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Research Papers

Time-Averaged and Time-Accurate Aerodynamic Effects of Forward Rotor Cavity Purge Flow for a High-Pressure Turbine—Part I: Analytical and Experimental Comparisons

[+] Author and Article Information
Brian R. Green

GE Aviation,
Cincinnati, OH 45215
e-mail: brian.green@ge.com

Randall M. Mathison

e-mail: mathison.4@osu.edu

Michael G. Dunn

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

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Turbomachinery. Manuscript received June 22, 2012; final manuscript received May 23, 2013; published online September 20, 2013. Editor: David Wisler.

J. Turbomach 136(1), 011004 (Sep 20, 2013) (13 pages) Paper No: TURBO-12-1074; doi: 10.1115/1.4024774 History: Received June 22, 2012; Revised May 23, 2013

The effect of rotor purge flow on the unsteady aerodynamics of a high-pressure turbine stage operating at design corrected conditions has been investigated, both experimentally and computationally. The experimental configuration consisted of a single-stage high-pressure turbine with a modern film-cooling configuration on the vane airfoil and the inner and outer end wall surfaces. Purge flow was introduced into the cavity located between the high-pressure vane and the high-pressure disk. The high-pressure blades and the downstream low-pressure turbine nozzle row were not cooled. All of the hardware featured an aerodynamic design typical of a commercial high-pressure ratio turbine and the flow path geometry was representative of the actual engine hardware. In addition to instrumentation in the main flow path, the stationary and rotating seals of the purge flow cavity were instrumented with high frequency response flush-mounted pressure transducers and miniature thermocouples in order to measure the flow field parameters above and below the angel wing.

Predictions of the time-dependent flow field in the turbine flow path were obtained using FINE/Turbo, a three-dimensional Reynolds-averaged Navier–Stokes computational fluid dynamics CFD code that had the capability to perform both a steady and unsteady analysis. The steady and unsteady flow fields throughout the turbine were predicted using a three blade-row computational model that incorporated the purge flow cavity between the high-pressure vane and disk. The predictions were performed in an effort to mimic the design process with no adjustment of boundary conditions to better match the experimental data. The time-accurate predictions were generated using the harmonic method. Part I of this paper concentrates on the comparison of the time-averaged and time-accurate predictions with measurements in and around the purge flow cavity. The degree of agreement between the measured and predicted parameters is described in detail, providing confidence in the predictions for the flow field analysis that will be provided in Part II.

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References

Figures

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Fig. 1

Turbine rig cross-section used for the experimental program (not to scale)

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Fig. 2

Instrumentation in and around the purge flow cavity rim seal (not to scale)

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Fig. 3

Surface grid resolution for the airfoils and flowpath (not to scale)

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Fig. 4

Purge flow cavity blocking structure and tangential cut of the grid resolution

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Fig. 5

Inlet total temperature profile for Run 22 (uncooled) and Run 28 (cooled)

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Fig. 6

Comparison of the cooled and uncooled time-averaged total temperature profiles for the exit rakes

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Fig. 7

Comparison of the predicted and measured uncooled-to-cooled exit total temperature δ

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Fig. 8

Comparison of the cooled and uncooled exit total pressure profiles

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Fig. 9

Comparison of the time-averaged static pressure for the trailing edge hub surface

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Fig. 10

Time-series comparison for Run 22 (uncooled) static pressure for the trailing edge hub

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Fig. 11

Time-series comparison for Run 28 (cooled) static pressure for the trailing edge hub

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Fig. 12

Time-averaged comparison for the blade leading edge relative total temperature profiles

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Fig. 13

Predicted and measured uncooled-to-cooled blade leading edge temperature difference

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Fig. 14

Platform thermocouple positions with TC labels (not to scale)

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Fig. 15

Comparison of the platform time-averaged total temperature and FINE/Turbo steady and unsteady results for (a) Run 22, and (b) Run 28

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Fig. 16

Stationary and rotating instrumentation locations in the purge flow cavity (not to scale)

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Fig. 17

Comparison of the stationary cavity time-averaged static pressure data and FINE/Turbo Run 22 and Run 28

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Fig. 18

Run 22 (uncooled) time-series comparison for stationary cavity locations in the (a) angel wing cavity, and (b) entrance region

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Fig. 19

Run 28 (cooled) time-series comparison for the stationary cavity in the (a) angel wing cavity, and (b) entrance region

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Fig. 20

Time-averaged total temperature comparison for the stationary cavity for cooled and uncooled runs

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Fig. 21

Comparison of the rotating cavity time-averaged static pressure data and the FINE/Turbo Run 22 and Run 28

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Fig. 22

Time-series static pressure comparison for the Run 22 (uncooled) rotating cavity for (a) PRW70, (b) PRW71, (c) PRW72, and (d) PRW74

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Fig. 23

Time-series static pressure comparison for the Run 28 (cooled) rotating cavity for (a) PRW70, (b) PRW71, (c) PRW72, and (d) PRW74

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Fig. 24

Comparison of the rotating cavity time-averaged total temperature data and the FINE/Turbo Run 22 and Run 28

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