Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade

Jun Su Park; Dong Hyun Lee; Dong Ho Rhee; Shin Hyung Kang; Hyung Hee Cho

doi:10.1016/j.energy.2014.05.041

Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade

Jun Su Park, Dong Hyun Lee, Dong Ho Rhee, Shin Hyung Kang, Hyung Hee Cho

Department of Mechanical Engineering

Research output: Contribution to journal › Article › peer-review

57 Citations (Scopus)

Abstract

Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim. The test blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, and the axial chord length (C_x) was 237mm with a turning angle of 126°, the mainstream Reynolds number based on the axial chord and inlet velocity was 1.5×10⁵. In addition, three different types of blade tip surfaces were equipped with a single row of film-cooling holes along the camber line, near the pressure and suction-side rim. The blowing ratio was fixed at 1.5. High heat transfer rates were observed near the leading edge on the tip surface due to reattached flow. Furthermore, heat transfer on both inner side surfaces was higher than that on the tip surface. High film cooling effectiveness was observed in the middle region (0.1<X/C_x<0.6) due to stagnation of the film cooling. Ultimately, a proper cooling system is suggested to reduce the thermal load and enhance the film cooling effectiveness in the squealer tip.

Original language	English
Pages (from-to)	331-343
Number of pages	13
Journal	Energy
Volume	72
DOIs	https://doi.org/10.1016/j.energy.2014.05.041
Publication status	Published - 2014 Aug 1

Bibliographical note

Funding Information:
This work was supported by the Human Resources Development program ( 20134030200200 ) of the Korea Institute of Energy Technology Evaluation and Planning (KETEP) grant funded by the Korea Government Ministry of Trade, Industry and Energy and a National Research Foundation of Korea (NRF) grant funded by the Korea Government (MEST (Ministry of Education, Science and Technology)) (no. 2011-0017673 ).

All Science Journal Classification (ASJC) codes

Civil and Structural Engineering
Modelling and Simulation
Renewable Energy, Sustainability and the Environment
Building and Construction
Fuel Technology
Energy Engineering and Power Technology
Pollution
Mechanical Engineering
Energy(all)
Management, Monitoring, Policy and Law
Industrial and Manufacturing Engineering
Electrical and Electronic Engineering

UN SDGs

This output contributes to the following UN Sustainable Development Goals (SDGs)

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10.1016/j.energy.2014.05.041

Cite this

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title = "Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade",

abstract = "Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim. The test blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, and the axial chord length (Cx) was 237mm with a turning angle of 126°, the mainstream Reynolds number based on the axial chord and inlet velocity was 1.5×105. In addition, three different types of blade tip surfaces were equipped with a single row of film-cooling holes along the camber line, near the pressure and suction-side rim. The blowing ratio was fixed at 1.5. High heat transfer rates were observed near the leading edge on the tip surface due to reattached flow. Furthermore, heat transfer on both inner side surfaces was higher than that on the tip surface. High film cooling effectiveness was observed in the middle region (0.1<X/Cx<0.6) due to stagnation of the film cooling. Ultimately, a proper cooling system is suggested to reduce the thermal load and enhance the film cooling effectiveness in the squealer tip.",

author = "Park, {Jun Su} and Lee, {Dong Hyun} and Rhee, {Dong Ho} and Kang, {Shin Hyung} and Cho, {Hyung Hee}",

note = "Funding Information: This work was supported by the Human Resources Development program ( 20134030200200 ) of the Korea Institute of Energy Technology Evaluation and Planning (KETEP) grant funded by the Korea Government Ministry of Trade, Industry and Energy and a National Research Foundation of Korea (NRF) grant funded by the Korea Government (MEST (Ministry of Education, Science and Technology)) (no. 2011-0017673 ).",

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AU - Park, Jun Su

AU - Lee, Dong Hyun

AU - Rhee, Dong Ho

AU - Kang, Shin Hyung

AU - Cho, Hyung Hee

N1 - Funding Information: This work was supported by the Human Resources Development program ( 20134030200200 ) of the Korea Institute of Energy Technology Evaluation and Planning (KETEP) grant funded by the Korea Government Ministry of Trade, Industry and Energy and a National Research Foundation of Korea (NRF) grant funded by the Korea Government (MEST (Ministry of Education, Science and Technology)) (no. 2011-0017673 ).

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Y1 - 2014/8/1

N2 - Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim. The test blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, and the axial chord length (Cx) was 237mm with a turning angle of 126°, the mainstream Reynolds number based on the axial chord and inlet velocity was 1.5×105. In addition, three different types of blade tip surfaces were equipped with a single row of film-cooling holes along the camber line, near the pressure and suction-side rim. The blowing ratio was fixed at 1.5. High heat transfer rates were observed near the leading edge on the tip surface due to reattached flow. Furthermore, heat transfer on both inner side surfaces was higher than that on the tip surface. High film cooling effectiveness was observed in the middle region (0.1<X/Cx<0.6) due to stagnation of the film cooling. Ultimately, a proper cooling system is suggested to reduce the thermal load and enhance the film cooling effectiveness in the squealer tip.

AB - Detailed heat/mass transfer coefficients and film-cooling effectiveness were measured on the tip and inner rim surfaces of a blade with a squealer rim. The test blade was a two-dimensional version of a modern first-stage gas turbine rotor blade with a squealer rim. The experimental apparatus was equipped with a linear cascade of three blades, and the axial chord length (Cx) was 237mm with a turning angle of 126°, the mainstream Reynolds number based on the axial chord and inlet velocity was 1.5×105. In addition, three different types of blade tip surfaces were equipped with a single row of film-cooling holes along the camber line, near the pressure and suction-side rim. The blowing ratio was fixed at 1.5. High heat transfer rates were observed near the leading edge on the tip surface due to reattached flow. Furthermore, heat transfer on both inner side surfaces was higher than that on the tip surface. High film cooling effectiveness was observed in the middle region (0.1<X/Cx<0.6) due to stagnation of the film cooling. Ultimately, a proper cooling system is suggested to reduce the thermal load and enhance the film cooling effectiveness in the squealer tip.

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Heat transfer and film cooling effectiveness on the squealer tip of a turbine blade

Abstract

Bibliographical note

All Science Journal Classification (ASJC) codes

UN SDGs

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