Thermal analysis of cooling system in a gas turbine transition piece

Jun Su Park, Namgeon Yun, Hokyu Moon, Kyung Min Kim, Sin Ho Kang, Hyung Hee Cho

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

This paper presents thermal analyses of the cooling system of a transition piece, which is one of the primary hot components in a gas turbine engine. The thermal analyses include heat transfer distributions induced by heat and fluid flow, temperature, and thermal stresses. The purpose of this study is to provide basic thermal and structural information on transition piece, to facilitate their maintenance and repair. The study is carried out primarily by numerical methods, using the commercial software, Fluent and ANSYS. First, the combustion field in a combustion liner with nine fuel nozzles is analyzed to determine the inlet conditions of a transition piece. Using the results of this analysis, pressure distributions inside a transition piece are calculated. The outside of the transition piece in a dump diffuser system is also analyzed. Information on the pressure differences is then used to obtain data on cooling channel flow (one of the methods for cooling a transition piece). The cooling channels have exit holes that function as film-cooling holes. Thermal and flow analyses are carried out on the inside of a film-cooled transition piece. The results are used to investigate the adjacent temperatures and wall heat transfer coefficients inside the transition piece. Overall temperature and thermal stress distributions of the transition piece are obtained. These results will provide a direction to improve thermal design of transition piece.

Original languageEnglish
Title of host publicationASME 2011 Turbo Expo
Subtitle of host publicationTurbine Technical Conference and Exposition, GT2011
Pages1915-1924
Number of pages10
EditionPARTS A AND B
DOIs
Publication statusPublished - 2011 Dec 1
EventASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011 - Vancouver, BC, Canada
Duration: 2011 Jun 62011 Jun 10

Publication series

NameProceedings of the ASME Turbo Expo
NumberPARTS A AND B
Volume5

Other

OtherASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011
CountryCanada
CityVancouver, BC
Period11/6/611/6/10

Fingerprint

Cooling systems
Thermoanalysis
Gas turbines
Cooling
Thermal stress
Heat transfer
Channel flow
Pressure distribution
Temperature
Heat transfer coefficients
Stress concentration
Flow of fluids
Nozzles
Numerical methods
Turbines
Repair
Hot Temperature

All Science Journal Classification (ASJC) codes

  • Engineering(all)

Cite this

Park, J. S., Yun, N., Moon, H., Kim, K. M., Kang, S. H., & Cho, H. H. (2011). Thermal analysis of cooling system in a gas turbine transition piece. In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011 (PARTS A AND B ed., pp. 1915-1924). (Proceedings of the ASME Turbo Expo; Vol. 5, No. PARTS A AND B). https://doi.org/10.1115/GT2011-45961
Park, Jun Su ; Yun, Namgeon ; Moon, Hokyu ; Kim, Kyung Min ; Kang, Sin Ho ; Cho, Hyung Hee. / Thermal analysis of cooling system in a gas turbine transition piece. ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011. PARTS A AND B. ed. 2011. pp. 1915-1924 (Proceedings of the ASME Turbo Expo; PARTS A AND B).
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abstract = "This paper presents thermal analyses of the cooling system of a transition piece, which is one of the primary hot components in a gas turbine engine. The thermal analyses include heat transfer distributions induced by heat and fluid flow, temperature, and thermal stresses. The purpose of this study is to provide basic thermal and structural information on transition piece, to facilitate their maintenance and repair. The study is carried out primarily by numerical methods, using the commercial software, Fluent and ANSYS. First, the combustion field in a combustion liner with nine fuel nozzles is analyzed to determine the inlet conditions of a transition piece. Using the results of this analysis, pressure distributions inside a transition piece are calculated. The outside of the transition piece in a dump diffuser system is also analyzed. Information on the pressure differences is then used to obtain data on cooling channel flow (one of the methods for cooling a transition piece). The cooling channels have exit holes that function as film-cooling holes. Thermal and flow analyses are carried out on the inside of a film-cooled transition piece. The results are used to investigate the adjacent temperatures and wall heat transfer coefficients inside the transition piece. Overall temperature and thermal stress distributions of the transition piece are obtained. These results will provide a direction to improve thermal design of transition piece.",
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Park, JS, Yun, N, Moon, H, Kim, KM, Kang, SH & Cho, HH 2011, Thermal analysis of cooling system in a gas turbine transition piece. in ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011. PARTS A AND B edn, Proceedings of the ASME Turbo Expo, no. PARTS A AND B, vol. 5, pp. 1915-1924, ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011, Vancouver, BC, Canada, 11/6/6. https://doi.org/10.1115/GT2011-45961

Thermal analysis of cooling system in a gas turbine transition piece. / Park, Jun Su; Yun, Namgeon; Moon, Hokyu; Kim, Kyung Min; Kang, Sin Ho; Cho, Hyung Hee.

ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011. PARTS A AND B. ed. 2011. p. 1915-1924 (Proceedings of the ASME Turbo Expo; Vol. 5, No. PARTS A AND B).

Research output: Chapter in Book/Report/Conference proceedingConference contribution

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AB - This paper presents thermal analyses of the cooling system of a transition piece, which is one of the primary hot components in a gas turbine engine. The thermal analyses include heat transfer distributions induced by heat and fluid flow, temperature, and thermal stresses. The purpose of this study is to provide basic thermal and structural information on transition piece, to facilitate their maintenance and repair. The study is carried out primarily by numerical methods, using the commercial software, Fluent and ANSYS. First, the combustion field in a combustion liner with nine fuel nozzles is analyzed to determine the inlet conditions of a transition piece. Using the results of this analysis, pressure distributions inside a transition piece are calculated. The outside of the transition piece in a dump diffuser system is also analyzed. Information on the pressure differences is then used to obtain data on cooling channel flow (one of the methods for cooling a transition piece). The cooling channels have exit holes that function as film-cooling holes. Thermal and flow analyses are carried out on the inside of a film-cooled transition piece. The results are used to investigate the adjacent temperatures and wall heat transfer coefficients inside the transition piece. Overall temperature and thermal stress distributions of the transition piece are obtained. These results will provide a direction to improve thermal design of transition piece.

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Park JS, Yun N, Moon H, Kim KM, Kang SH, Cho HH. Thermal analysis of cooling system in a gas turbine transition piece. In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition, GT2011. PARTS A AND B ed. 2011. p. 1915-1924. (Proceedings of the ASME Turbo Expo; PARTS A AND B). https://doi.org/10.1115/GT2011-45961