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

Gas turbine engine component with impingement and lobed cooling hole
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.
Information query
Patent Agency Ranking
0/0