Accession Number : ADP005512
Title : Influence of Shock and Boundary-Layer Losses on the Performance of Highly Loaded Supersonic Axial Flow Compressors,
Corporate Author : OFFICE OF THE PROJECT MANAGER FOR TRAINING DEVICES FORT EUSTIS VA FIELD OFFICE*
Personal Author(s) : Broichhausen,K.D. ; Gallus,H. E.
Report Date : MAR 1987
Pagination or Media Count : 14
Abstract : Performance and losses of trans/supersonic axial flow compressors are influenced by shock structure, shock-boundary layer interactions and boundary layer separation. The combination of these phenomena and their effects on the flow characteristics of supersonic compressors are discussed in the presented contribution. For this purpose experimental results are compared with theoretical approaches involving different semi-empirical correlations for shock and boundary layer losses, for separation and flow deviation. By an appropriate combination of these models the flow characteristics of supersonic compressors are interpreted and the performance of such compressors is successfully reproduced in a wide range. Finally, generally valuable statements on the design of highly loaded supersonic compressors are derived and possible perspectives are described.
Descriptors : *AXIAL FLOW COMPRESSORS, *SUPERSONIC CHARACTERISTICS, *GAS TURBINES, BOUNDARY LAYER TRANSITION, SHOCK WAVES, BOUNDARY LAYER FLOW, WEST GERMANY
Subject Categories : Fluid Mechanics
Hydraulic and Pneumatic Equipment
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE