The Experts below are selected from a list of 267 Experts worldwide ranked by ideXlab platform
Raymond E. Gaugler - One of the best experts on this subject based on the ideXlab platform.
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Journal of Turbomachinery, 2003Co-Authors: Jae Su Kwak, Je-chin Han, Ronald Scott Bunker, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. GauglerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1 ×10 6 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
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Heat Transfer Coefficients on the Squealer Tip and Near Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Volume 5: Turbo Expo 2003 Parts A and B, 2003Co-Authors: Jae Su Kwak, Je-chin Han, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. Gaugler, Ronald Scott BunkerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.Copyright © 2003 by ASME
Je-chin Han - One of the best experts on this subject based on the ideXlab platform.
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Film-Cooling Prediction on Turbine Blade Tip with Various Film Hole Configurations
Journal of Thermophysics and Heat Transfer, 2006Co-Authors: H Yang, Hamn-ching Chen, Je-chin HanAbstract:Different film hole arrangements on the plane and squealer tips of a turbine blade are investigated using a Reynolds stress turbulence model and nonequilibrium wall function. The three film hole configurations considered are 1) the Camber arrangement, where the film-cooling holes are located on the mid-Camber Line of the tips; 2) the upstream arrangement, where the film holes are located upstream of the tip leakage flow and high heat transfer region; and 3) the two-rows arrangement, which is a combination of the Camber and upstream arrangements. Calculations were performed first for the nonrotating cases under low inlet/outlet pressure ratio conditions with three different blowing ratios. The predicted heat transfer coefficients are in good agreement with the experimental data, but the film-cooling effectiveness is somewhat overpredicted downstream of the film holes. Simulations were then performed for the nonrotating and rotating Camber Line film hole configuration under high inlet/outlet pressure ratio conditions, which are close to engine conditions. It is found that the rotation decreases the plane tip film-cooling effectiveness but only slightly affects the squealer tip film cooling. However, the rotation significantly increases heat transfer coefficient on the shrouds.
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Journal of Turbomachinery, 2003Co-Authors: Jae Su Kwak, Je-chin Han, Ronald Scott Bunker, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. GauglerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1 ×10 6 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
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Heat Transfer Coefficients on the Squealer Tip and Near Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Volume 5: Turbo Expo 2003 Parts A and B, 2003Co-Authors: Jae Su Kwak, Je-chin Han, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. Gaugler, Ronald Scott BunkerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.Copyright © 2003 by ASME
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Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer
Journal of Heat Transfer, 2002Co-Authors: Gm. S. Azad, Je-chin Han, Ronald Scott Bunker, C. Pang LeeAbstract: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 E 3 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 1.1×10 6
Jae Su Kwak - One of the best experts on this subject based on the ideXlab platform.
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Journal of Turbomachinery, 2003Co-Authors: Jae Su Kwak, Je-chin Han, Ronald Scott Bunker, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. GauglerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1 ×10 6 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
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Heat Transfer Coefficients on the Squealer Tip and Near Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Volume 5: Turbo Expo 2003 Parts A and B, 2003Co-Authors: Jae Su Kwak, Je-chin Han, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. Gaugler, Ronald Scott BunkerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.Copyright © 2003 by ASME
Ronald Scott Bunker - One of the best experts on this subject based on the ideXlab platform.
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Journal of Turbomachinery, 2003Co-Authors: Jae Su Kwak, Je-chin Han, Ronald Scott Bunker, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. GauglerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1 ×10 6 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
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Heat Transfer Coefficients on the Squealer Tip and Near Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Volume 5: Turbo Expo 2003 Parts A and B, 2003Co-Authors: Jae Su Kwak, Je-chin Han, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. Gaugler, Ronald Scott BunkerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.Copyright © 2003 by ASME
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Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer
Journal of Heat Transfer, 2002Co-Authors: Gm. S. Azad, Je-chin Han, Ronald Scott Bunker, C. Pang LeeAbstract: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 E 3 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 1.1×10 6
C. Pang Lee - One of the best experts on this subject based on the ideXlab platform.
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Heat Transfer Coefficients on the Squealer Tip and Near-Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Journal of Turbomachinery, 2003Co-Authors: Jae Su Kwak, Je-chin Han, Ronald Scott Bunker, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. GauglerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid-crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1 ×10 6 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5%, and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.
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Heat Transfer Coefficients on the Squealer Tip and Near Tip Regions of a Gas Turbine Blade With Single or Double Squealer
Volume 5: Turbo Expo 2003 Parts A and B, 2003Co-Authors: Jae Su Kwak, Je-chin Han, C. Pang Lee, Jaeyong Ahn, Robert J. Boyle, Raymond E. Gaugler, Ronald Scott BunkerAbstract:Detailed heat transfer coefficient distributions on a gas turbine squealer tip blade were measured using a hue detection based transient liquid crystals technique. The heat transfer coefficients on the shroud and near tip regions of the pressure and suction sides of a blade were also measured. Squealer rims were located along (a) the Camber Line, (b) the pressure side, (c) the suction side, (d) the pressure and suction sides, (e) the Camber Line and the pressure side, and (f) the Camber Line and the suction side, respectively. Tests were performed on a five-bladed Linear cascade with a blow down facility. The Reynolds number based on the cascade exit velocity and the axial chord length of a blade was 1.1×106 and the overall pressure ratio was 1.2. Heat transfer measurements were taken at the three tip gap clearances of 1.0%, 1.5% and 2.5% of blade span. Results show that the heat transfer coefficients on the blade tip and the shroud were significantly reduced by using a squealer tip blade. Results also showed that a different squealer geometry arrangement changed the leakage flow path and resulted in different heat transfer coefficient distributions. The suction side squealer tip provided the lowest heat transfer coefficient on the blade tip and near tip regions compared to the other squealer geometry arrangements.Copyright © 2003 by ASME
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Effect of Squealer Geometry Arrangement on a Gas Turbine Blade Tip Heat Transfer
Journal of Heat Transfer, 2002Co-Authors: Gm. S. Azad, Je-chin Han, Ronald Scott Bunker, C. Pang LeeAbstract: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 E 3 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 1.1×10 6
