Zobrazeno 1 - 10
of 16
pro vyhledávání: '"Fujuan Tong"'
Publikováno v:
Advances in Mechanical Engineering, Vol 7 (2015)
In this article, the effects of film cooling holes arrangement and groove depth on the heat transfer and film cooling performance of blade tip are investigated. For this numerical research, a high-pressure turbine blade with the squealer tip is appli
Externí odkaz:
https://doaj.org/article/dc579f06f932474295cc8febf36f9ca7
Publikováno v:
Journal of Thermal Science. 28:472-483
The complex structure at trailing edge reduces the manufacturing precision, which results in an error in the size of the trailing edge structure. In this study, the performance of a stage high-pressure turbine (HP turbine) is calculated out in three
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::63fa7ca41a82bd79872803b953f4768f
https://doi.org/10.1007/s11630-019-1091-y
https://doi.org/10.1007/s11630-019-1091-y
Publikováno v:
Advances in Mechanical Engineering, Vol 5 (2013)
The turbine blade works at high thermal loads, especially the trailing edge of the blade due to the hot gas leakage flow. Pin-fins are well recognized as a kind of effective device to augment the convective heat transfer and effectively cool the trai
Externí odkaz:
https://doaj.org/article/36da7b702bd04bb6b48db805663e4547
Publikováno v:
Structural and Multidisciplinary Optimization. 59:659-673
Considering the coupling among aerodynamic, heat transfer and strength, a reliability based multidisciplinary design optimization method for cooling turbine blade is introduced. Multidisciplinary analysis of cooling turbine blade is carried out by se
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::09ae48895a251ba18474d7c27fc5d65a
https://doi.org/10.1007/s00158-018-2081-5
https://doi.org/10.1007/s00158-018-2081-5
Publikováno v:
Multidiscipline Modeling in Materials and Structures. 14:722-734
Purpose Blade tip clearance has always been a concern for the gas turbine design and control. The numerical analysis of tip clearance is based on the turbine components displacement. The purpose of this paper is to investigate the thermal and mechani
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d54c9bb74c28a2fef03b6b6fde53d321
https://doi.org/10.1108/mmms-08-2017-0081
https://doi.org/10.1108/mmms-08-2017-0081
Numerical simulation on film cooling with compound angle of blade leading edge model for gas turbine
Publikováno v:
International Journal of Heat and Mass Transfer. 115:839-855
Film cooling performances of the cylindrical film cooling holes with different compound angles on the turbine blade leading edge model are investigated in this paper. Several numerical simulation results are compared with available experimental data,
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::717690ca28a6dc2734164f6e3e21c82e
https://doi.org/10.1016/j.ijheatmasstransfer.2017.07.105
https://doi.org/10.1016/j.ijheatmasstransfer.2017.07.105
Publikováno v:
Volume 5B: Heat Transfer.
The laminated cooling configuration can effectively enhance heat transfer and improve cooling effectiveness through combining the advantage of impingement cooling, film cooling and pin fin cooling. In this study, four laminated configurations with di
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::724e1d7619d89bc386480c82ac4f5a4d
https://doi.org/10.1115/gt2019-92055
https://doi.org/10.1115/gt2019-92055
Publikováno v:
International Journal of Thermal Sciences. 149:106186
The multiple impingement jet system in a high-pressure turbine inner casing has been studied numerically. Four target surface configurations, i.e., smooth, cambered rib, square and round pin-fin are investigated, respectively. Three different boundar
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::341181c6f4916c4d495dc5ee6be705af
https://doi.org/10.1016/j.ijthermalsci.2019.106186
https://doi.org/10.1016/j.ijthermalsci.2019.106186
Publikováno v:
Volume 2: Development and Applications in Computational Fluid Dynamics; Industrial and Environmental Applications of Fluid Mechanics; Fluid Measurement and Instrumentation; Cavitation and Phase Change.
An efficient cooling method for the turbine inner casing is essential with the increasing of the turbine inlet temperature. The heat transfer and flow characteristics of a coupled cooling system in the turbine inner casing part, i.e., three rows of i
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::3a4ea61eae66be7f8aa8dbbc031a92a2
https://doi.org/10.1115/fedsm2018-83206
https://doi.org/10.1115/fedsm2018-83206
Publikováno v:
Volume 7A: Structures and Dynamics.
At present, advanced gas turbine are designed to work at increasingly higher turbine inlet temperatures (TIT) to obtain higher thermal efficiency and power. TIT of modern aircraft engine has exceeded temperature limit of high-temperature alloys appli
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1d0678b8f63c14c85913376ddca48951
https://doi.org/10.1115/gt2018-76285
https://doi.org/10.1115/gt2018-76285