Research Papers

Local Measurements of Disk Heat Transfer in Heated Rotating Cavities for Several Flow Regimes

[+] Author and Article Information
André Günther

Wieland Uffrecht, Stefan Odenbach

 Chair of Magnetofluiddynamics, Institute of Fluid Mechanics,Technische Universität Dresden, 01062 Dresden, Germany

J. Turbomach 134(5), 051016 (May 11, 2012) (9 pages) doi:10.1115/1.4003965 History: Received February 22, 2011; Revised March 21, 2011; Published May 10, 2012; Online May 11, 2012

This paper discusses experimental results from a two-cavity test rig representation of the internal air system of a high-pressure compressor. Thermal steady-state measurements of the time-averaged local heat fluxes on both sides of the middle disk are presented for three different flow regimes: pure axial throughflow of cooling air and axial throughflow of cooling air in two directions with a superposed radial inflow of hot air in one cavity. Mass flow ratios between 1/40 < mrad /max  < 2/1 are measured. Tests were carried out for a wide range of non-dimensional parameters: Reφ up to 107 , Rez up to 2 × 105 , and Cw up to −2.5 × 104 . In all cases, the shroud is uniformly heated to approximately 100 °C. The local axial heat fluxes are determined separately for both sides of the middle disk from measurements of the surface temperatures with open spot-welded thermo-couples. The method of heat flux determination and an analysis approach calculating the uncertainties and the sensitivity are described and discussed. The local heat flux results of the different flow paths are compared and interpreted by assumed flow structures. The time-averaged heat flux results can be adequately interpreted by flow structures of two toroidal vortices for axial throughflow and a source-sink flow for the radial inflow. The measurements show that the axial heat flux can change direction, i.e., areas exist where the disk is heated and not cooled by the flow. For axial throughflow, a local minimum of heat flux exists on the impinged side in the range of x = 0.65. On the back side, a heating area exists in all tests in the lower half of the disk (x < 0.6) due to recirculated air of higher temperature. This heating area corresponds to the range of the inner vortex and increases with higher axial and rotational Reynolds numbers.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 13

Location of the heat flux zeros on the right (not impinged) side of the middle disk

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Figure 11

Location of the heat flux minimum on the left side/impinged side of the middle disk

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Figure 12

Value of heat flux minimum, locates flow conditions, which can lead to a heating area on the impinged side of a disk with axial throughflow

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Figure 1

Scheme of high-pressure compressor cavities with axial throughflow and/or radial inflow

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Figure 2

Flow structures for an isothermal non-rotating cavity (G = 0.27, r-z-plane, left) and a heated rotating cavity (r-φ-plane, right) with axial throughflow from Farthing [1-2]. Additionally, the coordinate system used in this paper (left).

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Figure 3

Scheme of streamlines for a radial inflow in a rotating cavity from Owen and Rogers [8]

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Figure 4

Scheme of the two-cavity test rig

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Figure 5

Scheme of the core components with the locations of the measuring points relevant in this study and the modeled area of the middle disk for heat flux determination (dark green)

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Figure 6

Radial distribution of coefficients to determine the probable heat flux uncertainty of the left and the right side depending on the uncertainty of the mean surface temperature during a test

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Figure 7

Studied flow regimes

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Figure 8

(a) Surface temperatures of cavity C2 (left side of the middle disk) and (b) surface temperatures of cavity C1 (right side of the middle disk) for three flow regimes at similar conditions, Reφ  = 5.8 × 106 , Rez  = 9.0 × 104 , Cw  = −1.2 × 104

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Figure 9

(a) Axial heat flux on the left side of the middle disk and (b) axial heat flux on the right side of the middle disk for three flow regimes at similar conditions, Reφ  = 5.8 × 106 , Rez  = 9.0 × 104 , Cw  = −1.2 × 104

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Figure 10

Assumed time-averaged flow structures for three flow regimes inside rotating cavities



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