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Research Papers

Aeroperformance Measurements for a Fully Cooled High-Pressure Turbine Stage

[+] Author and Article Information
Charles Haldeman

e-mail: cwhaldeman@gmail.com

Michael Dunn

e-mail: dunn.129@osu.edu

Randall Mathison

e-mail: mathison.4@osu.eduThe Ohio State University,
Gas Turbine Laboratory,
2300 West Case Road,
Columbus, OH 43235

William Troha

e-mail: bill-troha@cox.net

Timothy Vander Hoek

e-mail: Timothy.vanderhoek@Honeywell.com

Ardeshir Riahi

e-mail: ardeshir.riahi@honeywell.comHoneywell International,
111 South 34th Street,
Phoenix, AZ 85072

1Presently at Pratt and Whitney, East Hartford, CT.

2Retired from Honeywell.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 5, 2012; final manuscript received May 23, 2013; published online September 26, 2013. Editor: David Wisler.

J. Turbomach 136(3), 031001 (Sep 26, 2013) (10 pages) Paper No: TURBO-12-1131; doi: 10.1115/1.4024777 History: Received July 05, 2012; Revised May 23, 2013

A detailed aero performance measurement program utilizing fully cooled engine hardware (high-pressure turbine stage) supplied by Honeywell Aerospace Advanced Technology Engines is described. The primary focus of this work was obtaining relevant aerodynamic data for a small turbine stage operating at a variety of conditions, including changes in operating conditions, geometry, and cooling parameters. The work extraction and the overall stage performance for each of these conditions can be determined using the measured acceleration rate of the turbine disk, the previously measured moment of inertia of the rotating system, and the mass flow through the turbine stage. Measurements were performed for two different values of tip/shroud clearance and two different blade tip configurations. The vane and blade cooling mass flow could be adjusted independently and set to any desired value, including totally off. A wide range of stage pressure ratios, coolant to free stream temperature ratios, and corrected speeds were used during the course of the investigation. A combustor emulator controlled the free stream inlet gas temperature, enabling variation of the temperature ratios and investigation of their effects on aero performance. The influence of the tip/shroud gap is clearly seen in this experiment. Improvements in specific work and efficiency achieved by reducing the tip/shroud clearance depend upon the specific values of stage pressure ratio and corrected speed. The maximum change of 3%–4% occurs at a stage pressure ratio and corrected speed greater than the initial design point intent. The specific work extraction and efficiency for two different blade tip sets (one damaged from a rub and one original) were compared in detail. In general, the tip damage only had a very small effect on the work extraction for comparable conditions. The specific work extraction and efficiency were influenced by the presence of cooling gas and by the temperature of the cooling gas relative to the free stream gas temperature and the metal temperature. These same parameters were influenced by the magnitude of the vane inlet gas total temperature relative to the vane metal temperature and the coolant gas temperature.

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References

Figures

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Fig. 1

Sketch of turbine rig configuration

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Fig. 2

Typical operating history for (a) inlet total pressure, (b) pressure ratio, and (c) rotor speed

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Fig. 3

Temperature establishment over main experiment (a) and stability over data time window (b)

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Fig. 4

Rotor speed and acceleration over data window

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Fig. 5

Variation of power extracted with mass flow

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Fig. 6

Specific work extracted for (a) 1.5% gap, (b) 3% gap, and (c) difference between cases (a minus b)

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Fig. 7

Efficiency for (a) nominal gap, (b) open gap, and (c) difference between cases (a minus b)

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Fig. 8

Effect of tip gap size on (a) specific work and (b) efficiency

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Fig. 9

Influence of blade tip configuration on efficiency

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Fig. 10

Influence of cooling gas introduction on specific work extraction for Tg = Tm = Tc

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Fig. 11

Influence of cooling gas introduction on efficiency for Tg = Tm = Tc

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Fig. 12

Influence of cooling on specific work for Tg> Tm> Tc

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Fig. 13

Influence of cooling on efficiency for Tg> Tm> Tc

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