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Research Papers: Flows in Complex Systems

An Evaluation Approach for the Stall Margin Enhancement With Stall Precursor-Suppressed Casing Treatment

[+] Author and Article Information
Dakun Sun

School of Energy and Power Engineering;Co-Innovation Center for Advanced Aero-Engine,
Beihang University,
No. 37 Xueyuan Road,
Haidian District,
Beijing 100191, China
e-mail: sundk@buaa.edu.cn

Xiaohua Liu

Engine Certification Center,
Civil Aviation Administration of China,
No. 3 Huajiadi East Road,
Chaoyang District,
Beijing 100102, China
e-mail: liuxh@buaa.edu.cn

Xiaofeng Sun

School of Energy and Power Engineering;Co-Innovation Center for Advanced Aero-Engine,
Beihang University,
No. 37 Xueyuan Road,
Haidian District,
Beijing 100191, China
e-mail: sunxf@buaa.edu.cn

1Corresponding author.

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received October 4, 2014; final manuscript received February 26, 2015; published online April 28, 2015. Assoc. Editor: Frank C. Visser.

J. Fluids Eng 137(8), 081102 (Aug 01, 2015) (16 pages) Paper No: FE-14-1553; doi: 10.1115/1.4030017 History: Received October 04, 2014; Revised February 26, 2015; Online April 28, 2015

It is known that a kind of stall precursor-suppressed (SPS) casing treatment can be used to enhance compressor stall margin (SM) without recognizable efficiency loss. The further requirement in this regard is to develop an effective way to determine the variation range of the SM improvement during the design of such SPS casing treatment. In this investigation, based on the extrapolation hypothesis and the existing work, an extended stall inception model for quantitative evaluation of the SM enhancement is presented for both subsonic and transonic compressors with the SPS casing treatment. The capability of the extended model to quantitatively evaluate the SM enhancement with the SPS casing treatment is validated against the experimental data. The quantitative evaluation results show that the SPS casing treatments with different geometric parameters can improve the SM by a diverse percentage. In particular, for the facilities used in the present investigation, the experiments show that the SPS casing treatments can cause relevant increases of the SM. The change trend of the SM enhancement with various design parameters of the SPS casing treatment is in line with the corresponding theoretical results.

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References

Figures

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Fig. 1

Road map for the SPS casing treatment design

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Fig. 2

Sketch of vortex and pressure wave interaction in the SPS casing treatment

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Fig. 3

Extension of compressor operating range via casing treatment

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Fig. 4

Experimental results of the SPS casing treatment on compressor stability: (a) transonic compressor J69 and (b) subsonic fan TA36

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Fig. 5

Characteristics of aerodynamic parameters in average flow field at inlet/outlet of cascade: (a) inlet meridional velocity and (b) outlet static pressure

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Fig. 6

Characteristics of aerodynamic parameters in average flow field across cascade: (a) total pressure loss and (b) deviation condition of flow angle

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Fig. 7

Sketch map of a compressor stage unwrapped in the circumferential direction

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Fig. 8

Sketch map of a transonic compressor rotor with SPS casing treatment unwrapped in circumferential direction

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Fig. 9

Total pressure loss of subsonic fan TA36 stage: (a) rotor blade row and (b) stator blade row

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Fig. 10

Effect of open area ratio on stability of TA36 at design rotational speed: (a) DF and (b) RS

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Fig. 11

Effect of height of backchamber hb on stability of TA36 at design rotational speed: (a) DF and (b) RS

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Fig. 12

Effect of length of backchamber lb on stability of TA36 at design rotational speed: (a) DF and (b) RS

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Fig. 13

Effect of Mach number of bias flow Mab on stability of TA36 at design rotational speed: (a) DF and (b) RS

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Fig. 14

Effect of Mach number of bias flow Mab on stability of TA36 at design rotational speed: (a) DF and (b) RS (continued)

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Fig. 15

Effect of Mach number of bias flow Mab on stability of TA36 at design rotational speed: (a) DF and (b) RS (continued)

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Fig. 16

Characteristics of aerodynamic parameters on J69 Rotor at inlet/outlet of cascade: (a) static pressure and (b) meridional velocity

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Fig. 17

Characteristics of aerodynamic parameters on J69 Rotor in cascade passage: (a) static pressure and (b) meridional velocity

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Fig. 18

Characteristics of aerodynamic parameters on J69 Rotor: (a) flow angle at inlet/outlet of cascade and (b) total pressure loss and deviation condition of flow angle

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Fig. 19

Effect of length of backchamber lb on stability of J69 Rotor at design rotational speed: (a) DF and (b) RS

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Fig. 20

Effect of Mach number of bias flow Mab on stability of J69 Rotor at design rotational speed: (a) DF and (b) RS

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Fig. 21

Effect of height of backchamber hb on stability of J69 Rotor at design rotational speed, σ = 6%: (a) DF and (b) RS

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Fig. 22

Effect of height of backchamber hb on stability of J69 Rotor at design rotational speed, σ = 8%: (a) DF and (b) RS

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Fig. 23

Effect of height of backchamber hb on stability of J69 Rotor at design rotational speed, σ = 12%: (a) DF and (b) RS

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Fig. 24

Effect of height of backchamber hb on stability of J69 Rotor at design rotational speed, σ = 12%: (a) DF and (b) RS

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Fig. 25

Effect of combined parameters on stability of J69 Rotor at design rotational speed: (a) DF and (b) RS

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