초록 ▼

A method for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine by channeling a substrate to provide cooling channels through the substrate having a diameter of about 0.005′ to about 0.02′ to allow passage of cooling fluid from a cooling fluid s

A method for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine by channeling a substrate to provide cooling channels through the substrate having a diameter of about 0.005′ to about 0.02′ to allow passage of cooling fluid from a cooling fluid source through the cooling channels. A bond coat of about 0.0005′ to about 0.005′ in thickness is applied to the substrate such that the bond coat partially fills the cooling channels. A porous TBC of at least about 0.003′ to about 0.01′ thick is applied over the bond coat, such that the TBC completely fills the cooling channels. Cooling fluid from a cooling fluid source is passed through the cooling channels and porous TBC. Because the channel exit is filled with TBC, the cooling fluid is transmitted through the porous passageways of the TBC. The porous passageways provide a plurality of tortuous routes to the TBC surface. The present invention further comprises both the cooled flow path surface region formed by the foregoing methods and the turbine component having a porous TBC cooling system connected to a cooling fluid source for cooling the component.

대표청구항 ▼

1. A cooling system for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine comprising:at least one channel having a first and second end, the first end terminating in an exit orifice located on a surface of a substrate, the second end in fluid c

1. A cooling system for transpiration cooling of the flow path surface region of an engine component used in a gas turbine engine comprising:at least one channel having a first and second end, the first end terminating in an exit orifice located on a surface of a substrate, the second end in fluid communication with a cooling circuit contained within a turbine engine component, wherein the channel has a diameter of about 0.0005′ to about 0.02′; a bond coat having a thickness of about 0.0005′ to about 0.005′ applied to the substrate surface, wherein the bond coat partially fills the exit orifice of the at least one channel at the first channel end; and, a TBC layer having a preselected density applied to the bond coat such that the TBC fills the remainder of the exit orifice at the first channel end, and having a thickness of at least about 0.003′ applied over the bond coat, the preselected density being sufficient to permit diffusion and discharge of a cooling fluid.