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Research Papers

Film-Cooling Effectiveness on a Rotating Turbine Platform Using Pressure Sensitive Paint Technique

[+] Author and Article Information
A. Suryanarayanan, B. Ozturk, M. T. Schobeiri, J. C. Han

Department of Mechanical Engineering, Texas A&M University, College Station, TX 77843-3123

J. Turbomach 132(4), 041001 (Apr 26, 2010) (13 pages) doi:10.1115/1.3142860 History: Received June 20, 2007; Revised March 03, 2009; Published April 26, 2010; Online April 26, 2010

Film-cooling effectiveness is measured on a rotating turbine blade platform for coolant injection through discrete holes using pressure sensitive paint technique. Most of the existing literatures provide information only for stationary endwalls. The effects of rotation on the platform film-cooling effectiveness are not well documented. Hence, the existing three-stage turbine research facility at the Turbomachinery and Flow Performance Laboratory, Texas A&M University was redesigned and installed to enable coolant gas injection on the first stage rotor platform. Two distinct coolant supply loops were incorporated into the rotor to facilitate separate feeds for upstream cooling using stator-rotor gap purge flow and downstream discrete-hole film cooling. As a continuation of the previously published work involving stator-rotor gap purge cooling, this study investigates film-cooling effectiveness on the first stage rotor platform due to coolant gas injection through nine discrete holes located downstream within the passage region. Film-cooling effectiveness is measured for turbine rotor frequencies of 2400 rpm, 2550 rpm, and 3000 rpm corresponding to rotation numbers of Ro=0.18, 0.19, and 0.23, respectively. For each of the turbine rotational frequencies, film-cooling effectiveness is determined for average film-hole blowing ratios of Mholes=0.5, 0.75, 1.0, 1.25, 1.5, and 2.0. To provide a complete picture of hub cooling under rotating conditions, simultaneous injection of coolant gas through upstream stator-rotor purge gap and downstream discrete film-hole is also studied. The combined tests are conducted for gap purge flow corresponding to coolant to mainstream mass flow ratio of MFR=1% with three downstream film-hole blowing ratios of Mholes=0.75, 1.0, and 1.25 for each of the three turbine speeds. The results for combined upstream stator-rotor gap purge flow and downstream discrete holes provide information about the optimum purge flow coolant mass, average coolant hole blowing ratios for each rotational speed, and coolant injection location along the passage to obtain efficient platform film cooling.

Copyright © 2010 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

The overall layout of TPFL-research turbine facility, from Schobeiri (1-3)

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Figure 2

Section view of the modified stator-rotor turbine assembly for stator-rotor purge flow and platform film cooling

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Figure 3

Turbine rotor component with the 24-channel slip ring, stator cavity, and labyrinth seal

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Figure 4

Detailed view of the stator-rotor gap

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Figure 5

Detailed view of rotor platform film-cooling holes

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Figure 6

Sample PSP calibration curve

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Figure 7

Optical setup for PSP data acquisition

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Figure 8

Film-cooling effectiveness distribution on the film-cooling holes for all blowing ratios at 2550 rpm

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Figure 9

Velocity triangles and relative inlet and exit flow angles design speed and for off-design rotating speeds

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Figure 10

Film-cooling effectiveness distribution on the film-cooling holes for all blowing ratios at 2400 rpm

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Figure 11

Film-cooling effectiveness distribution on the film-cooling holes for all blowing ratios at 3000 rpm

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Figure 12

Pitchwise average film-cooling effectiveness distribution along the axial chord for different turbine rotating speeds (Mholes=blowing ratio for holes)

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Figure 13

Pitchwise average film-cooling effectiveness distribution along the axial chord for different hole blowing ratios (at different turbine rotating speeds)

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Figure 14

Film-cooling effectiveness for combined stator-rotor gap and hole coolant injection, 2400 rpm

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Figure 15

Film-cooling effectiveness for combined stator-rotor gap and hole coolant injection, 2550 rpm

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Figure 16

Film-cooling effectiveness for combined stator-rotor gap and hole coolant injection, 3000 rpm

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Figure 17

Film-cooling effectiveness for stator-rotor gap injection for 2400 rpm, 2550 rpm, and 3000 rpm

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Figure 18

Pitchwise averaged film-cooling effectiveness for combined upstream slot and downstream discrete-hole injection

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