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Research Papers

Pressure Side and Cutback Trailing Edge Film Cooling in a Linear Nozzle Vane Cascade at Different Mach Numbers

[+] Author and Article Information
Giovanna Barigozzi

Università degli Studi di Bergamo, Dipartimento di Ingegneria Industriale, Viale Marconi, 24044 Dalmine (BG) Italygiovanna.barigozzi@unibg.it

Antonio Perdichizzi

Università degli Studi di Bergamo, Dipartimento di Ingegneria Industriale, Viale Marconi, 24044 Dalmine (BG) Italyantonio.perdichizzi@unibg.it

Silvia Ravelli

Università degli Studi di Bergamo, Dipartimento di Ingegneria Industriale, Viale Marconi, 24044 Dalmine (BG) Italysilvia.ravelli@unibg.it

J. Turbomach 134(5), 051037 (Jun 05, 2012) (10 pages) doi:10.1115/1.4004825 History: Received July 10, 2011; Revised July 28, 2011; Published June 05, 2012; Online June 05, 2012

Tests on a specifically designed linear nozzle guide vane cascade with trailing edge coolant ejection were carried out to investigate the influence of trailing edge bleeding on both aerodynamic and thermal performance. The cascade is composed of six vanes with a profile typical of a high pressure turbine stage. The trailing edge cooling features a pressure side cutback with film cooling slots, stiffened by evenly spaced ribs in an inline configuration. Cooling air is ejected not only through the slots but also through two rows of cooling holes placed on the pressure side, upstream of the cutback. The cascade was tested for different isentropic exit Mach numbers, ranging from M2is  = 0.2 to M2is  = 0.6, while varying the coolant to mainstream mass flow ratio MFR up to 2.8%. The momentum boundary layer behavior at a location close to the trailing edge, on the pressure side, was assessed by means of laser Doppler measurements. Cases with and without coolant ejection allowed us to identify the contribution of the coolant to the off the wall velocity profile. Thermochromic liquid crystals (TLC) were used to map the adiabatic film cooling effectiveness on the pressure side cooled region. As expected, the cutback effect on cooling effectiveness, compared to the other cooling rows, was dominant.

Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 1

View of the wind tunnel

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Figure 2

Vane and trailing edge cooling geometry (size in mm)

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Figure 3

Downstream M2is distributions (X/cax  = 1.45)

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Figure 4

Normalized isentropic profile Mach number distributions at Z/H  = 0.5

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Figure 5

Acceleration parameter

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Figure 6

Solid vane PS boundary layer traverses (X/cax  = 0.92)

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Figure 7

Mass flow share between holes and cutback slots

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Figure 8

VR for holes and cutback slots

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Figure 9

PS boundary layer traverses (X/cax  = 0.92) for variable MFR at M2is  = 0.2

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Figure 12

Laterally averaged adiabatic effectiveness for M2is  = 0.2, at different MFR values

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Figure 13

Adiabatic effectiveness η for M2is  = 0.6 at different MFR values

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Figure 14

Comparison between ηav for M2is  = 0.2 and M2is  = 0.6, at similar MFR values

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Figure 15

Area averaged film cooling effectiveness for variable MFR and M2is

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Figure 10

PS boundary layer traverses (X/cax  = 0.92) for variable MFR and M2is

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Figure 11

Adiabatic effectiveness η for M2is  = 0.2 at different MFR values

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Figure 16

Thermodynamic kinetic energy loss coefficient for variable MFR and M2is

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