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Research Papers

Effects of Inlet Temperature Uniformity and Nonuniformity on the Tip Leakage Flow and Rotor Blade Tip and Casing Heat Transfer Characteristics

[+] Author and Article Information
Md. Hamidur Rahman1

 Concordia University, 1455 De Maisonneuve Blvd. West, Montreal, QC, Canada H3G 1M8

Sung In Kim2

Department of Mechanical and Industrial Engineering, Concordia University, 1515 St. Catherine St. West, EV4.139, Montreal, QC, Canada H3B 5L1

Ibrahim Hassan

Department of Mechanical and Industrial Engineering, Concordia University, 1515 St. Catherine St. West, EV4.139, Montreal, QC, Canada H3B 5L1ibrahimh@alcor.concordia.ca

1

Present address: Assistant Professor of Department of Mechanical and Chemical Engineering, IUT, Bangladesh.

2

Present address: Pratt & Whitney Canada, Longueuil, QC, Canada.

J. Turbomach 134(2), 021001 (Jun 21, 2011) (10 pages) doi:10.1115/1.4003211 History: Received October 12, 2009; Revised July 24, 2010; Published June 21, 2011; Online June 21, 2011

High thermal load appears at the blade tip and casing of a gas turbine engine. It becomes a significant design challenge to protect the turbine materials from this severe situation. As a result of geometric complexity and experimental limitations, computational fluid dynamics tools have been used to predict blade tip leakage flow aerodynamics and heat transfer at typical engine operating conditions. In this paper, the effect of turbine inlet temperature on the tip leakage flow structure and heat transfer has been studied numerically. Uniform low (444 K) and high (800 K) inlet temperatures and nonuniform (parabolic) temperature profiles have been considered at a fixed rotor rotation speed (9500 rpm). The results showed that the change of flow properties at a higher inlet temperature yields significant variations in the leakage flow aerodynamics and heat transfer relative to the lower inlet temperature condition. Aerodynamic behavior of the tip leakage flow varies significantly with the distortion of turbine inlet temperature. For more realistic inlet condition, the velocity range is insignificant at all time instants. At a high inlet temperature, reverse secondary flow is strongly opposed by the tip leakage flow and the heat transfer fluctuations are reduced greatly.

Copyright © 2012 by American Society of Mechanical Engineers
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References

Figures

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Figure 4

Comparison of predicted static pressure distribution at the rotor midspan

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Figure 5

v-velocity profile at x/Cx=50% inside the tip clearance for different numbers of cells

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Figure 6

Temperature profile at x/Cx=50% inside the tip clearance for different numbers of cells

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Figure 7

Periodic natures of the vane pass

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Figure 8

Effect of the number of (a) iterations and (b) time steps on the solutions

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Figure 9

Pressure contour at the stator-rotor midspan; case: high uniform

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Figure 10

Inlet flow angle at the midspan of the rotor side interface along the circumference; (a) case: low uniform, (b). case: high uniform, and (c) case: nonuniform

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Figure 11

Streamlines at the quarter axial chord plane; (a) case: high uniform and (b) case: nonuniform

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Figure 13

Nusselt number contours on the casing; case: high uniform

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Figure 14

Nusselt number contours on the casing; case: nonuniform

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Figure 15

Nusselt number contours on the blade tip; case: high uniform

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Figure 16

Nusselt number contours on the blade tip; case: nonuniform

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Figure 17

Nusselt number distributions along 0–1 at 25% chord; (a) case: low uniform, (b) case: high uniform, and (c) case: nonuniform

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Figure 18

Temperature distributions at the midclearance of the front tip at t∗=0.25, 25% chord

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Figure 12

v-velocity profile in the clearance region at x/Cx=25% and y/ty=50%; (a) case: low uniform, (b) case: high uniform, and (c) case: nonuniform

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Figure 3

Comparison of circumferentially averaged adiabatic wall temperature on the casing from the blade tip leading to the trailing edge

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Figure 2

Computational grid at (a) rotor midspan and (b) streamwise location, showing grid resolution in the tip clearance region

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Figure 1

Computational domain consists of one stator and two rotor blades

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