Invention Grant
US08683814B2 Gas turbine engine component with impingement and lobed cooling hole
有权
燃气涡轮发动机部件带有冲击和裂纹冷却孔
- Patent Title: Gas turbine engine component with impingement and lobed cooling hole
- Patent Title (中): 燃气涡轮发动机部件带有冲击和裂纹冷却孔
-
Application No.: US13544257Application Date: 2012-07-09
-
Publication No.: US08683814B2Publication Date: 2014-04-01
- Inventor: JinQuan Xu
- Applicant: JinQuan Xu
- Applicant Address: US CT Hartford
- Assignee: United Technologies Corporation
- Current Assignee: United Technologies Corporation
- Current Assignee Address: US CT Hartford
- Agency: Kinney & Lange, P.A.
- Main IPC: F02C7/12
- IPC: F02C7/12

Abstract:
A gas turbine engine component includes a gas path wall having a first and second opposing surfaces and a baffle positioned along the gas path wall. The baffle has impingement holes for directing cooling fluid onto the first surface of the gas path wall. A cooling hole is formed in the gas path wall and extends from a metering section having an inlet in the first surface through a transition to a diffusing section having an outlet in the second surface. A longitudinal ridge extends along the cooling hole between the transition and the outlet. The longitudinal ridge divides the diffusing section of the cooling hole into first and second lobes.
Public/Granted literature
- US20130205794A1 GAS TURBINE ENGINE COMPONENT WITH IMPINGEMENT AND LOBED COOLING HOLE Public/Granted day:2013-08-15
Information query
IPC分类: