Turbine blade squealer tip including internal squealer tip cooling channel

• Main Authors: Weaver, John Alan, Wood, Michael, Henderkott, Joseph Peter, Moga, Corina
• Format: Patent
• Language: English
• Published: 23.05.2023
• Subjects: BLASTING; CLADDING OR PLATING BY SOLDERING OR WELDING; COMBINED OPERATIONS; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; ENGINE PLANTS IN GENERAL; HEATING; LIGHTING; MACHINE TOOLS; MACHINES OR ENGINES IN GENERAL; MECHANICAL ENGINEERING; METAL-WORKING NOT OTHERWISE PROVIDED FOR; NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES; OTHER WORKING OF METAL; PERFORMING OPERATIONS; SOLDERING OR UNSOLDERING; STEAM ENGINES; TRANSPORTING; UNIVERSAL MACHINE TOOLS; WEAPONS; WELDING; WORKING BY LASER BEAM

A gas turbine engine component may include an airfoil extending radially from a base to a blade tip, the airfoil including a pressure sidewall and a suction sidewall each extending between a leading edge and a trailing edge opposite the leading edge, an internal cooling circuit extending from the base to the blade tip; and a squealer tip. The squealer tip may include a first and a second squealer tip rail adjacent to the first squealer tip rail, and a squealer tip cap extending between the first and second squealer tip rails. The blade tip, the first and second squealer tip rails, and the squealer tip cap may define an internal squealer tip cooling channel. The blade tip may define a supply aperture that fluidly connect the internal cooling circuit and the internal squealer tip cooling channel.