Accession Number : ADA251937
Title : A Wide-Range Axial-Flow Compressor Stage Performance Model.
Descriptive Note : Final rept. May 90-Aug 91,
Corporate Author : WRIGHT LAB WRIGHT-PATTERSON AFB OH
Personal Author(s) : Bloch, Gregory S.
Report Date : APR 1992
Pagination or Media Count : 81
Abstract : Dynamic compression system response is a major concern in the operability of aircraft gas turbine engines and computer models have been developed to predict compressor response to changing operating conditions. These models require a knowledge of the steady-stage operating characteristics as inputs, which limits the ability to use them as predicting tools. The full range of dynamic axial flow compressor operation spans forward and reversed flow conditions. A model for predicting the wide flow range characteristics of axial flow compressor stages has been developed and a parametric study of the effect of changing design variables on steady-state performance has been conducted. The model was applied to a 3-stage, low-speed compressor with very favorable results and to a 10-stage, high-speed compressor with mixed results. Conclusions were made regarding the inception of stalling and the effects associated with operating a stage in a multistage environment. It was also conclude that there are operating points of an isolated compressor stage that are not attainable when that stage is operated in a multistage environment. Axial Compressor, Stalling Performance, Aircraft Turbine, Engine, Performance Prediction.
Descriptors : *AXIAL FLOW, *GAS TURBINES, *JET ENGINES, AIRCRAFT, AXIAL FLOW COMPRESSORS, COMPRESSION, COMPRESSORS, COMPUTERS, DYNAMICS, ENGINES, ENVIRONMENTS, FLOW, INPUT, MODELS, OPERATION, PREDICTIONS, RESPONSE, STALLING, STEADY STATE, TURBINES, VARIABLES, VELOCITY.
Subject Categories : Jet and Gas Turbine Engines
Hydraulic and Pneumatic Equipment
Distribution Statement : APPROVED FOR PUBLIC RELEASE