Aerodynamic and Heat-flux Measurements with Predictions on a Modern One and One-Half State High Pressure transonic Turbine

[+] Author and Article Information
Charles W. Haldeman, Michael G. Dunn

Gas Turbine Laboratory,  Ohio State University, 2300 West Case Road, Columbus, OH 43235

John W. Barter, Brain R. Green, Robert F. Bergholz

 General Electric Aircraft Engines, Cincinnati, OH 45215

J. Turbomach 127(3), 522-531 (Mar 01, 2004) (10 pages) doi:10.1115/1.1861916 History: Received October 01, 2003; Revised March 01, 2004

Aerodynamic and heat-transfer measurements were acquired using a modern stage and 12 high-pressure turbine operating at design corrected conditions and pressure ratio. These measurements were performed using the Ohio State University Gas Turbine Laboratory Turbine Test Facility. The research program utilized an uncooled turbine stage for which all three airfoils are heavily instrumented at multiple spans to develop a full database at different Reynolds numbers for code validation and flow-physics modeling. The pressure data, once normalized by the inlet conditions, was insensitive to the Reynolds number. The heat-flux data for the high-pressure stage suggests turbulent flow over most of the operating conditions and is Reynolds number sensitive. However, the heat-flux data do not scale according to flat plat theory for most of the airfoil surfaces. Several different predictions have been done using a variety of design and research codes. In this work, comparisons are made between industrial codes and an older code called UNSFLO-2D initially published in the late 1980’s. The comparisons show that the UNSFLO-2D results at midspan are comparable to the modern codes for the time-resolved and time-averaged pressure data, which is remarkable given the vast differences in the processing required. UNSFLO-2D models the entropy generated around the airfoil surfaces using the full Navier-Stokes equations, but propagates the entropy invisicidly downstream to the next blade row, dramatically reducing the computational power required. The accuracy of UNSFLO-2D suggests that this type of approach may be far more useful in creating time-accurate design tools, than trying to utilize full time-accurate Navier-Stokes codes which are often currently used as research codes in the engine community, but have yet to be fully integrated into the design system due to their complexity and significant processor requirements.

Copyright © 2005 by American Society of Mechanical Engineers
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Figure 5

HPTV envelope shapes, 50% span

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Figure 2

Reynolds number and pressure ratio variation

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Figure 4

Time-average pressures with envelope range, 50% span, all airfoils

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Figure 16

LPTV 50% span FFT, selected gauges

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Figure 3

Time-averaged pressures for all experimental cases

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Figure 6

HPTV frequency content, 50% span

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Figure 7

HPTB normalized pressure envelopes, pressure surface, 50% span

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Figure 8

HPTB normalized pressure envelopes, suction surface, 50% span

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Figure 9

HPTB normalized pressure leading edge, 50% span

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Figure 10

LPTV normalized pressure envelopes, 50% span

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Figure 11

LPTV normalized pressure FFT amplitudes, 50% span, ±26% wetted distance

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Figure 12

UNSFLO predictions HPTV and HPTB 50%

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Figure 13

Locations on the three airfoil rows as a function of Reynolds number

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Figure 14

Exponent in stanton number∕Reynolds number relationship

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Figure 15

HPTV 50% span FFT, selected gauges




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