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Research Papers

A Predictive Model for Preliminary Gas Turbine Blade Cooling Analysis

[+] Author and Article Information
Nafiz H. K. Chowdhury, Hootan Zirakzadeh

Turbine Heat Transfer Laboratory,
Mechanical Engineering Department,
Texas A&M University,
College Station, TX 77843-3123

Je-Chin Han

Turbine Heat Transfer Laboratory,
Mechanical Engineering Department,
Texas A&M University,
College Station, TX 77843-3123
e-mail: jc-han@tamu.edu

1Corresponding author.

Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received December 21, 2015; final manuscript received March 13, 2017; published online April 25, 2017. Assoc. Editor: Jim Downs.

J. Turbomach 139(9), 091010 (Apr 25, 2017) (12 pages) Paper No: TURBO-15-1308; doi: 10.1115/1.4036302 History: Received December 21, 2015; Revised March 13, 2017

The growing trend to achieve a higher turbine inlet temperature (TIT) in the modern gas turbine industry requires a more efficient and advanced cooling system design. Therefore, a complete study of heat transfer is necessary to predict the thermal loadings on the gas turbine vanes and blades. In the current work, a predictive model for the gas turbine blade cooling analysis has been developed. The model is capable of calculating the distribution of coolant mass flow rate (MFR) and metal temperatures of a turbine blade using the mass and energy balance equations at given external and internal boundary conditions. Initially, the performance of the model is validated by demonstrating its capability to predict the temperature distributions for a NASA E3 blade. The model is capable of predicting the temperature distributions with reasonable accuracy, especially on the suction side (SS). Later, this paper documents the overall analysis for the same blade profile but at different boundary conditions to demonstrate the flexibility of the model for other cases. Additionally, guidelines are provided to obtain external heat transfer coefficient (HTC) distributions for the highly turbulent mainstream.

Copyright © 2017 by ASME
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References

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Figures

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Fig. 1

Turbine blade cooling terminology [17]

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Fig. 2

Nodal subdivision in chord direction (x) [18]

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Fig. 3

One-dimensional coolant network mapping in span direction (y)

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Fig. 4

Schematic of single element

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Fig. 5

Heat balance in (a) LE and (b) other portion

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Fig. 6

Coolant flow through the TE region

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Fig. 7

Piecewise model for effectiveness calculation

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Fig. 10

Detailed view of the reference case [18]

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Fig. 11

(a) Spanwise nondimensional RIT and inlet Mach number profile [18] and (b) surface Mach number distribution [18]

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Fig. 12

HTC distribution along the blade surface [18]

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Fig. 13

(a) Calculated internal Reynolds number for the forward loop, MFR = 1.63%W25 and (b) calculated internal Reynolds number for the backward loop, MFR = 1.67%W25

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Fig. 14

(a) Calculated internal HTC for the forward loop, MFR = 1.63%W25 and (b) calculated internal HTC for the backward loop, MFR = 1.67%W25

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Fig. 15

Results comparison with the reference case for external and internal surface temperature (Twi), RIT = 1396 °C, MFR = 3.3%W25, and no TBC layer

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Fig. 16

Variable HTC distributions along the blade surface

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Fig. 17

Temperature contour for E3 blade, RIT = 1700 °C, MFR = 3.3%W25, and with TBC layer (0.25 mm)

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