Prediction of compressor stall for distorted and undistorted flow by use of a multistage compressor simulation on the digital computer
Abstract
A simulation technique is presented for the prediction of compressor stall for axial-flow compressors for clean and distorted inlet flow. The simulation is implemented on the digital computer and uses stage stacking and lumped-volume gas dynamics. The resulting nonlinear differential equations are linearized about a steady-state operating point, and a Routh-Hurwitz stability test is performed on the linear system matrix. Parallel compressor theory is utilized to extend the technique to the distorted inlet flow problem. The method is applied to the eight-stage J85-13 compressor.
- Publication:
-
Presented at 13th Aerospace Sci. Meeting
- Pub Date:
- 1974
- Bibcode:
- 1974aesc.meet...20D
- Keywords:
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- Axial Flow Turbines;
- Digital Simulation;
- Flow Distortion;
- Gas Flow;
- J-85 Engine;
- Turbocompressors;
- Aerodynamic Stalling;
- Flow Characteristics;
- Flow Equations;
- Performance Prediction;
- Fluid Mechanics and Heat Transfer