Investigation on the influence of the structure parameters of blade tip recess on the performance of axial flow compressor

Abstract

As one of the important components of an aero engine, the compressor plays an important role in improving the performance of the aero engine. The blade tip recess (BTR) has great potential and advantages in improving the performance of the compressor. It is very important to clarify the influence of the structure parameters of the BTR on the performance of the compressor. In this study, the two-dimensional results of the BTR were analyzed by using the method of variance analysis, and the two-dimensional calculation results of the BTR were used to guide the design of the BTR of axial flow compressor rotor. In the NASA Rotor 35, the influence rules of the structure parameters of BTR on the recess effect that was basically the same as the two-dimensional conditions. The optimization of the rotor BTR structure parameters may be achieved by the two-dimensional calculation. The flow field analysis showed the BTR can retard the growth rate of the blockage area of the leading edge of blade tip by weakening the tip clearance leakage flow intensity that delayed the occurrence of blade tip blockage and improved the aerodynamic stability of the rotor.

Keywords

Axial flow compressor analysis of variance blade tip recess performance aerodynamic stability

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References

Hoying

Tan

, et al. Role of blade passage flow structurs in axial compressor rotating stall inception[J]. Journal of Turbomachinery 1998; 121(4): 735–742.

Davis

Yao

. Axial compressor rotor flow structure at stall-inception. In: 44th AIAA Aerospace sciences meeting, Reno, Nevada, 09–12 January 2006, 4881–4891, 24(7). American Institute of Aeronautics and Astronautics.

Hembera

Danner

Kau

. Development of circumferential grooves for axial compressors based on flow mechanisms. In: 44th AIAA/ASME/SAE/ASEE joint propulsion conference and exhibit, Hartford,CT, 21–23 July 2008, GT2008-4998.

Bailey

Voit

. Some observations of effects of porous casings on operating range of single stage axial-flow compressor rotor. NASA TM X-2120.

Takata

Tsukuda

Stall margin improvement by casing treatments – its mechanisms and effectiveness. J Eng Power 1977; 99(1): 121–133.

Bailey

. Effect of grooved casing treatment on the flow range capability of a single-stage axial-flow compressor. NASA TM X-2459.

Osborn

Lewis

. Effect of several porous casing treatments on stall limit and overall performance of an axial-flow compressor rotor. NASA TN D-6537.

Moore

, and Kovich

. Effect of casing treatment on overall and blade-element performance of a compressor rotor. NASA TN D-6538.

Fujita

Takata

. A study on configurations of casing treatment for axial flow compressors. JSME 1984; 27(230): 1675–1681.

10.

Prince

Wisler

Hilvers

. Study of casing treatment stall margin improvement. NASA CR-134552.

11.

Rabe

Hah

. Application of casing circumferential grooves for improved stall margin in a transonic axial compressor. ASME Paper GT -2002-30641.

12.

Nezym

. Development of new casing treatment configuration. JSME Int J Ser B 2004; 47(4): 804–812.

13.

Wilke

Kau

. A numerical investigation of the influence of casing treatments on the tip leakage flow in a HPC front stage. In: Proceedings of the ASME turbo expo 2002: power for land, sea, and air. Volume 5: turbo expo 2002, parts A and B, Amsterdam, The Netherlands, June 3–6, 2002, pp. 1155–1165. ASME Paper GT-2002-30642.

14.

Ameri

Steinthorsson

Rigby

. Effect of squealer tip on rotor heat transfer and efficiency. J Turbomach 199; 120(4): 753–759.

15.

Azad

Han

J-C

Boyle

. Heat transfer and flow on the squealer tip of a gas turbine blade. J Turbomach 2000; 122(4): 725–732.

16.

Key

Arts

. Comparison of turbine tip leakage flow for flat tip and squealer tip geometries at high-speed conditions. J Turbomach 2006; 128(2): 213–220.

17.

Mischo

Behr

Abhari

. Flow physics and profiling of recessed blade tips: impact on performance and heat load. J Turbomach 2008; 130(2): 021008.

18.

Mischo

Burdet

Abhari

. Influence of stator–rotor interaction on the aerothermal performance of recess blade tips. J Turbomach 2011; 133(1): 011023.

19.

Sijal

Jehanzeb

. Effect of casing recess and tip clearance on the efficiency of high-pressure turbine stage with contoured endwall NGV[C]. In: 47th AIAA aerospace sciences meeting including the new horizons forum & aerospace exposition, Orlando, Florida, 05–08 January 2009.

20.

Dunn

Haldeman

. Time-Averaged heat flux for a recessed tip, lip, and platform of a transonic turbine Blade. J Turbomach 2000; 122(4): 692.

21.

Gourdain

Leboeuf

. Unsteady simulation of an axial compressor stage with casing and blade passive treatment. J Turbomach 2009; 131(2): 1–12.

22.

Khan

Mushtaq

Parvez

, et al. Studying the performance of transonic axial flow compressor by implementing circumferential grooves, tip recess and tip injection[C]. In: 50th Aerospace sciences meeting including the new horizons forum and aerospace exposition, Nashville, Tennessee, 09–12 January 2012.

23.

Jung

Y-J

Jeon

Jung

, et al. Effects of recessed blade tips on stall margin in a transonic axial compressor. Aerospace Sci Tech 2016; 54: 41–48.

24.

Jung

Moore

. Design and overall performance of four highly-loaded, high speed inlet stages for an advanced high-pressure ratio core compressor, NASA Technical Paper, TP-1337, 1978.