Patent ID: 11959396
Assignee: RTX CORPORATION
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F  Y | IPC F

Claim 9:
10. A method of mitigating silicon recession, the method comprising:
providing a gas turbine engine article in a gas turbine engine, the gas turbine engine article includes a silicon-containing ceramic wall that has an external combustion gas path side and an internal side that borders a cooling air cavity, and an array of cooling holes that extend through the silicon-containing ceramic wall and that connect the internal side with the external combustion gas path side, wherein there is a combustion gas flow across the external combustion gas path side along an associated combustion gas flow direction; and
emitting cooling air from the array of cooling holes in a direction counter to the combustion gas flow direction, the cooling air cooling the external combustion gas path side-, shielding the external combustion gas path side from the combustion gas flow, and locally reducing velocity of the combustion gas flow to mitigate silicon recession, each of the cooling holes being comprised of a metering hole section of constant cross-sectional area and a surface breakout section that diverges from the metering hole section, the cooling holes being arranged in the array with a ligament length to cooling hole diameter of 2:1 to 8:1, the array including at least a first row of the cooling holes and a second row of the cooling holes, the surface breakout section of each of the cooling holes of the first row has a crescent geometry, and the surface breakout section of each of the cooling holes of the second row has a lobed geometry.