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Research Papers: Gas Turbines: Structures and Dynamics

Development of a New Factor for Hot Gas Ingestion Through Rim Seal

[+] Author and Article Information
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

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

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

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

Xiao Yu

Shenyang Aero-Engine Research Institute,
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 138(7), 072501 (Dec 04, 2015) (10 pages) Paper No: GTP-15-1372; doi: 10.1115/1.4031758 History: Received July 27, 2015; Revised September 17, 2015

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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References

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Figures

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Fig. 1

The overall layout of the experimental facility

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Fig. 2

Cross section of the overall configuration

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Fig. 3

Structure of two models

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Fig. 4

Sealing efficiency comparison between A and B at Cw = 3047

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Fig. 5

Sealing efficiency with sealing air flow rate for models A and B

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Fig. 6

The radial static pressure in static wall for models A and B with Cw = 3047

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Fig. 7

The radial average static pressure at difference sealing air flow rates

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Fig. 9

The pressure of annulus and cavity assumed in orifice model

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Fig. 10

The uneven pressure field of annulus and cavity

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Fig. 11

The uneven dimensionless pressure field of annulus and cavity in an arbitrary b

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Fig. 12

The curves of Φo and ε for uneven and uniform pressure inside cavity

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Fig. 13

The curves of Φo and ε in different amplitudes of cavity pressure wave

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Fig. 14

Annulus and cavity pressure with an initial phase angle α

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Fig. 15

Curves of Φo and ε in different initial phase angle differences of cavity and annulus pressure waves

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Fig. 16

Circumferential variations of uneven frequency of annulus and cavity pressure wave. (a) annulus pressure wave f = 1 and cavity pressure wave f = 2 and (b) annulus pressure wave f = 1 and cavity pressure wave f = 0.5.

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Fig. 17

The curves of Φo and ε for uneven frequency of annulus and cavity pressure wave

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Fig. 18

The theory curve of ε and Φo when f=sin(32θ)g=0.5 sin(59θ)+b

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