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您的检索式：作者名="T.Sugimoto"
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| 1 | 金属注射成形冷作工具钢的超声疲劳性能显示文摘用超声疲劳试验研究了金属注射成形(MIM)冷作工具钢和锻轧钢(JISSKD11)的高周疲劳性能。锻轧钢试样于423K回火1h。另一方面,为了评估回火温度对疲劳性能的影响,将MIM钢试样于不同温度下进行了回火。在N=103~108疲劳寿命范围内进行了超声疲劳试验。MIM钢试样的疲劳强度和锻轧钢试样相同。MIM钢试样的疲劳强度随着回火温度升高而减低。显微组织的观察结果表明,MIM钢试样的碳化物的直径与形状比锻轧钢试样的均一。 | K.Doi K.Hanami T.Teraoka S.Terauchi T.Sugimoto 韩风麟 | 2005 | 粉末冶金技术2005，23，2： | 1 |
| 2 | Numerical investigation on heat transfer in an advanced new leading edge impingement cooling configuration显示文摘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 turbine thermal efficiency the development of more advanced internal cooling configurations at leading edge is very necessary.As the state of the art leading edge cooling configuration a concave channel with multi inline jets has been widely used in most of the blades.However,this kind of configuration also generates strong spent flow,which shifts the impingement off the stagnation point and weakens the impingement heat transfer.In order to solve this problem a new internal cooling configuration using double swirl chambers in gas turbine leading edge has been developed and introduced in this paper.The double swirl chambers cooling(DSC)technology is introduced by the authors and contributes a significant enhancement of heat transfer due to the generation of two anti-rotated swirls.In DSC-cooling,the reattachment of the swirl flows always occurs in the middle of the chamber,which results in a linear impingement effect.Compared with the reference standard impingement cooling configuration this new cooling system provides a much more uniform heat transfer distribution in the chamber axial direction and also provides a much higher heat transfer rate.In this study,the influences of different geometrical parameters e.g.merging ratio of two cylinder channels,the jet inlet hole configurations and radius of blunt protuberances in DSC have been investigated numerically.The results show that in the DSC cooling system the jet inlet hole configurations have large influences on the thermal performance.The rectangular inlet holes,especially those with higher aspect ratios,show much better heat transfer enhancement than the round inlet holes.However,as the price for it the total pressure drop is increased.Using blunt protuberances instead of sharp edges in the DSC cooling can improve the heat transfer enhancement and reduce the total pressure drop. | G.Lin K.Kusterer A.H.Ayed D.Bohn T.Sugimoto R.Tanaka M.Kazari | 2015 | Propulsion and Power Research2015，4，4： | 1 |
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