Research Papers

Aerodynamics and Heat Transfer for a Cooled One and One-Half Stage High-Pressure Turbine—Part I: Vane Inlet Temperature Profile Generation and Migration

[+] Author and Article Information
R. M. Mathison

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235mathison.4@osu.edu

C. W. Haldeman

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235haldeman.5@osu.edu

M. G. Dunn

Gas Turbine Laboratory, The Ohio State University, 2300 West Case Road, Columbus, OH 43235dunn.129@osu.edu

J. Turbomach 134(1), 011006 (May 25, 2011) (11 pages) doi:10.1115/1.4002994 History: Received July 06, 2010; Revised July 07, 2010; Published May 25, 2011; Online May 25, 2011

As controlled laboratory experiments using full-stage turbines are expanded to replicate more of the complicated flow features associated with real engines, it is important to understand the influence of the vane inlet temperature profile on the high-pressure vane and blade heat transfer as well as its interaction with film cooling. The temperature distribution of the incoming fluid governs not only the input conditions to the boundary layer but also the overall fluid migration. Both of these mechanisms have a strong influence on surface heat flux and therefore component life predictions. To better understand the role of the inlet temperature profile, an electrically heated combustor emulator capable of generating uniform, radial, or hot streak temperature profiles at the high-pressure turbine vane inlet has been designed, constructed, and operated over a wide range of conditions. The device is shown to introduce a negligible pressure distortion while generating the inlet temperature conditions for a stage-and-a-half turbine operating at design-corrected conditions. For the measurements described here, the vane is fully cooled and the rotor purge flow is active, but the blades are uncooled. Detailed temperature measurements are obtained at rake locations upstream and downstream of the turbine stage as well as at the leading edge and platform of the blade in order to characterize the inlet temperature profile and its migration. The use of miniature butt-welded thermocouples at the leading edge and on the platform (protruding into the flow) on a rotating blade is a novel method of mapping a temperature profile. These measurements show that the reduction in fluid temperature due to cooling is similar in magnitude for both uniform and radial vane inlet temperature profiles.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Cross section of turbine rig (not to scale)

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Figure 2

Layout of instrumentation and heating elements in combustor emulator (view: forward looking aft)

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Figure 3

Film-cooled vane instrumented with double-sided heat-flux gauges

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Figure 4

Leading edge total temperature thermocouples

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Figure 5

Blade heat-flux gauge positions

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Figure 6

Overview of purge, platform, and tip instrumentation locations (not to scale)

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Figure 7

Unshrouded thermocouple as installed on platform and angel wing

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Figure 8

Coolant supply pressure history for a typical run with nominal flow rates

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Figure 9

Coolant supply temperature history for a typical run with nominal flow rates

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Figure 10

Comparison of sector centerline metal temperature profile factor for different profile shapes

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Figure 11

Metal temperature distortion factor for three inlet temperature profile shapes

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Figure 12

Comparison of metal and rake profile factors

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Figure 13

Comparison of metal and rake temperatures for different profiles

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Figure 14

Temperature profile migration through the turbine stage for (a) uniform profile and (b) radial profile





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