotor and the stator passages. The comparisons indicate that many flow field features are correctly captured by viscous flow analysis, and therefore unmeasured phenomena can be studied with some level of confidence.

• OSTI ID: 6474386
• Journal Information: Journal of Turbomachinery; (United States), Vol. 115:2; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPRESSOR BLADES
AERODYNAMICS
DESIGN
AIRCRAFT
AIRCRAFT COMPONENTS
ASPECT RATIO
COMPRESSORS
EXPERIMENTAL DATA
NUMERICAL ANALYSIS
TRANSONIC FLOW
TURBOMACHINERY
DATA
EQUIPMENT
FLUID FLOW
FLUID MECHANICS
INFORMATION
MACHINERY
MATHEMATICS
MECHANICS
NUMERICAL DATA
330103* - Internal Combustion Engines- Turbine