This article presents a further investigation on the mechanism of hot gas ingestion by exploring the ingress with complicated cavity generated by the rotor-mounted cylinder protrusion. During the experiment, a cavity with 32 cylinder protrusions circumferentially distributed in rotor that contained 59 blades is applied. The annulus Reynolds number and rotating Reynolds number are fixed to be 1.77 × 105 and 7.42 × 105, respectively, while the dimensionless sealing air flow rate ranges from 3047 to 8310. The measurement of CO2 concentration and pressure is conducted. Experimental results show that the sealing efficiency is improved with the introduction of the cylinder protrusions even the static pressure inside cavity is found to be reduced. The effect of the circumferentially nonuniform cavity pressure wave is considered and added into the orifice model, and the effect of some impact factors, i.e., the amplitude, initial phase angle difference, and frequency of the cavity pressure wave, on hot gas ingestion is theoretically discussed in detail. However, it is noted that the cavity pressure wave that was introduced by 32 cylinder rotor-mounted protrusions is found to have insignificant effect on improving the sealing efficiency. In the present study, a modified orifice model that takes the tangential velocity into account is proposed and a new factor H is introduced to well explain the mechanism of the ingress.
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July 2016
Research-Article
Development of a New Factor for Hot Gas Ingestion Through Rim Seal
Dongdong Liu,
Dongdong Liu
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: liudongdongbuaa@buaa.edu.cn
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: liudongdongbuaa@buaa.edu.cn
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Zhi Tao,
Zhi Tao
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: tao_zhi@buaa.edu.cn
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: tao_zhi@buaa.edu.cn
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Xiang Luo,
Xiang Luo
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: xiang.luo@buaa.edu.cn
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: xiang.luo@buaa.edu.cn
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Hongwei Wu,
Hongwei Wu
Department of Mechanical and Construction
Engineering,
Faculty of Engineering and Environment,
Northumbria University,
Newcastle upon Tyne NE1 8ST, UK
e-mail: hongwei.wu@northumbria.ac.uk
Engineering,
Faculty of Engineering and Environment,
Northumbria University,
Newcastle upon Tyne NE1 8ST, UK
e-mail: hongwei.wu@northumbria.ac.uk
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Xiao Yu
Xiao Yu
Shenyang Aero-Engine Research Institute,
Aviation Industry Corporation of China,
Shenyang 110015, China
e-mail: yx-mail@sohu.com
Aviation Industry Corporation of China,
Shenyang 110015, China
e-mail: yx-mail@sohu.com
Search for other works by this author on:
Dongdong Liu
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: liudongdongbuaa@buaa.edu.cn
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: liudongdongbuaa@buaa.edu.cn
Zhi Tao
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: tao_zhi@buaa.edu.cn
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: tao_zhi@buaa.edu.cn
Xiang Luo
National Key Laboratory of Science and Technology on Aero-Engine
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: xiang.luo@buaa.edu.cn
Aero-Thermodynamics,
School of Energy and Power Engineering,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: xiang.luo@buaa.edu.cn
Hongwei Wu
Department of Mechanical and Construction
Engineering,
Faculty of Engineering and Environment,
Northumbria University,
Newcastle upon Tyne NE1 8ST, UK
e-mail: hongwei.wu@northumbria.ac.uk
Engineering,
Faculty of Engineering and Environment,
Northumbria University,
Newcastle upon Tyne NE1 8ST, UK
e-mail: hongwei.wu@northumbria.ac.uk
Xiao Yu
Shenyang Aero-Engine Research Institute,
Aviation Industry Corporation of China,
Shenyang 110015, China
e-mail: yx-mail@sohu.com
Aviation Industry Corporation of China,
Shenyang 110015, China
e-mail: yx-mail@sohu.com
1Corresponding author.
Contributed by the Structures and Dynamics Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received July 27, 2015; final manuscript received September 17, 2015; published online December 4, 2015. Editor: David Wisler.
J. Eng. Gas Turbines Power. Jul 2016, 138(7): 072501 (10 pages)
Published Online: December 4, 2015
Article history
Received:
July 27, 2015
Revised:
September 17, 2015
Citation
Liu, D., Tao, Z., Luo, X., Wu, H., and Yu, X. (December 4, 2015). "Development of a New Factor for Hot Gas Ingestion Through Rim Seal." ASME. J. Eng. Gas Turbines Power. July 2016; 138(7): 072501. https://doi.org/10.1115/1.4031758
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