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Research Papers

Experimental Evidence of Temperature Ratio Effect on Turbine Blade Tip Heat Transfer

[+] Author and Article Information
H. Jiang

University of Michigan-Shanghai,
Jiao Tong University Joint Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: jianghm188@163.com

Q. Zhang

City University London,
London EC1V 0HB, UK
e-mail: Qiang.Zhang.1@city.ac.uk

L. He

University of Oxford, Oxford
200240, UK
e-mail: li.he@eng.ox.ac.uk

S. Lu

School of Aeronautics and Astronautics,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: lusp@sjtu.edu.cn

L. Wang

University of Michigan-Shanghai,
Jiao Tong University Joint Institute,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: lipo.wang@sjtu.edu.cn

J. Teng

School of Aeronautics and Astronautics,
Shanghai Jiao Tong University,
Shanghai 200240, China
e-mail: tjf@sjtu.edu.cn

1Corresponding author.

Manuscript received January 25, 2018; final manuscript received October 17, 2018; published online November 28, 2018. Assoc. Editor: Cengiz Camci.

J. Turbomach 140(12), 121010 (Nov 28, 2018) (7 pages) Paper No: TURBO-18-1011; doi: 10.1115/1.4041811 History: Received January 25, 2018; Revised October 17, 2018

Determination of a scalable Nusselt number (based on “adiabatic heat transfer coefficient”) has been the primary objective of the most existing heat transfer experimental studies. Based on the assumption that the wall thermal boundary conditions do not affect the flow field, the thermal measurements were mostly carried out at near adiabatic condition without matching the engine realistic wall-to-gas temperature ratio (TR). Recent numerical studies raised a question on the validity of this conventional practice in some applications, especially for turbine blade. Due to the relatively low thermal inertia of the over-tip-leakage (OTL) flow within the thin clearance, the fluids' transport properties vary greatly with different wall thermal boundary conditions and the two-way coupling between OTL aerodynamics and heat transfer cannot be neglected. The issue could become more severe when the gas turbine manufacturers are making effort to achieve much tighter clearance. However, there has been no experimental evidence to back up these numerical findings. In this study, transient thermal measurements were conducted in a high-temperature linear cascade rig for a range of tip clearance ratio (G/S) (0.3%, 0.4%, 0.6%, and 1%). Surface temperature history was captured by infrared thermography at a range of wall-to-gas TRs. Heat transfer coefficient (HTC) distributions were obtained based on a conventional data processing technique. The profound influence of tip surface thermal boundary condition on heat transfer and OTL flow was revealed by the first-of-its-kind experimental data obtained in the present experimental study.

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Figures

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Fig. 1

Low speed wind tunnel employed in the present study

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Fig. 2

Test section and instrumentations for transient thermal measurement

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Fig. 3

IR camera calibration curve

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Fig. 4

Inlet total temperature and one sample of surface temperature history during a transient thermal measurement

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Fig. 5

Heat flux variations obtained from direct numerical solution and “Impulse Method” (G/S = 1%)

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Fig. 6

Heat flux and tip surface temperature histories at three sample tip locations for G/S = 1%

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Fig. 7

Heat transfer coefficient distributions obtained at low and high TR conditions for G/S = 1%

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Fig. 8

Contours of (a) R2, relative uncertainty and (b) in HTC for G/S = 1%

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Fig. 9

Heat transfer coefficient distributions for three small tip gaps (G/S = 0.3%, 0.4%, and 0.6%) at low and high TRs

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Fig. 10

Distributions of HTC percentage difference (HTC low TR−HTC high TR)/HTC low TR × 100%) at low and high TRs for different tip gaps

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Fig. 12

(a) Density and (b) Mach number distributions for G/S = 0.3% at TR = 0.7 and TR = 0.9

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Fig. 11

Heat flux and tip surface temperature histories measured at three sample tip locations for G/S = 0.3%

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