Modeling for control of rotating stall in high-speed multistage axial compressors

Journal Article · Mon Jan 01 04:00:00 EST 1996 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.2836601· OSTI ID:194213

Feulner, M R; Hendricks, G J ^[1]; Paduano, J D ^[2]

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1. United Technologies Research Center, East Hartford, CT (United States)
2. Massachusetts Inst. of Tech., Cambridge, MA (United States). Dept. of Aeronautics and Astronautics

Using a two-dimensional compressible flow representation of axial compressor dynamics, a control-theoretic input-output model is derived, which is of general utility in rotating stall/surge active control studies. The derivation presented here begins with a review of the fluid dynamic model, which is a two-dimensional stage stacking technique that accounts for blade row pressure rise, loss, and deviation as well as blade row and interblade row compressible flow. This model is extended to include the effects of the upstream and downstream geometry and boundary conditions, and then manipulated into a transfer function form that dynamically relates actuator motion to sensor measurements. Key relationships in this input-output form are then approximated using rational polynomials. Further manipulation yields an approximate model in standard form for studying active control of rotating stall and surge. As an example of high current relevance, the transfer function from an array of jet actuators to an array of static pressure sensors is derived. Numerical examples are also presented, including a demonstration of the importance of proper choice of sensor and actuator locations, as well as a comparison between sensor types. Under a variety of conditions, it was found that sensor locations near the front of the compressor or in the downstream gap are consistently the best choices, based on a quadratic optimization criterion and a specific three-stage compressor model. The modeling and evaluation procedures presented here are a first step toward a rigorous approach to the design of active control systems for high-speed axial compressors.

• Sponsoring Organization: USDOE
• OSTI ID: 194213
• Report Number(s): CONF-940626--
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 1 Vol. 118; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

42 ENGINEERING
COMPRESSIBLE FLOW
CONTROL
GAS COMPRESSORS
LAPLACE EQUATION
MATHEMATICAL MODELS