Research Papers

Aerodynamic and Endwall Film-Cooling Investigations of a Gas Turbine Nozzle Guide Vane Applying Temperature-Sensitive Paint

[+] Author and Article Information
Martin Kunze1

Institute of Fluid Mechanics, Technische Universität Dresden, D-01062 Dresden, Germanymartin.kunze@tu-dresden.de

Konrad Vogeler

Institute of Fluid Mechanics, Technische Universität Dresden, D-01062 Dresden, Germanykonrad.vogeler@tu-dresden.de

Glenn Brown

 Siemens Energy, Inc., 1680 South Central Boulevard, Jupiter, FL 33458glenn.brown@siemens.com

Chander Prakash

 Siemens Energy, Inc., 4400 Alafaya Trail, Orlando, FL 32826-2399prakash.chander@siemens.com

Kenneth Landis

 Florida Turbine Technologies, Inc., 1701 Military Trail, Suite 110, Jupiter, FL 33458-7101ken.landis@siemens.com


Corresponding author.

J. Turbomach 133(3), 031027 (Feb 28, 2011) (9 pages) doi:10.1115/1.4003426 History: Received June 15, 2009; Revised July 14, 2009; Published February 28, 2011; Online February 28, 2011

Endwall film-cooling investigations are conducted with a single row of fan-shaped holes in a low-speed, six-bladed linear cascade. The incidence of the inlet flow was changed between −5 deg and 40 deg to achieve higher loading conditions, which results in an intensification of the secondary flow and enhanced interaction with the injected coolant. The investigated profile is based on a near-hub section of the nozzle guide vane of a highly loaded gas turbine. The aerodynamic performance was investigated using pneumatic probes. The film-cooling effectiveness distribution is determined using the temperature-sensitive paint technique. Carbon dioxide was used as coolant to provide elevated density ratios of about 1.4. Although low thermal conductivity material is used for the endwall test plate, the measured temperature fields show influences of 3D-heat conduction inside the test plate. To measure film effectiveness and the heat transfer separately, an adiabatic test surface is needed. Therefore, the effects of heat conduction are modeled using the finite-element-method. With the resulting convective heat flux pattern derived from the computations, the endwall film-cooling measurements are corrected. Furthermore, this approach is applied to evaluate the heat loss inside the holes and the film discharge temperature at the hole exit.

Copyright © 2011 by American Society of Mechanical Engineers
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Figure 1

Endwall cooling scheme with hole geometry

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Figure 2

Temperature-sensitive paint applied to the endwall test plate

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Figure 3

Normalized profile loss characteristic of airfoil, net endwall loss coefficient, and outlet flow angle versus inlet flow angle β1,ms at the midspan

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Figure 4

Total pressure loss coefficient ζ2 at measurement plane MP2 for the investigated three incidence cases of (a) β1,ms=94.8 deg, (b) β1,ms=75.0 deg, and (c) β1,ms=49.4 deg

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Figure 5

Pitchwise-averaged endwall loss coefficient ζew and flow angle deviation Δβ2 versus the spanwise direction

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Figure 6

Profile pressure distributions at the airfoil midspan z/zms=1.0

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Figure 7

Pressure coefficient Cp2 along hole exit locations of row SS-3

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Figure 8

Normalized discharge coefficient CD/CD,OP versus coolant pressure ratio and normalized local blowing rate per hole for row SS-3

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Figure 9

Schematic of thermal situation in the film-cooled endwall

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Figure 10

Schematic of finite-element model

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Figure 11

CFD-computational domain of the investigated turbine cascade

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Figure 12

Heat transfer ratio hm/hm,1 at the endwall surface for the main flow gas path

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Figure 13

Normalized heat transfer coefficient hh for the cylindrical part of the holes of film row SS-3 based on the correlation given in Eq. 11

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Figure 14

(a) Measured wall temperature distribution and (b) FEM-wall temperature field due to heat conduction displayed for endwall cooling through row SS-3 and reference case (data normalized with cascade inlet temperature T1)

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Figure 15

Normalized adiabatic film effectiveness ηaw/ηref for SS-3, M=1.60, and DR=1.40: (a) β1,ms=94.8 deg, (b) β1,ms=75.0 deg, and (c) β1,ms=49.4 deg



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