Research Papers

Heat Transfer Performance of a Transonic Turbine Blade Passage in the Presence of Leakage Flow Through Upstream Slot and Mateface Gap With Endwall Contouring

[+] Author and Article Information
Arnab Roy

Department of Mechanical Engineering,
Virginia Tech,
Blacksburg, VA 24061
e-mail: arnab8@vt.edu

Sakshi Jain

Department of Mechanical Engineering,
Virginia Tech,
Blacksburg, VA 24061
e-mail: sj1987@vt.edu

Srinath V. Ekkad

Department of Mechanical Engineering,
Virginia Tech,
301 Burruss Hall,
800 Drillfield Drive,
Blacksburg, VA 24061
e-mail: sekkad@vt.edu

Wing Ng

Department of Mechanical Engineering,
Virginia Tech,
425 Goodwin Hall (0238),
635 Prices Fork Road,
Blacksburg, VA 24061
e-mail: wng@vt.edu

Andrew S. Lohaus

Siemens Energy, Inc.,
4400 Alafaya Trail,
Orlando, FL 32789
e-mail: andrew.lohaus@siemens.com

Michael E. Crawford

Siemens Energy, Inc.,
11842 Corporate Boulevard,
Orlando, FL 32817
e-mail: michaelcrawford@siemens.com

Santosh Abraham

Siemens Energy, Inc.,
5101 Westinghouse Boulevard,
Charlotte, NC 28273-9640
e-mail: santosh.abraham@siemens.com

1Corresponding author.

2Present address: National Energy Technology Laboratory, Morgantown, WV 26507.

3Present address: Cummins Columbus Engine Plant, 500 Central Avenue, Columbus, IN 47201.

Contributed by the Heat Transfer Division of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received August 2, 2017; final manuscript received August 28, 2017; published online October 3, 2017. Editor: Kenneth Hall.

J. Turbomach 139(12), 121006 (Oct 03, 2017) (11 pages) Paper No: TURBO-17-1101; doi: 10.1115/1.4037909 History: Received August 02, 2017; Revised August 28, 2017

Comparison of heat transfer performance of a nonaxisymmetric contoured endwall to a planar baseline endwall in the presence of leakage flow through stator–rotor rim seal interface and mateface gap is reported in this paper. Heat transfer experiments were performed on a high turning turbine airfoil passage at Virginia Tech's transonic blow down cascade facility under design conditions for two leakage flow configurations—(1) mateface blowing only, (2) simultaneous coolant injection from the upstream slot and mateface gap. Coolant to mainstream mass flow ratios (MFRs) were 0.35% for mateface blowing only, whereas for combination blowing, a 1.0% MFR was chosen from upstream slot and 0.35% MFR from mateface. A common source of coolant supply to the upstream slot and mateface plenum made sure the coolant temperatures were identical at both upstream slot and mateface gap at the injection location. The contoured endwall geometry was generated to minimize secondary aerodynamic losses. Transient infrared thermography technique was used to measure endwall surface temperature and a linear regression method was developed for simultaneous calculation of heat transfer coefficient (HTC) and adiabatic cooling effectiveness, assuming a one-dimensional (1D) semi-infinite transient conduction. Results indicate reduction in local hot spot regions near suction side as well as area averaged HTC using the contoured endwall compared to baseline endwall for all coolant blowing cases. Contoured geometry also shows better coolant coverage further along the passage. Detailed interpretation of the heat transfer results along with near endwall flow physics has also been discussed.

Copyright © 2017 by ASME
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Fig. 1

Turbine assembly features: (a) blade cooling scheme [1] and (b) annular blade rows [2]

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Fig. 2

Virginia Tech transonic cascade facility

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Fig. 3

Cascade test section baseline geometry with mateface and purge slot

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Fig. 4

Mateface gap design

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Fig. 5

Endwall contour designs: (a) baseline and (b) AO

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Fig. 6

Coolant plenums for leakage flows

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Fig. 7

Cascade heat transfer experimental setup

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Fig. 8

Mainstream and coolant temperature variation

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Fig. 9

Linear regression method for uncooled heat transfer (sample data)

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Fig. 10

Linear regression method for film-cooled heat transfer (sample data)

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Fig. 11

Endwall Nusselt number distribution showing effect of the mateface gap (cases 1 and 3)

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Fig. 12

Endwall adiabatic effectiveness for all leakage cases (cases 2, 4, and 5)

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Fig. 13

Endwall Nusselt number distribution for all mateface cases (cases 3–5)

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Fig. 14

Net heat flux reduction for mateface leakage cases (cases 4 and 5)




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