Development of a Transonic Cascade Facility for the Heat Transfer Research of Gas Turbine Blade Tip

This study investigates the effect of a squealer tip geometry arrangement on heat transfer coefficient and static pressure distributions on a gas turbine blade tip in a five-bladed stationary linear cascade. A transient liquid crystal technique is used to obtain detailed heat transfer coefficient distribution. The test blade is a linear model of a tip section of the GE E3 high-pressure turbine first stage rotor blade. Six tip geometry cases are studied: (1) squealer on pressure side, (2) squealer on mid camber line, (3) squealer on suction side, (4) squealer on pressure and suction sides, (5) squealer on pressure side plus mid camber line, and (6) squealer on suction side plus mid camber line. The flow condition during the blowdown tests corresponds to an overall pressure ratio of 1.32 and exit Reynolds number based on axial chord of 1.1×106. Results show that squealer geometry arrangement can change the leakage flow and results in different heat transfer coefficients to the blade tip. A squealer on suction side provides a better benefit compared to that on pressure side or mid camber line. A squealer on mid camber line performs better than that on a pressure side.

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NUMERICAL SIMULATION OF GAS TURBINE BLADE COOLING FOR ENHANCEMENT OF HEAT TRANSFER OF THE BLADE TIP

International Journal of Research in Engineering and Technology ◽

10.15623/ijret.2014.0309006 ◽

2014 ◽

Vol 03 (09) ◽

pp. 35-41

Author(s):

Sushil Sunil Gaikwad .

Keyword(s):

Heat Transfer ◽

Numerical Simulation ◽

Gas Turbine ◽

Turbine Blade ◽

Gas Turbine Blade ◽

Enhancement Of Heat Transfer ◽

Turbine Blade Cooling ◽

Blade Cooling ◽

Blade Tip

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Heat Transfer Enhancement of a Gas Turbine Blade-Tip Wall

Emerging Topics in Heat Transfer - WIT Transactions on State of the Art in Science and Engineering ◽

10.2495/978-1-84564-818-3/003 ◽

2013 ◽

pp. 67-88

Author(s):

G. Xie ◽

B. Sunden

Keyword(s):

Heat Transfer ◽

Heat Transfer Enhancement ◽

Gas Turbine ◽

Turbine Blade ◽

Gas Turbine Blade ◽

Transfer Enhancement ◽

Blade Tip

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Effect of Squealer Geometry Arrangement on Gas Turbine Blade Tip Heat Transfer

10.1115/imece2001/htd-24314 ◽

2001 ◽

Author(s):

Gm Salam Azad ◽

Je-Chin Han ◽

Ronald S. Bunker ◽

C. Pang Lee

Keyword(s):

Heat Transfer ◽

Heat Transfer Coefficient ◽

Transfer Coefficient ◽

Gas Turbine ◽

Turbine Blade ◽

Pressure Ratio ◽

Suction Side ◽

Pressure Side ◽

Gas Turbine Blade ◽

Blade Tip

Abstract This study investigates the effect of a squealer tip geometry arrangement on heat transfer coefficient and static pressure distributions on a gas turbine blade tip in a five-bladed stationary linear cascade. A transient liquid crystal technique is used to obtain detailed heat transfer coefficient distribution. The test blade is a linear model of a tip section of the GE E3 high-pressure turbine first stage rotor blade. Six tip geometry cases are studied: 1) squealer on pressure side, 2) squealer on mid camber line, 3) squealer on suction side, 4) squealer on pressure and suction sides, 5) squealer on pressure side plus mid camber line, and 6) squealer on suction side plus mid camber line. The flow condition corresponds to an overall pressure ratio of 1.32 and exit Reynolds number based on axial chord of 1.1 × 106. Results show that squealer geometry arrangement can change the leakage flow and results in different heat transfer coefficients to the blade tip. A squealer on suction side provides a better benefit compared to that on pressure side or mid camber line. A squealer on mid camber line performs better than that on a pressure side.

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