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Research Papers

Study of a Cooling Feed Pipe With a Covering Plate on a Ribbed Turbine Case

[+] Author and Article Information
Fangyuan Liu

Aero-engine Thermal Environment
and Structure Key Laboratory,
Ministry of Industry and Information Technology,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: mucongfei@126.com

Junkui Mao

Professor
Aero-engine Thermal Environment
and Structure Key Laboratory,
Ministry of Industry and Information Technology,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: mjkpe@nuaa.edu.cn

Chao Han

School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: danielhchp@gmail.com

Yuanjian Liu

Aero-engine Thermal Environment
and Structure Key Laboratory,
Ministry of Industry and Information Technology,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: 874520612@qq.com

Xingsi Han

Aero-engine Thermal Environment
and Structure Key Laboratory,
Ministry of Industry and Information Technology,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: xshan@nuaa.edu.cn

Fengli Liang

Aero-engine Thermal Environment
and Structure Key Laboratory,
Ministry of Industry and Information Technology,
Nanjing University of Aeronautics
and Astronautics,
Nanjing 210016, China
e-mail: fengli912@nuaa.edu.cn

1Corresponding author.

Manuscript received June 14, 2018; final manuscript received April 8, 2019; published online May 23, 2019. Assoc. Editor: Scott C. Morris.

J. Eng. Gas Turbines Power 141(7), 071024 (May 23, 2019) (10 pages) Paper No: GTP-18-1253; doi: 10.1115/1.4043445 History: Received June 14, 2018; Revised April 08, 2019

Considering the complicated geometry in an active clearance control (ACC) system, the design of an improved cooling feed pipe with a covering plate for a high pressure ribbed turbine case was investigated. Numerical calculations were analyzed to obtain the interactions between the impinging jet arrays fed by the pipe. Experimental tests were performed to explore the effect of the Reynolds number (2000–20,000) and the jet-to-surface spacing ratio (6–10) on the streamwise-averaged Nusselt numbers. Additionally, the effect of the crossflow produced by the configuration was investigated. Results showed a confined curved channel was formed by the pipe and ribbed case, which resulted in crossflow. The crossflow evolved into vortices and the streamwise-averaged Nusselt number on the high ribs was subsequently increased. Furthermore, the distribution of the heat transfer on the entire surface became more uniform compared with that of traditional impinging jet arrays. A higher Nusselt number was achieved by decreasing the jet-to-surface spacing and increasing the Reynolds number. This investigation has revealed a cooling configuration for controlling the wall flow and evening the heat transfer on the case surface, especially for the ribs.

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References

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Figures

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Fig. 1

Schematic of a turbine ACC system [4]

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Fig. 2

Schematic of test section: (a) entire section; (b) cross section; and (c) measuring holes in the target

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Fig. 3

Schematic of test rig

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Fig. 4

Schematic of heat transfer measurement

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Fig. 5

Schematic of the computational domain

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Fig. 6

Mesh sensitivity analysis

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Fig. 7

A comparison of the experimental and numerical results

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Fig. 8

Nuy¯ distributions with increasing Re: (a) H/d = 6; (b) H/d = 8; and (c) H/d = 10

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Fig. 9

A comparison of the experimental data and the reference results for S/d = 8, H/d = 6, and Re = 20,000

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Fig. 10

Streamlines of the cooling air in cross section X1 (Re = 5000)

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Fig. 11

Streamlines of the cooling air in cross section X2 (Re = 5000)

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Fig. 12

Velocity vector of jet array no. 2 in the streamwise direction with increasing Re

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Fig. 13

Nuy¯ distributions with increasing H/d: (a) Re = 2000; (b) Re = 3000; (c) Re = 4000; (d) Re = 5000; (e) Re = 10,000; and (f) Re = 20,000

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