Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
-
Efrén M. Benavides
and
Gregorio L. Juste
Abstract
Recently, a theoretical criterion to calculate the stability of an axial-flow compressor rotor has been presented in the scientific literature. This theoretical criterion was used for determining the locus of the stability line over the rotor map and for predicting the post-stall evolution of the constant-speed line of a rotor. The main objective of this paper is to improve the predictions of such a model. To do that, the paper proposes a different characterization of the characteristic azimuthal length and a calculation of the ratio of specific heats based on a polytropic exponent. Thanks to these new values, the model predicts two bifurcation points in the behaviour of the flow: the inception point of the instability and the surge point. Experimental data from a pure axial compressor are used to validate the model showing that the prediction of the flow coefficient at the surge point has an error inferior to 5%. The paper presents a discussion about how the model can explain the different behaviours exhibited by the same rotor when the flow coefficient is reduced.
©[2012] by Walter de Gruyter Berlin Boston
Articles in the same Issue
- Masthead
- Flow Field around a Blunt-nosed Body with Spike
- The Flow Analysis and Performance Improvement of the Flow Return System in High Pressure Fans
- Numerical Investigation of Heat Transfer Characteristic on Scalelike Platelet Inner Duct
- Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
- Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums
- Numerical Simulation of Tangling in Jet Engine Turbines
- Statistical Turbofan Architecture Management for Use in a Supercirculation Wing Aircraft
- Calculating High Speed Centrifugal Compressor Performance from Averaged Measurements
- Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
- An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor
Articles in the same Issue
- Masthead
- Flow Field around a Blunt-nosed Body with Spike
- The Flow Analysis and Performance Improvement of the Flow Return System in High Pressure Fans
- Numerical Investigation of Heat Transfer Characteristic on Scalelike Platelet Inner Duct
- Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
- Fatigue Life Estimation of an Aircaft Engine Under Different Load Spectrums
- Numerical Simulation of Tangling in Jet Engine Turbines
- Statistical Turbofan Architecture Management for Use in a Supercirculation Wing Aircraft
- Calculating High Speed Centrifugal Compressor Performance from Averaged Measurements
- Preliminary Experimental Investigation on Detonation Initiation in the Ejector of a Pulse Detonation Rocket Engine
- An Application of Fuzzy Fault Tree Analysis to Uncontained Events of an Areo-Engine Rotor
