초록 ▼

The present invention provides for cooling the squealer tip region of a high pressure turbine blade used in a gas turbine engine comprising coating the squealer tip with a metallic bond coat. Micro grooves oriented in the radial direction are fabricated into the airfoil on the interior surface of th

The present invention provides for cooling the squealer tip region of a high pressure turbine blade used in a gas turbine engine comprising coating the squealer tip with a metallic bond coat. Micro grooves oriented in the radial direction are fabricated into the airfoil on the interior surface of the squealer tip above and substantially perpendicular to the tip cap. A micro groove oriented in the axial direction is fabricated along the joint corner between the squealer tip side wall and the, tip cap to connect and act as a plenum with all of the micro grooves oriented in the radial direction. Tip cap cooling holes are drilled through the tip cap and connected to the micro groove that ultimately forms a plenum. TBC ceramic is then deposited on both blade external surfaces and the tip cavity, forming micro channels from micro grooves as a result of self shadowing. In this manner, cooling fluid passes from a cooling fluid source through the tip cap holes and into the plenum created by the micro channel, subsequently passing into the micro channels that are oriented in the radial direction. Cooling fluid is thereby directed through the micro channels to cool the squealer, exiting in the vicinity of the tip. Since the TBC is porous, some of the cooling fluid will also flow through the TBC to provide transpiration cooling. The present invention further comprises both the cooled blade and squealer tip region formed by the foregoing methods and the blade and squealer tip with the micro channels for cooling the squealer tip.

대표청구항 ▼

1. A cooling system for cooling of a squealer tip of a high pressure turbine blade used in a gas turbine engine comprising:a superalloy tip cap; a superalloy squealer tip extending outward in an engine radial direction from the superalloy tip cap into a hot gas stream of the engine; at least one flu

1. A cooling system for cooling of a squealer tip of a high pressure turbine blade used in a gas turbine engine comprising:a superalloy tip cap; a superalloy squealer tip extending outward in an engine radial direction from the superalloy tip cap into a hot gas stream of the engine; at least one fluid supply channel having a first and second end, the first end terminating in a tip cap hole located on a surface of the tip cap, the second end in fluid communication with a cooling circuit located within the blade, wherein the at least one fluid supply channel has a diameter to permit an effective flow of cooling fluid; a bond coat having a thickness of about 0.0005′ to about 0.005' applied to the tip cap surface; at least one structured micro channel oriented in a radial direction formed by shadowing a thermal barrier coating (TBC) onto a structured micro groove, said micro groove fabricated in a plane substantially parallel to the plane of the substrate surface in a generally radial direction on an interior surface of the squealer tip above and substantially perpendicular to the tip cap in fluid communication with the at least one fluid supply channel; at least one structured micro channel oriented in an axial direction formed by shadowing a TBC onto a structured micro groove fabricated in a plane substantially parallel to the plane of the substrate surface at a joint corner between the squealer tip and the tip cap, such that the structured micro groove oriented in the axial direction and the resultant axially oriented micro channel is in fluid communication with the at least one structured micro groove oriented in the radial direction and resultant axially oriented micro channel and the tip cap hole; and, a means for providing cooling fluid to the tip cap hole.