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Research Papers

Influence of Coolant Flow Rate on Aero-Thermal Performance of a Rotor Blade Cascade With Endwall Film Cooling

[+] Author and Article Information
G. Barigozzi

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

F. Fontaneto

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

G. Franchini

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

A. Perdichizzi

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

M. Maritano

 Ansaldo Energia S.p.A.—Hot Gas Path Engineering, Via N. Lorenzi 8, 16152 Genova, Italymaritano@aen.ansaldo.it

R. Abram

 Ansaldo Energia S.p.A.—Hot Gas Path Engineering, Via N. Lorenzi 8, 16152 Genova, Italyabram@aen.ansaldo.it

J. Turbomach 134(5), 051038 (Jun 05, 2012) (8 pages) doi:10.1115/1.4004858 History: Received July 10, 2011; Revised July 28, 2011; Published June 05, 2012; Online June 05, 2012

This paper investigates the influence of coolant injection on the aerodynamic and thermal performance of a rotor blade cascade with endwall film cooling. A seven blade cascade of a high-pressure-rotor stage of a real gas turbine has been tested in a low speed wind tunnel for linear cascades. Coolant is injected through 10 cylindrical holes distributed along the blade pressure side. Tests have been preliminarily carried out at low Mach number (Ma2is  = 0.3). Coolant-to-mainstream mass flow ratio has been varied in a range of values corresponding to inlet blowing ratios M1  = 0–4.0. Secondary flows have been surveyed by traversing a five-hole miniaturized aerodynamic probe in two downstream planes. Local and overall mixed-out secondary loss coefficient and vorticity distributions have been calculated from measured data. The thermal behavior has been also analyzed by using thermochromic liquid crystals technique to obtain film cooling effectiveness distributions. All this information, including overall loss production for variable injection conditions, allows us to draw a comprehensive picture of the aero-thermal flow field in the endwall region of a high pressure rotor blade cascade.

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Copyright © 2012 by American Society of Mechanical Engineers
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Figures

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Figure 5

Detail of holes geometry

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Figure 6

Detail of coolant supply plenum

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Figure 7

Blade Mach number distribution

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Figure 8

Solid cascade local ζ distributions: (a) X/cax  = 108% and (b) X/cax  = 130%

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Figure 9

Solid cascade local Ω and secondary velocity vectors distributions: (a) X/cax  = 108% and (b) X/cax  = 130%

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Figure 10

Spanwise (a) primary loss distributions and (b) flow angle deviation—no coolant flow

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Figure 11

Cooled cascade local (a) ζ and (b) Ω and secondary velocity vectors distributions at X/cax  = 108% and M1  = 1.61

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Figure 12

Spanwise (a) flow angle deviation and (b) primary loss distributions—with coolant flow

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Figure 13

Film cooling effectiveness distributions for the different injection conditions

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Figure 14

Area averaged η distributions versus M1

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Figure 3

Inlet velocity profile

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Figure 2

Cascade and endwall cooling geometry

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Figure 1

The wind tunnel (1, inlet duct; 2, test section; 3, tailboard; 4, diffuser; 5, fan; 6, AC motor; 7, discharge channel)

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