Analysis of instability inception in high-speed multistage axial-flow compressors

Journal Article · Wed Oct 01 04:00:00 EDT 1997 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2841181· OSTI ID:563926

Hendricks, G J; Sabnis, J S; Feulner, M R ^[1]

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1. United Technologies Research Center, East Hartford, CT (United States)

A nonlinear, two-dimensional, compressible dynamic model has been developed to study rotating stall/surge inception and development in high-speed, multistage, axial flow compressors. The flow dynamics are represented by the unsteady Euler equations, solved in each interblade row gap and inlet and exit ducts as two-dimensional domains, and in each blade passage as a one-dimensional domain. The resulting equations are solved on a computational grid. The boundary conditions between domains are represented by ideal turning coupled with empirical loss and deviation correlations. Results are presented comparing model simulations to instability inception data of an eleven stage, high-pressure-ratio compressor operating at both part and full power, and the results analyzed in the context of a linear modal analysis.

• Sponsoring Organization: USDOE
• OSTI ID: 563926
• Report Number(s): CONF-960608--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 4 Vol. 119; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
COMPRESSOR BLADES
GAS COMPRESSORS
GAS TURBINE ENGINES
INSTABILITY
MATHEMATICAL MODELS
MESH GENERATION