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Research Papers: Flows in Complex Systems

Modeling the Effect of Stability Bleed on Back-Pressure in Mixed-Compression Supersonic Inlets

[+] Author and Article Information
Lv Yongzhao

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Collaborative Innovation
Center of Advanced Aero-Engine,
School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road,
Haidian District, Beijing 100191, China
e-mail: lvjiuhui@163.com

Li Qiushi

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Collaborative Innovation
Center of Advanced Aero-Engine,
School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road,
Haidian District, Beijing 100191, China
e-mail: liqs@buaa.edu.cn

Li Shaobin

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Collaborative Innovation
Center of Advanced Aero-Engine,
School of Energy and Power Engineering,
Beihang University,
37 Xueyuan Road,
Haidian District, Beijing 100191, China
e-mail: lee_shaobin@buaa.edu.cn

Contributed by the Fluids Engineering Division of ASME for publication in the JOURNAL OF FLUIDS ENGINEERING. Manuscript received August 18, 2014; final manuscript received June 4, 2015; published online August 4, 2015. Assoc. Editor: Samuel Paolucci.

J. Fluids Eng 137(12), 121101 (Aug 04, 2015) Paper No: FE-14-1456; doi: 10.1115/1.4030811 History: Received August 18, 2014

To stabilize the terminal normal shock on high-static pressure at outlet, called back-pressure pout, stability bleed slots are used in the throat of mixed-compression supersonic inlets. In this paper, a model for the functional relation between the bleed flow rate mbl and back-pressure pout is established based on a bleed flow rate model (BFRM) in order to study the effect of stability bleed on the back-pressure in mixed-compression supersonic inlets. Given the inlet flow parameters Min, pin*, and Tin*, the plenum pressure ppl at slots' outlet, the terminal normal shock position xs in this model, the bleed flow rate mbl, Mach number M¯out, and back-pressure pout were derived one by one from the basic laws of conservation. To study the effect of plenum pressure ppl on subsonic flow of the divergent section behind the terminal normal shock, a correction coefficient κ is introduced to modify the Mach number M¯out. Furthermore, numerical simulations based on Reynolds-Averaged Navier–Stokes equations were performed to analyze the functional relation between the bleed flow rate mbl and back-pressure pout. Computational fluid dynamics (CFD) results show that the present model agrees with the data.

Copyright © 2015 by ASME
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References

Figures

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Fig. 1

Axisymmetric mixed-compression inlet

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Fig. 3

Flow field characteristics through the bleed slot

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Fig. 4

Schematic of the specified shock positions: (a) xs =  xs2 and (b) xs =  xs1

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Fig. 5

Schematic of the simplified expansion wave

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Fig. 6

Schematic of the flow characteristics of the divergent nozzle: (a) xs2<xs<xs3, (b) xs1<xs<xs2, and (c) 0<xs<xs1

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Fig. 7

Flow field characteristics through the bleed slot: (a) case (A) and (b) case (B)

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Fig. 8

Validation model (m)

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Fig. 9

Generated mesh near the bleed slot for numerical solution

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Fig. 10

Normalized pressure distribution

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Fig. 11

Mesh independence verification: (a) bleed flow rate and (b) terminal normal shock position

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Fig. 12

Flow domain and Mach number contours (Case 2:M=1.6,ppl=18,000 Pa,pout/pin*=0.72)

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Fig. 13

Distribution of the Maher number: (a) x/xs3=0.6 and (b) x/xs3=2.8

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Fig. 14

Distribution of the deflection angle: (a) x/xs3=0.6 and (b) x/xs3=2.8

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Fig. 15

Comparison of the back-pressure at the outlet (case 1): (a) ppl = 22,000 Pa, (b) ppl = 18,000 Pa, (c) ppl = 14,000 Pa, and (d) ppl = 10,000 Pa

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Fig. 16

Comparison of the back-pressure at the outlet (case 2): (a) ppl = 18,000 Pa, (b) ppl = 14,000 Pa, (c) ppl = 10,000 Pa, and (d) ppl = 8000 Pa

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Fig. 17

Comparison of the back-pressure at the outlet (case 3): (a) ppl = 14,000 Pa, (b) ppl = 12,000 Pa, (c) ppl = 8000 Pa, and (d) ppl = 6000 Pa

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Fig. 18

The back-pressure for different plenum pressures (case 2)

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Fig. 19

The total pressure for different plenum pressures (case 2)

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Fig. 20

Comparison of the back-pressure at the outlet: (a) M = 1.5, ppl = 14,000 Pa and (b) M = 1.6, ppl = 10,000 Pa

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Fig. 21

Comparison of the Mach number at the outlet: (a) M = 1.5, ppl = 14,000 Pa and (b) M = 1.6, ppl = 10,000 Pa

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