A method for casting a turbine blade body comprises; providing a mold defining the external geometry of the blade body; providing a core defining an internal geometry of the blade body, the core comprising a main body defining an internal chamber of the blade body and having a root end and...
法律状态 权利要求 说明书 基本信息 申请号GB19720034367申请日1972-07-21 授权公告号GB1352485(A)授权公告日- 优先权号 -优先权日 - 分类号 F01D11/08 申请人信息 申请(专利权)人 SNECMA 发明人- 地址-邮编- 代理人信息 代理机构 -代理人 -
External cooling of turbine blades by film cooling is achieved by injecting relatively cooler air from the internal coolant passages out of the blade surface in order to form a protective layer between the blade surface and hot gas-path flow. For internal cooling, this presentation focuses on ...
The tips of turbine blades experience especially large thermal loads due to hot gases flowing through the gap between blade tip and shroud at high velocity. Apart from the thermal effects, this flow across the tip increases the losses in the flow. A recessed tip – a so-called squealer tip...
A near wall cooling technique for cooling the pressure and suction sides of a turbine airfoil that includes a matrix of cells oriented chord-wise and extending longitudinally having
Turbine rotor, cooling method of turbine blades of 专利名称：Turbine rotor, cooling method of turbine blades of the rotor and gas turbine with the rotor 发明人：Ryo Akiyama,Shinya Marushima,Manabu Matsumoto 申请号：US09506811 申请日：20000218 公开号：US06334756B1 公开日：20020101 专利内容由知识产权...
Thus, it is very important to cool the turbine blades for a long durability and safe operation. Cooling the blade must include cooling of the key regions being exposed to the hot gas. The blade tip region is such a critical area and is indeed difficult to cool. This results from the ...
来源会议 Herald of the Samara State Aerospace University. Series: Problems and Perspectives of Propulsion Engineering Development. Issue 3. Part 1. Samara. 1999/01/01 研究点推荐 one-stage gas generator combined shroud cooling effectiveness film cooling turbine blades 站内活动 0...
A turbine rotor blade with a row of exit slots adjacent to a trailing edge region of the airfoil that extends from the platform to the blade tip, where the row of exit slots is form
1. A method for cooling the blades/vanes, in particular, of a main turbine (3) of a gas storage power plant (1), comprising a gas reservoir (10), in which fresh gas is stored under pressure, a main turbine (3) with associated burner (6), a recuperator (7), which contains a fre...