Research Papers

The Effect of Coolant Injection on the Endwall Flow of a High Pressure Turbine

[+] Author and Article Information
Jonathan Ong1

Whittle Laboratory,  University of Cambridge, 1 JJ Thomson Avenue, Cambridge CB3 0DY, England e-mail: jonathan.ong@ge.com

Robert J. Miller

Whittle Laboratory, 1 JJ Thomson Avenue, Cambridge CB3 0DY, England

Sumiu Uchida

Mitsubishi Heavy Industries,  Takasago Research and Development Centre, 1-1, Arai-cho Shinhama 2-chome Takasago, Hyogo Prefecture, 676-8686, Japan


Corresponding author. Current address: GE Global Research, Freisinger Landstrasse 50, D-85748 Garching bei München, Germany.

J. Turbomach 134(5), 051003 (May 07, 2012) (8 pages) doi:10.1115/1.4003838 History: Received January 07, 2011; Revised January 08, 2011; Published May 07, 2012; Online May 07, 2012

This paper presents a study of the effects of two types of hub coolant injection on the rotor of a high pressure gas turbine stage. The first involves the leakage flow from the hub cavity into the mainstream. The second involves a deliberate injection of coolant from a row of angled holes from the edge of the stator hub. The aim of this study is to improve the distribution of the injected coolant on the rotor hub wall. To achieve this, it is necessary to understand how the coolant and leakage flows interact with the rotor secondary flows. The first part of the paper shows that the hub leakage flow is entrained into the rotor hub secondary flow and the negative incidence of the leakage strengthens the secondary flow and increases its penetration depth. Three-dimensional unsteady calculations were found to agree with fast response pressure probe measurements at the rotor exit of a low speed test turbine. The second part of the paper shows that increasing the injected coolant swirl angle reduced the secondary flow penetration depth, improves the coolant distribution on the rotor hub, and improves stage efficiency. Most of the coolant however, was still found to be entrained into the rotor secondary flow.

Copyright © 2012 by American Society of Mechanical Engineers
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Figure 1

Low speed research turbine (LSRT) stage

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Figure 2

Fast response pressure probe head design

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Figure 7

Effect of seal gap variation on ZTE

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Figure 8

Effect of seal gap variation on coolant development through the rotor passage (TRAT contours shown)

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Figure 9

Effect of seal gap variation on pitchwise mass averaged relative stagnation temperature at rotor trailing edge plane

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Figure 10

Hub injection modeling on engine representative stage

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Figure 11

Effect of injected swirl angle on ZTE

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Figure 12

Effect of injected swirl angle on time averaged coolant development (TRAT contours)

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Figure 13

Pitchwise mass averaged rotor exit relative stagnation temperature distribution (time averaged)

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Figure 14

Rotor hub normalized time averaged relative stagnation temperature distribution (TRAT)

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Figure 15

Pitchwise mass averaged rotor relative flow angles at (a) 1% Cx and (b) 94% Cx (time averaged)

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Figure 16

Delta stage total-total efficiency from 70 deg case

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Figure 17

Variation in δ velocity components

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Figure 18

Estimated lost efficiency due to thermal and viscous mixing

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Figure 3

LSRT computational domain for unsteady calculations with injected hub leakage flows

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Figure 4

Measured and predicted time averaged rotor relative deviation angle (δ) downstream of the rotor with and without leakage on the LSRT

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Figure 5

Comparison of unsteady measurements with CFD downstream of the rotor on the LSRT

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Figure 6

Smallest and largest seal clearance gaps for the engine representative stage




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