Zobrazeno 1 - 10
of 17
pro vyhledávání: '"Will F. Colban"'
Autor:
Ulf Aronsson, Rolf D. Reitz, Isaac Ekoto, Will F. Colban, David E. Foster, Sungwook Park, Paul C. Miles, Öivind Andersson
Publikováno v:
SAE International Journal of Engines. 2:411-430
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8648002d9fdb8701bb0328085f7c1a9b
https://doi.org/10.4271/2009-24-0043
https://doi.org/10.4271/2009-24-0043
Publikováno v:
SAE International Journal of Engines. 2:1265-1289
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1698e4c298dab54c5ed271efe8a06479
https://doi.org/10.4271/2009-01-1446
https://doi.org/10.4271/2009-01-1446
Publikováno v:
SAE International Journal of Fuels and Lubricants. 1:933-956
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c2c49163f452c040d74d8cc3de3b0c0a
https://doi.org/10.4271/2008-01-1602
https://doi.org/10.4271/2008-01-1602
Autor:
Paul C. Miles, A. Manuel, Seungmook Oh, David E. Foster, Roger Krieger, Duksang Kim, Russell P. Durrett, D. Gonzalez, Will F. Colban, Richard Opat
Publikováno v:
SAE International Journal of Fuels and Lubricants. 1:505-519
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e1970557ae20e2e00a57820fcfc37e6a
https://doi.org/10.4271/2008-01-1066
https://doi.org/10.4271/2008-01-1066
Autor:
Karen A. Thole, Will F. Colban
Publikováno v:
International Journal of Heat and Fluid Flow. 28:341-356
Rising combustor exit temperatures in gas turbine engines necessitate active cooling for the downstream turbine section to avoid thermal failure. Film-cooling has long been an integral part of turbine cooling schemes. Cooling the endwall of a turbine
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d1fc245b0b4de3d038915ba696dc8d49
https://doi.org/10.1016/j.ijheatfluidflow.2006.05.002
https://doi.org/10.1016/j.ijheatfluidflow.2006.05.002
Publikováno v:
Journal of Turbomachinery. 129:23-31
The flow exiting the combustor in a gas turbine engine is considerably hotter than the melting temperature of the turbine section components, of which the turbine nozzle guide vanes see the hottest gas temperatures. One method used to cool the vanes
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b22f1faba299a1cb011f2d972dc083ac
https://doi.org/10.1115/1.2370747
https://doi.org/10.1115/1.2370747
Publikováno v:
Journal of Turbomachinery. 127:718-725
This study evaluates the impact of typical cooling hole shape variations on the thermal performance of fan-shaped film holes. A comprehensive set of experimental test cases featuring 16 different film-cooling configurations with different hole shapes
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::07600f100f9702428868847e65953cc4
https://doi.org/10.1115/1.2019315
https://doi.org/10.1115/1.2019315
Publikováno v:
Journal of Turbomachinery. 128:53-61
In a typical gas turbine engine, the gas exiting the combustor is significantly hotter than the melting temperature of the turbine components. The highest temperatures in an engine are typically seen by the turbine inlet guide vanes. One method used
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::d1486873ae50dbe2c432a589fd4eb5c7
https://doi.org/10.1115/1.2098789
https://doi.org/10.1115/1.2098789
Publikováno v:
Journal of Turbomachinery. 125:193-202
Improved durability of gas turbine engines is an objective for both military and commercial aeroengines as well as for power generation engines. One region susceptible to degradation in an engine is the junction between the combustor and first vane g
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::5ae39ef7cc8b5885342e2aa4bc062535
https://doi.org/10.1115/1.1561811
https://doi.org/10.1115/1.1561811
Publikováno v:
Volume 5: Heat Transfer, Parts A and B.
Low emission requirements for heavy-duty gas turbines can be achieved with flat combustor temperature profiles, reducing the combustor peak temperature. As a result, the heat load on the first stage heat shield above the first stage blade increases.
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::52889d91b4d034550fbe91246af5abd1
https://doi.org/10.1115/gt2011-46294
https://doi.org/10.1115/gt2011-46294