Effect of stator design on stator boundary layer flow in a highly loaded single-stage axial-flow low-speed compressor

Journal of Turbomachinery

Volumn 123, Issue 3, 2001, Pages 483-489

  Friedrichs, J ^a   Baumgarten, S ^a   Kosyna, G ^a   Stark, U ^a  

^a TECHNICAL UNIVERSITY OF BRAUNSCHWEIG   (Germany)

Author keywords

[No Author keywords available]

Indexed keywords

AERODYNAMICS; BOUNDARY LAYER FLOW; COMPRESSORS; MACHINE DESIGN; STATORS; TURBOMACHINE BLADES;

STATOR HUB;

AXIAL FLOW TURBOMACHINERY;

AXIAL FLOW COMPRESSOR; BLADE AERODYNAMICS; BOUNDARY LAYER; DESIGN; SINGLE STAGE PUMP; STATOR;

EID: 0035389279     PISSN: 0889504X     EISSN: None     Source Type: Journal    
DOI: 10.1115/1.1370168     Document Type: Article

References (14)

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2. A simple method for calculating the span and chordwise loading on straight and swept wings of any given aspect ratio at subsonic speeds
3. Investigation on axial flow fan impellers with forward swept blades
4. Stator endwall leading-edge sweep and hub shroud influence on compressor performance
5. A three-dimensional model for the prediction of shock losses in compressor blade rows
6. Inner workings of aerodynamic sweep
7. Control of shock structure and secondary flow field inside transonic compressor rotors through aerodynamic sweep
8. Three-Dimensional relief in turbomachinery blading
9. Effect of stator design on stator hub boundary layer separation in a highly loaded single-stage axial-flow low-speed compressor
10. Die Berechnung der Druckverteilung an dicken Gitterprofilen mit Hilfe von Fredholmschen Integralgleichungen zweiter Art
11. Topology of three-dimensional separated flows
12. Sweep and dihedral effects in axial-flow turbomachinery
13. Comparison of sweep and dihedral effects on compressor cascade performance