Influence of compressor exit conditions on combustor annular diffusers part II: Flow redistribution

Journal of Propulsion and Power

Volumn 17, Issue 3, 2001, Pages 687-694

  Barker, A G ^a   Carrotte, J F ^a  

^a LOUGHBOROUGH UNIVERSITY   (United Kingdom)

Author keywords

[No Author keywords available]

Indexed keywords

AXIAL FLOW; BOUNDARY LAYER FLOW; COMBUSTORS; COMPRESSORS; DIFFUSERS (FLUID); ROTORS; TURBOMACHINE BLADES;

DOWNSTREAM COMBUSTORS; OUTLET GUIDE VANES (OGV);

GAS TURBINES;

EID: 0035331570     PISSN: 07484658     EISSN: 15333876     Source Type: Journal    
DOI: 10.2514/2.5796     Document Type: Article

References (11)

1. Spanwise mixing in axial flow turbomachines
2. Spanwise mixing in multistage axial flow compressors Part I: Experimental investigation
3. Secondary flow, turbulent diffusion, and mixing in axial flow compressors
4. Mixing in axial-flow compressors: Conclusions drawn from 3-D Navier-Stokes analyses and experiments
5. The development of a large annular facility for testing gas turbine combustor diffuser systems
6. Performance of annular combustor-dump diffusers
7. Experimentally determined optimum geometries for rectilinear diffusers with rectangular, conical or annular cross-section
8. The influence of inlet conditions on the performance of two annular diffusers
9. Characteristics of combustor diffusers
10. Detailed measurements on a modern combustor dump diffuser system