The effect of variable stator on performance of a highly loaded tandem axial flow compressor stage

A computational method for secondary flows in a compressor has been extended to treat stalled flows. An integral equation is used which simulates the inviscid flow at the wall, under the viscous flow influence. We present comparisons with experimental results for a 2D stalled boundary layer, and for the secondary flow in a highly loaded stator of an axial flow compressor.

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Some Blade Designs for an Axial Flow Compressor Stage

Journal of the Royal Aeronautical Society ◽

10.1017/s0368393100098138 ◽

1954 ◽

Vol 58 (517) ◽

pp. 61-64

Author(s):

R. G. Taylor

Keyword(s):

Mach Number ◽

Axial Flow ◽

Compressor Stage ◽

Axial Flow Compressor ◽

Design Specifications ◽

Reaction Condition ◽

Forced Vortex ◽

Vortex Solutions ◽

Flow Compressor ◽

Constant Mach Number

Two design conditions for an axial flow compressor stage are proposed and examined. These are, the constant reaction condition (incorporating I “ radial equilibrium ”), and the condition that the Mach number at inlet to the rotor shall be invariant with radius. In addition, the combination of these two properties in one stage is considered. It is found, with further assumptions regarding the nature of the flow, that a forced vortex type of flow will satisfy both design specifications. The forced vortex solutions for the various cases are presented, and for constant Mach number at inlet to the rotor, more general solutions are given.

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Design and test of a highly-loaded three-stage, axial-flow compressor

10.2514/6.1976-6 ◽

1976 ◽

Cited By ~ 1

Author(s):

R. COOK

Keyword(s):

Axial Flow ◽

Axial Flow Compressor ◽

Flow Compressor ◽

Highly Loaded

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Effects of Endwall Profiling on Axial Flow Compressor Stage

Volume 7: Turbomachinery, Parts A and B ◽

10.1115/gt2009-59418 ◽

2009 ◽

Cited By ~ 4

Author(s):

Jialing Lu ◽

Wuli Chu ◽

Yanhui Wu

Keyword(s):

Flow Field ◽

Engineering Design ◽

Axial Flow ◽

Design Tool ◽

Operating Conditions ◽

Compressor Stage ◽

Corner Separation ◽

Axial Flow Compressor ◽

Flow Compressor ◽

Stage Efficiency

In recent years endwall profiling has been well validated as a major new engineering design tool for the reduction of secondary loss in turbines. However, its application on compressors have been rarely performed and reported. This paper documents the findings of the analysis for diminishing compressor stator corner separation using endwall profiling; In the study, novel profiled endwalls were designed and numerically studied on a subsonic axial-flow compressor stage. The compressor stator endwalls were profiled on both axial and azimuthal directions. The results showed, the stator corner separation was significantly suppressed under all the operating conditions by implementing this profiled endwall. Significant improvements on stage pressure ratios and stage efficiency were observed. Detailed flow field changes, as well as endwall profiling methods are provided in the paper, so that the results of this research can be referenced to other compressor designs.

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Experimental Investigation on the Effect of Porosity of Bend Skewed Casing Treatment on a Single Stage Transonic Axial Flow Compressor

Volume 2A: Turbomachinery ◽

10.1115/gt2014-26102 ◽

2014 ◽

Cited By ~ 1

Author(s):

Dilipkumar B. Alone ◽

Subramani Satish Kumar ◽

Shobhavathy Thimmaiah ◽

Janaki Rami Reddy Mudipalli ◽

A. M. Pradeep ◽

...

Keyword(s):

Experimental Investigation ◽

Axial Flow ◽

Compressor Stage ◽

Casing Treatment ◽

Operating Range ◽

Axial Flow Compressor ◽

Transonic Compressor ◽

Stable Operating ◽

Flow Compressor ◽

Casing Treatments

A bend skewed casing treatment was designed, to study the influence of one of its geometrical parameter porosity on the stable performance of single stage transonic axial flow compressor. The compressor was designed for the stage total-to-total pressure ratio of 1.35, corrected mass flow rate of 22 kg/s at corrected design speed of 12930 RPM. Bend skewed casing treatment has an axial inlet segment till 50% of the total length and rear segment that is skewed by 45° in the direction of the rotor tip section stagger. Both the sections were oriented at a skew angle of 45° to the radial plane such that the flow exiting the slot is in counter-clockwise direction to that of the rotor direction. The casing treatment slot width was equal to the maximum thickness of the rotor blades. Three casing treatment configurations were identified for the current experimental investigation. All the treatment geometries considered for the experimental research have lower porosities than reported in the open literatures. The effect of the porosity parameter on the performance of transonic compressor stage was evaluated at two axial coverages of 20% and 40% relative to the rotor tip axial chord. Performance maps were obtained for the solid casing and casing treatment with three different porosities. Comparative studies were carried out and experimental results showed a maximum of 65% improvement in the stable operating range of the compressor for one of the treatment configurations. It was also observed that the stable operating range of the compressor increases with an increase in the casing treatment porosity. All the casing treatment configurations showed that the compressor stall occurs at lower mass flows as compared to the solid casing. Compressor stage peak efficiency shows significant degradations with increase in the porosity as compared to solid casing. Detailed blade element performances were also obtained using calibrated multi-hole aerodynamic probe. Comparative variations of flow parameters like absolute flow angle, Mach number were studied at full flow and near stall conditions for the solid casing and casing treatment configurations. Hot wire measurements show very high fluctuation in the inlet axial velocity in the presence of solid casing as compared to casing treatments. Experimental investigation revealed that the porosity of the casing treatments has strong influence on the transonic compressor stage performance.

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