Axial-Flow Compressors, Pumps, and Fans

A new method for predicting performance of multistage axial flow compressors is proposed that utilizes stage performance curves. The method differs from the conventional sequential stage-stacking method in that it employs simultaneous calculation of all interstage variables (temperature, pressure and flow velocity). A consistent functional formulation of governing equations enables this simultaneous calculation. The method is found to be effective, i.e. fast and stable, in obtaining solutions for compressor inlet and outlet boundary conditions encountered in gas turbine analyses. Another advantage of the method is that the effect of changing the angles of movable stator vanes on the compressor's operating behaviour can be simulated easily. Accordingly, the proposed method is very suitable for complicated gas turbine system analysis. This paper presents the methodology and performance estimation results for various multistage compressors employing both fixed and variable vane setting angles. The effect of interstage air bleeding on compressor performance is also demonstrated.

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Axial Flow Compressors

Process Plant Machinery ◽

10.1016/b978-075067081-4/50015-7 ◽

1998 ◽

pp. 475-515

Keyword(s):

Axial Flow ◽

Axial Flow Compressors

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Investigation on a Type of Flow Control to Weaken Unsteady Separated Flows by Unsteady Excitation in Axial Flow Compressors

Volume 5: Turbo Expo 2004, Parts A and B ◽

10.1115/gt2004-53167 ◽

2004 ◽

Cited By ~ 2

Author(s):

Xin-Qian Zheng ◽

Xiao-Bo Zhou ◽

Sheng Zhou

Keyword(s):

Wide Spectrum ◽

Excitation Frequency ◽

Axial Flow ◽

Maximum Velocity ◽

Excitation Amplitude ◽

High Order Scheme ◽

Wide Range ◽

Optimal Excitation ◽

Suction And Blowing ◽

Axial Flow Compressors

By solving unsteady Reynolds-averaged 2-D N-S equations discretized by a high-order scheme, the results showed that the disordered unsteady separated flow could be effectively controlled by periodic suction and blowing in a wide range of incidence, resulting in enhancement of time-averaged aerodynamic performances. The effects of unsteady excitation frequency, amplitude and excitation location were investigated in detail. The effective excitation frequency spans a wide spectrum and there is an optimal excitation frequency that is nearly equal to the Characteristic frequency of vortex shedding. Excitation amplitude exhibits a threshold value (nearly 10% in term of the ratio of maximum velocity of periodic suction and blowing to the velocity of free flow) and an optimal value (nearly 35%). The optimal excitation location is just upstream of the separation point. We also explored feasible unsteady actuators by utilizing upstream wake for constraining unsteady separation in axial flow compressors.

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UNSTEADY STALL OF AXIAL FLOW COMPRESSORS

10.21236/ad0401467 ◽

1963 ◽

Cited By ~ 1

Author(s):

W. G. Brady

Keyword(s):

Axial Flow ◽

Axial Flow Compressors

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Robust stabilization of axial flow compressors with uncertain pressure-flow maps

Proceedings of the 1997 IEEE International Conference on Control Applications ◽

10.1109/cca.1997.627736 ◽

2002 ◽

Cited By ~ 1

Author(s):

A. Leonessa ◽

V.-S. Chellaboina ◽

W.M. Haddad

Keyword(s):

Robust Stabilization ◽

Axial Flow ◽

Pressure Flow ◽

Flow Maps ◽

Axial Flow Compressors

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Mixing in Axial Flow Compressors: Part I — Test Facilities and Measurements in a Four-Stage Compressor

Volume 1: Turbomachinery ◽

10.1115/90-gt-038 ◽

1990 ◽

Author(s):

Y. S. Li ◽

N. A. Cumpsty

Keyword(s):

Axial Flow ◽

Single Stage ◽

Two Dimensional ◽

Similar Magnitude ◽

Low Speed ◽

The Third ◽

Mixing Coefficients ◽

Experimental Facilities ◽

Axial Flow Compressors

The mechanism of mixing in axial flow compressors has been investigated in two low speed machines. For reasons of length this is described in two parts. Results in a 4-stage compressor are described here in Part I and show that the mixing coefficients across the first and the third stators are of similar magnitude. Part I also describes the background and experimental facilities and techniques used in both parts together with the nomenclature and all the references. Part II describes the results from a large single stage compressor. It also presents measurements of mixing in a simple two-dimensional duct, and presents conclusions for the whole investigation.

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