Aerodynamic performance of a high-turning compressor stator with flow control

Carter, C.; Guillot, Stephen; Ng, W. F.; Copenhaver, William W.

doi:10.2514/6.2001-3973

Cited by 23 publications

(11 citation statements)

References 2 publications

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“…The results indicated that a highly adverse pressure gradient took place in compressor cascades with large turning angles, which induced severe flow separations, and accordingly induced rapid loss augmentation and decrease of stage pressure ratio. Carter et al [3] tested the rectangular compressor cascade with a 69u camber angle, and the experimental results demonstrated that the compressor cascade with large turning angles had the characteristics of strong 3D separations and high aerodynamic losses. As an effective way to restrain flow separations near the end-walls by controlling the 3D flow and to enhance efficiency and pressure ratio, bowed compressor blades have been widely recognized by researchers from many countries.…”

Section: Introductionmentioning

confidence: 97%

Aerodynamic performance of bowed compressor cascades with different camber angles

Chen

Wang

et al. 2008

Front. Energy Power Eng. China

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The effects of a positively bowed blade on the aerodynamic performance of annular compressor cascades with different camber angles were experimentally investigated. The distributions of the exit total pressure loss and secondary flow vectors of the compressor cascades were analyzed. The static pressure was measured by tapping on the cascade surfaces, and the ink-trace flow visualizations were conducted. The results show that the value of the optimum bowed angle and optimum bowed height decrease because of the increased losses at the midspan with the increase of the camber angle. The C-shape static pressure distribution along the radial direction exists on the suction surface of the straight cascade with larger camber angles. When bowed blade is applied, the larger bowed angle and larger bowed height will further enhance the accumulation of the low-energy fluid at the mid-span, thus causing the flow behavior to deteriorate. Under 60u camber angle, flow behavior near the end-wall region of some bowed cascades even deteriorates instead of improving because the blockage of the separated flow near the mid-span keeps the low-energy fluid near the endwalls from moving towards the mid-span region. As a result, a rapid augmentation of the total loss can easily take place under a large bowed angle.

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Section: Introductionmentioning

confidence: 97%

Aerodynamic performance of bowed compressor cascades with different camber angles

Chen

Wang

et al. 2008

Front. Energy Power Eng. China

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“…Then they designed a two-stage counter-rotating fan with a pressure ratio of 3 and adiabatic efficiency of 89% by employing suction on the second rotor blades extended from the hub to 80% span, and the test attained an overall polytropic efficiency better than 90% [10]. Carter designed and tested a compressor stator with boundary layer suction and blowing, and a reduction of 65% of loss coefficient was achieved when blowing mass flow rate was 1.6% of the passage throughflow [11]. Dang designed aspirated compressor blades using 3D inverse method, and found a minimum of sucked flow that required for a performance improvement at design and off-design operations [12].…”

Section: Introductionmentioning

confidence: 99%

“…Flow control techniques used in fan/compressor have also attained great success. However, the generally employed methods in fan/compressor flow control were blowing only or suction only method, the method of combined blowing and suction flow control technique rarely applied to boundary layer control in fan/compressor [11].…”

Section: Introductionmentioning

confidence: 99%

Boundary layer separation control on a highly-loaded, low-solidity compressor cascade

Zhou¹,

Liu²,

Zou³

et al. 2010

J. Therm. Sci.

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Separated flow can be effectively controlled through the management of blade boundary layer development. Numerical simulations on a highly-loaded, low-solidity compressor cascade indicate that combined blowing and suction flow control technique can significantly improve cascade performance, especially in increasing the cascade loading and static pressure ratio as well as decreasing the loss coefficient. Meanwhile, it is more effective to improve cascade performance by blowing near leading edge on suction surface than suction near trailing edge.Both the locations and flow rates of blowing and suction are major impact factors of this method to cascade performance. Comparing to the baseline, the static pressure ratio increases by 15% and loss coefficient decreases by 80%, with a blowing fraction of 1.7% and a suction fraction of 1.38% of the inlet mass flow.

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“…[1][2][3][4] It has the potential to open the design envelope for axial compressors to higher loading levels. This translates into higher overall pressure ratios for reduced thrust specific fuel consumption (TSFC).…”

Section: Introductionmentioning

confidence: 99%

Fluid Mechanics of Compression System Flow Control

Car¹,

Puterbaugh²

2005

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information AFRL-PR-WP-TM-2006-2003 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTARY NOTESReport contains color.Prepared for AFOSR Annual Program Review. ABSTRACTThe aim of Fluid Mechanics of Compression System Flow Control is to increase the diffusion capacity of an axial compressor stator through the application of bladesurface-mounted flow control. The experimental portion of the work employs a small wind tunnel that allows the investigation of flow control concepts applied to a simulated single stator passage. Baseline results are presented along with those of three flow control modules; all are variations of blowing (no aspiration) flow control using a planar jet behind a backward facing step positioned upstream of the passage curvature. Two preliminary investigations are presented. The first includes the effect of the thickness of the lip separating the main stream from the core stream of the backward facing step and its impact on the flow control effectiveness. The second introduces streamwise vorticity via flat plate vortex generators as a means of enhancing the interaction between the blowing jet and the core stream. AbstractThe aim of Fluid Mechanics of Compression System Flow Control is to increase the diffusion capacity of an axial compressor stator through the application of bladesurface-mounted flow control. The experimental portion of the work employs a small wind tunnel that allows the investigation of flow control concepts applied to a simulated single stator passage. Baseline results are presented along with those of three flow control modules; all are variations of blowing (no aspiration) flow control using a planar jet behind a backward facing step positioned upstream of the passage curvature. Two preliminary investigations are presented. The first includes the effect of the thickness of the lip separating the main stream from the core stream of the backward facing step and its impact on the flow control effectiveness. The second introduces streamwise vorticity via flat plate vortex generators as a means of enhancing the interaction between the blowing jet and the core stream.

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Aerodynamic performance of a high-turning compressor stator with flow control

Cited by 23 publications

References 2 publications

Aerodynamic performance of bowed compressor cascades with different camber angles

Aerodynamic performance of bowed compressor cascades with different camber angles

Boundary layer separation control on a highly-loaded, low-solidity compressor cascade

Fluid Mechanics of Compression System Flow Control

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