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Research Papers

Performance Simulations of a Gas Turbine Disk-Blade Assembly Employing Miniature Radially Rotating Heat Pipes

[+] Author and Article Information
Yiding Cao

Jian Ling

 Department of Mechanical and Materials Engineering,Florida International University, Miami, FL 33174

J. Heat Transfer 134(5), 051016 (Apr 13, 2012) (7 pages) doi:10.1115/1.4005707 History: Received April 30, 2010; Revised August 09, 2011; Published April 11, 2012; Online April 13, 2012

With a substantially increased gas inlet temperature in modern gas turbines, the cooling of turbine disks is becoming a challenging task. In order to reduce the temperature at the disk rim, a new turbine disk incorporating radially rotating heat pipes has been proposed. The objective of this paper is to conduct a numerical investigation for the cooling effectiveness of the rotating heat pipe. One of the major tasks of this paper is to compare the performance between a proposed disk-blade assembly incorporating radially rotating heat pipes and a conventional disk-blade assembly without the heat pipes under the same heating and cooling conditions. The numerical investigation illustrates that the turbine disk cooling technique incorporating radially rotating heat pipes is feasible. The maximum temperature at the rim of the proposed disk can be reduced by more than 100 °C in comparison with that of a conventional disk without heat pipes. However, the average temperature at the blade airfoil surface can be reduced by only about 10 °C. In addition, both the heat pipe length and diameter have an important effect on the turbine disk cooling. Under the permission of material strength, a longer heat pipe or a larger heat pipe diameter will produce a lower temperature at the disk rim.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

Schematic of a disk-blade assembly sector

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Figure 2

Schematic of a disk-blade assembly sector incorporating rotating heat pipes

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Figure 3

Comparison of overall temperature distributions between the sectors with and without heat pipes

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Figure 4

Average, maximum, and minimum temperature reductions at the disk rim with different dimensionless heat pipe lengths (s = 0.003 m, dhp  = 0.008 m, hhp  = 20,000 W/m K)

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Figure 5

Average temperature reduction at the airfoil surface and average temperature increase at the disk base with different dimensionless heat pipe lengths (s = 0.003 m, dhp  = 0.008 m, hhp  = 20,000 W/m K)

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Figure 6

Average, maximum, and minimum temperature reductions at the disk rim with different dimensionless heat pipe diameters (s = 0.003 m, Lhp  = 0.08 m, hhp  = 20,000 W/m K)

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Figure 7

Average temperature reduction of the airfoil surface and average temperature increase at the disk base with different dimensionless heat pipe diameters (s = 0.003 m, Lhp  = 0.08 m, hhp  = 20,000 W/m K)

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Figure 8

Average, maximum, and minimum temperature reductions at the disk rim with different cooling air temperatures (dhp  = 0.008 m, hhp  = 20,000 W/m K, Lhp  = 0.1 m)

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Figure 9

Average and maximum temperature reductions of the airfoil surface with different cooling air temperatures (dhp  = 0.008 m, hhp  = 20,000 W/m K, Lhp  = 0.1 m)

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Figure 10

Average and maximum temperature reductions at the disk rim and average temperature reduction at the airfoil surface with different effective thermal conductance of the heat pipes (dhp  = 0.008 m, s = 0.003 m, Lhp  = 0.1 m)

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Figure 11

Average and maximum temperature reductions at the disk rim and average temperature reduction of the airfoil surface with different distances, s (dhp  = 0.008 m, hhp  = 20,000 W/m K, Lhp  = 0.1 m)

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