Zobrazeno 1 - 10
of 57
pro vyhledávání: '"Takao Sugimoto"'
Publikováno v:
Propulsion and Power Research, Vol 2, Iss 3, Pp 177-187 (2013)
By merging two standard swirl chambers, an alternative cooling configuration named double swirl chambers (DSC) has been developed. In the DSC cooling configuration, the main physical phenomena of the swirl flow in swirl chamber and the advantages of
Externí odkaz:
https://doaj.org/article/ebfe29a65fa249399d9d07893f8147b7
Autor:
Norbert Moritz, Karsten Kusterer, Dieter Bohn, Takao Sugimoto, Ryozo Tanaka, Tomoki Taniguchi
Publikováno v:
Propulsion and Power Research, Vol 2, Iss 1, Pp 1-9 (2013)
Great efforts are still put into the design process of advanced film-cooling configurations. In particular, the vanes and blades of turbine front stages have to be cooled extensively for a safe operation. The conjugate calculation technique is used f
Externí odkaz:
https://doaj.org/article/c493b75bfda44131bcd79f7a0c07eec1
Publikováno v:
Measurement. 196:111183
A calibration scheme of position and orientation errors of rotary axis average lines based on touch-trigger probing is widely available on many commercial five-axis machine tools. Such a measurement is influenced by error motions of both linear and r
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::e0a5a72e64e6a98c3602dae28124b151
http://ir.lib.hiroshima-u.ac.jp/00054004
http://ir.lib.hiroshima-u.ac.jp/00054004
Autor:
Takao Sugimoto, Ryozo Tanaka, Dieter Bohn, Masahide Kazari, Karsten Kusterer, A.H. Ayed, Gang Lin
Publikováno v:
Propulsion and Power Research, Vol 4, Iss 4, Pp 179-189 (2015)
It is known that the leading edge has the most critical heat transfer area of a gas turbine blade. The highest heat transfer rates on the airfoil can always be found on the stagnation region of the leading edge. In order to further improve the gas tu
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::2ede32421d437ca8b9f580fcf668f71f
http://www.sciencedirect.com/science/article/pii/S2212540X15000632
http://www.sciencedirect.com/science/article/pii/S2212540X15000632
Publikováno v:
International Journal of Gas Turbine, Propulsion and Power Systems. 6:9-15
In order to achieve high process efficiencies for the economic operation of stationary gas turbines and aero engines, extremely high turbine inlet temperatures at adjusted pressure ratios are applied. The allowable hot gas temperature is limited by t
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8aab8dfadc670f1e65ae5ec1e1386497
https://doi.org/10.38036/jgpp.6.3_9
https://doi.org/10.38036/jgpp.6.3_9
Publikováno v:
Propulsion and Power Research, Vol 2, Iss 3, Pp 177-187 (2013)
By merging two standard swirl chambers, an alternative cooling configuration named double swirl chambers (DSC) has been developed. In the DSC cooling configuration, the main physical phenomena of the swirl flow in swirl chamber and the advantages of
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::16e47ff65dd15d2de4a611102e98f3e7
http://www.sciencedirect.com/science/article/pii/S2212540X13000369
http://www.sciencedirect.com/science/article/pii/S2212540X13000369
Autor:
Noël T. Campana, Masahide Kazari, Takao Sugimoto, Karsten Kusterer, Jens Dickhoff, Ryozo Tanaka, Dieter Bohn
Publikováno v:
Volume 5C: Heat Transfer.
In modern gas turbines, the film cooling technology is essential for the protection of hot parts. Today, shaped holes are widely used, but besides others, the NEKOMIMI-shaped cooling holes have shown that there is still potential to increase the film
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1ed4c79b439d0ffd32cb83d4fe7c7991
https://doi.org/10.1115/gt2016-56194
https://doi.org/10.1115/gt2016-56194
Autor:
Karsten Kusterer, Masahide Kazari, Gang Lin, Peter Bühler, Takao Sugimoto, Ryozo Tanaka, Dieter Bohn
Publikováno v:
Volume 5B: Heat Transfer.
The efforts to improve the process efficiency of modern gas turbines usually lead to competing objectives for the design of the cooling system as turbine inlet temperatures are continuously increased. Typically, the designer of modern cooling systems
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::4a080757d077f8c85227cca8c322b8f3
https://doi.org/10.1115/gt2016-56937
https://doi.org/10.1115/gt2016-56937
Publikováno v:
The Proceedings of the International Conference on Power Engineering (ICOPE). :2-61
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c942b9cebc15901dc78cdd834e59ac87
https://doi.org/10.1299/jsmeicope.2009.2._2-61_
https://doi.org/10.1299/jsmeicope.2009.2._2-61_
Publikováno v:
Journal of Turbomachinery. 129:809-815
Film cooling in gas turbines leads to aerodynamic mixing losses and reduced temperatures of the gas flow. Improvements of the gas turbine thermal efficiency can be achieved by reducing the cooling fluid amount and by establishing a more equal distrib
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::80c94fa41c3db98b12aaea23f4af663e
https://doi.org/10.1115/1.2720508
https://doi.org/10.1115/1.2720508