Observatorio de I+D+i UPM

Memorias de investigación
Research Publications in journals:
Analytical Calculation of Stall-inception and Surge Points for an Axial-flow Compressor Rotor
Year:2012
Research Areas
  • Mechanical aeronautics and naval engineering
Information
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%. For the rotor studied, the paper provides a quantitative and qualitative description of the inception of the instability and of the mechanism involved in the instable region of the compressor map. The paper also discusses the role of rotor efficiency in the position of the bifurcations and gives a sensitivity analysis of its position. Finally, it presents a discussion about how the model can explain the different behaviours exhibited by the same rotor when the flow coefficient is reduced.
International
Si
JCR
No
Title
International Journal of Turbo and Jet Engines
ISBN
0334-0082
Impact factor JCR
0,025
Impact info
Volume
Journal number
From page
1
To page
32
Month
SIN MES
Ranking
Participants
  • Autor: Efren Moreno Benavides (UPM)
Research Group, Departaments and Institutes related
  • Creador: Grupo de Investigación: Ciencias y Operaciones Aeroespaciales
  • Departamento: Motopropulsión y Termofluidodinámica
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