0
Research Papers: Gas Turbines: Turbomachinery

Windage Heating in a Shrouded Rotor-Stator System

[+] Author and Article Information
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

Da Zhang

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: zhangdamail@gmail.com

Xiang Luo

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: xiang.luo@buaa.edu.cn

Guoqiang Xu

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: guoqiang_xu@buaa.edu.cn

Jianqiao Han

National Key Laboratory of Science
and Technology on Aero-Engine
Aero-Thermodynamics,
Beihang University,
37# Xueyuan Road, Haidian District,
Beijing 100191, China
e-mail: 777aaas@sina.com

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received December 8, 2013; final manuscript received January 2, 2014; published online February 4, 2014. Editor: David Wisler.

J. Eng. Gas Turbines Power 136(6), 062602 (Feb 04, 2014) (10 pages) Paper No: GTP-13-1441; doi: 10.1115/1.4026429 History: Received December 08, 2013; Revised January 02, 2014

This paper has experimentally and numerically studied the windage heating in a shrouded rotor-stator disk system with superimposed flow. Temperature rise in the radius direction on the rotating disk is linked to the viscous heating process when cooling air flows through the rotating component. A test rig has been developed to investigate the effect of flow parameters and the gap ratio on the windage heating, respectively. Experimental results were obtained from a 0.45 m diameter disk rotating at up to 12,000 rpm with gap ratio varying from 0.02 to 0.18 and a stator of the same diameter. Infrared temperature measurement technology has been proposed to measure the temperature rise on the rotor surface directly. The PIV technique was adapted to allow for tangential velocity measurements. The tangential velocity data along the radial direction in the cavity was compared with the results obtained by CFD simulation. The comparison between the free disk temperature rise data and an associated theoretical analysis for the windage heating indicates that the adiabatic disk temperature can be measured by infrared method accurately. For the small value of turbulence parameter, the gap ratio has limited influence on the temperature rise distribution along the radius. As turbulence parameter increases, the temperature rise difference is independent of the gap ratio, leaving that as a function of rotational Reynolds number and throughflow Reynolds number only. The PIV results show that the swirl ratio of the rotating core between the rotor and the stator has a key influence on the windage heating.

Copyright © 2014 by ASME
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Fig. 1

The schematic of the test rig

Grahic Jump Location
Fig. 2

General assembly of the disks for IR measurement

Grahic Jump Location
Fig. 4

Disk temperature counter by infrared measurement for the free disk case

Grahic Jump Location
Fig. 5

Variation of disk-to-surroundings temperature rise with dimensional radius for a free disk, as well as the theoretical values

Grahic Jump Location
Fig. 6

Sketch of the solving domain and the computational grid

Grahic Jump Location
Fig. 7

Computed streamline in the r-z plane of different gap ratio for Cw = 0.68 × 104, ReΦ = 4.23 × 106 (λT  <  0.219)

Grahic Jump Location
Fig. 8

Computed streamline in r-z plane of different gap ratio for Cw = 3.41 × 104, ReΦ = 2.82 × 106 (λT  >  0.219)

Grahic Jump Location
Fig. 9

Computed radial distributions of swirl ratio β in the midaxial plane for gap ratio G = 0.02–0.18

Grahic Jump Location
Fig. 10

Flow vectors for the middle plane between the rotor and the stator (ReΦ = 4.23 × 106, G = 0.18)

Grahic Jump Location
Fig. 11

Tangential velocity of the rotating core by CFD and PIV for the case (G = 0.18)

Grahic Jump Location
Fig. 12

Temperature rise along the radius of the rotor (Gc = 0.0044)

Grahic Jump Location
Fig. 13

Temperature rise along the radius of the rotor λT = 0.034 (Cw = 0.68 × 104, ReΦ = 4.23 × 106)

Grahic Jump Location
Fig. 14

Temperature rise along the radius of the rotor λT = 0.17 (Cw = 3.42 × 104, ReΦ = 4.23 × 106)

Grahic Jump Location
Fig. 15

Comparison between the measured data and the correction by Eq. (9) (Gc = 0.0044)

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In