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Research Papers

An Experimental Study on Aerodynamic Performance of Turbine Nozzle Guide Vanes With Trailing-Edge Span-Wise Ejection

[+] Author and Article Information
S. M. Aminossadati

Senior Lecturer
e-mail: uqsamino@uq.edu.au

D. J. Mee

Professor
e-mail: d.mee@uq.edu.au
School of Mechanical and Mining Engineering,
The University of Queensland,
QLD 4072, Australia

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 8, 2010; final manuscript received January 5, 2012; published online March 25, 2013. Assoc. Editor: Karen A. Thole.

J. Turbomach 135(3), 031002 (Mar 25, 2013) (12 pages) Paper No: TURBO-10-1225; doi: 10.1115/1.4006663 History: Received December 08, 2010; Revised January 05, 2012

The present experimental study is to examine the influence of trailing-edge coolant ejection with the span-wise inclination on the aerodynamic loss of turbine nozzle guide vanes. This study uses a cascade of five vanes located in the test section of a low-speed wind tunnel. The vanes have the profile of high-pressure nozzle guide vanes, and the central vane is equipped with the internal cooling and the trailing-edge coolant ejection. The coolant is ejected through trailing-edge slots that are inclined in the span-wise direction at angles varying from 0 deg to 45 deg in 15 deg increments. The results indicate an optimum ejection rate, at which the aerodynamic loss is minimum. There is a little variation in loss as the span-wise inclination is varied when the ratio of coolant to mainstream gas mass flow rate is less than 1.5%. For higher coolant flow rates, however, the loss increases with increases in the span-wise ejection angle.

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References

Figures

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Fig. 1

A schematic diagram of the low speed wind tunnel

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Fig. 2

A schematic diagram of the cascade

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Fig. 3

Cross section of the central vane

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Fig. 4

Trailing-edge sections

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Fig. 5

A schematic diagram of the coolant feed system

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Fig. 6

A schematic diagram of the probe, showing the hole labeling convention

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Fig. 7

Pitch and yaw coefficients at constant pitch and yaw angles

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Fig. 8

Distribution of sidewall static pressure coefficients upstream and downstream of the cascade

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Fig. 9

Local flow properties at the midspan downstream of the cascade (ReCax=2×105)

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Fig. 10

Span-wise flow behavior at pitch position 3 downstream of the cascade with trailing edge ejection (ReCax=2×105)

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Fig. 11

Pitch-wise flow behavior downstream of the cascade at span = 35.5% (ReCax=2×105)

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Fig. 12

Boundary-layer profiles on the pressure and suction sides of the central vane (ReCax=2×105)

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Fig. 13

Computational fluid dynamics domain for the vane’s surface pressure distribution

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Fig. 14

Pressure distributions on the pressure and suction surfaces of vane 3

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Fig. 15

Control volume downstream of the central vane

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Fig. 16

Variation of MFR and BR with coolant mass flow rate ratio (Cm)

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Fig. 17

A schematic diagram of the experimental setup

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Fig. 18

Contour plots of CPt for four different ejection rates (β=0 deg and ReCax=2×105)

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Fig. 19

Variation of aerodynamic loss coefficient with (a) coolant mass flow rate ratio and (b) momentum flux ratio at zero span-wise ejection angle (β=0 deg and ReCax=2×105)

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Fig. 20

Distribution of CPt at different ejection angles (Cm=2.5% and ReCax=2×105)

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Fig. 21

Variation of aerodynamic loss coefficient with (a) coolant mass flow rate ratio and (b) momentum flux ratio at different span-wise ejection angles (ReCax=2×105)

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