Invention Grant
- Patent Title: Cooled turbine blade for gas turbine engine
- Patent Title (中): 用于燃气轮机的冷却涡轮叶片
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Application No.: US13693649Application Date: 2012-12-04
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Publication No.: US09435210B2Publication Date: 2016-09-06
- Inventor: Jean-Luc Bacha , Emmanuel Berche , Tangi Brusq
- Applicant: SNECMA
- Applicant Address: FR Paris
- Assignee: SNECMA
- Current Assignee: SNECMA
- Current Assignee Address: FR Paris
- Agency: Oblon, McClelland, Maier & Neustadt, L.L.P
- Priority: FR1161206 20111206
- Main IPC: F01D5/14
- IPC: F01D5/14 ; F01D5/20 ; F01D25/12

Abstract:
A cooled turbine blade for a gas turbine engine including a pressure surface wall, a suction surface wall and a distal wall connecting the pressure surface wall and the suction surface wall, arranged so as to create in the region of the distal end of the blade at least one external cavity forming a bathtub-shaped cavity and at least one internal cavity separated by the distal wall, the blade having at least one opening for the introduction of a flow of cooling air into the external cavity, wherein, on the one hand, at least one part of the distal wall is inclined relative to the verticals of the pressure surface wall and, on the other hand, the opening is created in the vicinity of the distal wall so that the flow of cooling air is directed towards the distal end of the pressure surface wall.
Public/Granted literature
- US20130142668A1 COOLED TURBINE BLADE FOR GAS TURBINE ENGINE Public/Granted day:2013-06-06
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