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    • 5. 发明授权
    • Cooled turbine blade for a gas turbine
    • 用于燃气轮机的冷却涡轮叶片
    • US5624231A
    • 1997-04-29
    • US364686
    • 1994-12-28
    • Fumio OhtomoYoshitaka FukuyamaYuji NakataAsako InomataHisashi MatsudaShoko Ito
    • Fumio OhtomoYoshitaka FukuyamaYuji NakataAsako InomataHisashi MatsudaShoko Ito
    • F01D5/18F02C7/18
    • F01D5/187F01D5/186F05D2260/201F05D2260/202
    • A turbine blade performs internal cooling by a cooling gas flowing through internal cooling flow passages and FCFC cooling by a cooling gas jetted out through film holes arranged on the substantially whole area of the blade surface. The film holes are arranged in rows extending in the span direction at predetermined pitches in the chord direction. The dimensions of the elements of the turbine blade are determined by a mathematical formula 5.ltoreq.L/N.multidot.D.ltoreq.50, where L is the length of any interval of the surface of the cooled turbine blade, N is the number of rows of the film holes in the interval and D is an average diameter of the film holes in the interval. With this arrangement, the maximum cooling efficiency at a small amount of cooling gas flow is attained, and both the quantity of heat per unit area of the blade surface transmitted from the main flow gas to the blade surface and the thermal stresses are reduced.
    • 涡轮叶片通过流过内部冷却流路的冷却气体进行内部冷却,并且通过冷却气体进行FCFC冷却,所述冷却气体通过布置在叶片表面的大致整个区域上的薄膜孔喷出。 薄膜孔以沿翼弦方向以预定的间距在翼展方向上延伸的排布置。 涡轮叶片的元件的尺寸由数学公式5确定,其中L是冷却的涡轮叶片的表面的任何间隔的长度,N是行数 的间隔中的膜孔,D是间隔中的膜孔的平均直径。 由此,能够实现少量冷却气体流动时的最大冷却效率,从主流动气体向叶片表面传递的叶片面积的单位面积的热量和热应力减小。
    • 6. 发明授权
    • Cooled turbine blade for a gas turbine
    • 用于燃气轮机的冷却涡轮叶片
    • US5538394A
    • 1996-07-23
    • US365430
    • 1994-12-28
    • Asako InomataHisashi MatsudaYoshitaka FukuyamaFumio OhtomoYuji NakataHideo Nomoto
    • Asako InomataHisashi MatsudaYoshitaka FukuyamaFumio OhtomoYuji NakataHideo Nomoto
    • F01D5/18F02C7/18F28F3/02
    • F01D5/187F28F3/02F05D2240/127F05D2260/2212Y02T50/673Y02T50/676
    • A cooling flow passage assembly consisting of pressure side cooling flow passages extending in a span direction and suction side cooling flow passages extending in the span direction and serially connected to the pressure side cooling flow passages is formed in a turbine blade. A cooling medium flows through the pressure side cooling flow passages in the direction toward the tip portion and through the suction side cooling flow passages in the direction toward the root. Cooling effect is improved by a Coriolis force. The number of the suction side cooling flow passages is larger than the number of the pressure side cooling flow passages. At least one of the suction side cooling flow passages forms at least one most downstream cooling flow passage. The cooling medium flows through the most downstream cooling flow passage and is exhausted outside of the turbine blade through nozzles, whereby the flow of the cooling medium through the most downstream cooling flow passage is speeded up.
    • 在涡轮叶片中形成有由在跨度方向上延伸的压力侧冷却流路和沿跨度方向延伸并串联连接到压力侧冷却流路的吸入侧冷却流路构成的冷却流路组件。 冷却介质沿着朝向前端部的方向流过压力侧冷却流路,并且沿着朝向根部的方向通过吸入侧冷却流路。 科里奥利力提高了冷却效果。 吸入侧冷却流路的数量大于压力侧冷却流路的数量。 吸入侧冷却流路中的至少一个形成至少一个最下游的冷却流路。 冷却介质流过最下游的冷却流道,并通过喷嘴排出涡轮叶片的外部,由此冷却介质通过最下游的冷却流道的流动被加速。
    • 7. 发明授权
    • Gas turbine blade
    • 燃气轮机叶片
    • US4992026A
    • 1991-02-12
    • US370080
    • 1989-06-22
    • Fumio OhtomoYasuo OkamotoShoko ItoYoshitaka FukuyamaHideo IwasakiTakeshi Watanabe
    • Fumio OhtomoYasuo OkamotoShoko ItoYoshitaka FukuyamaHideo IwasakiTakeshi Watanabe
    • F01D5/18
    • F01D5/187F05D2260/202F05D2260/2212
    • A blade of a gas turbine includes a main body having a dovetail portion and a blade portion extending from the dovetail portion. A cooling air passage for flowing a cooling air is formed in the main body to cool the blade portion. The passage includes a cooling air inlet port open to the dovetail portion and an outlet port open to an extended tip of the blade portion. A first passage portion extends from the inlet port to the portion close to the extended tip along a leading edge of the blade portion. A final passage portion extends from the dovetail portion to the outlet port. The flow sectional area of the final passage portion is gradually decreased from the dovetail portion toward the outlet port. The final passage portion communicates with a number of film cooling holes which are open to the suction side surface of the blade portion.
    • 燃气涡轮机的叶片包括具有燕尾部分的主体和从燕尾部分延伸的叶片部分。 在主体中形成用于流动冷却空气的冷却空气通道以冷却叶片部分。 通道包括通向燕尾部分的冷却空气入口和与叶片部分的延伸尖端相通的出口。 第一通道部分沿着叶片部分的前缘从入口延伸到靠近延伸尖端的部分。 最后通道部分从燕尾部分延伸到出口。 最终通道部分的流动截面积从燕尾部分朝向出口逐渐减小。 最后的通道部分与许多对叶片部分的吸力侧表面开口的薄膜冷却孔连通。
    • 10. 发明授权
    • Remote control system
    • 遥控系统
    • US09158305B2
    • 2015-10-13
    • US13565153
    • 2012-08-02
    • Fumio OhtomoKazuki OsaragiTetsuji Anai
    • Fumio OhtomoKazuki OsaragiTetsuji Anai
    • H04N13/02G05D1/00
    • G05D1/0038G05D1/0016
    • A remote control system comprises a mobile object, a remote controller for remotely controlling the mobile object, and a storage unit where background images to simulate a driving room or an operation room of the mobile object are stored. The mobile object has a stereo camera, a camera control unit for controlling image pickup direction of the stereo camera, and a first communication unit for communicating information including at least images photographed by the stereo camera. The remote controller has a second communication unit for communicating to and from the first communication unit, a control unit for controlling the mobile object, and a display unit for synthesizing at least a part of the images photographed by the stereo camera and the background images and for displaying the images so that a stereoscopic view can be displayed.
    • 远程控制系统包括移动对象,用于远程控制移动对象的遥控器,以及存储用于模拟移动对象的驾驶室或操作室的背景图像的存储单元。 移动体具有立体摄像机,摄像机控制单元,用于控制立体摄像机的摄像方向,以及第一通信单元,用于传送至少包含由立体摄像机拍摄的图像的信息。 遥控器具有用于与第一通信单元进行通信的第二通信单元,用于控制移动体的控制单元和用于合成由立体摄像机和背景图像拍摄的图像的至少一部分的显示单元,以及 用于显示图像,使得可以显示立体视图。