Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge, and at least one cooling cavity disposed within the platform. A pair of circumferential edges connects the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A support hook protrudes radially outward from a leading edge of the platform. A boss structure protrudes radially outward from the platform and defining a solid kinetic energy path from an inner diameter of the platform to a radially outward facing surface of the boss structure, wherein the boss structure extends less than a circumferential length of the platform.

Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.

Abstract: In one exemplary embodiment, a blade outer air seal for a gas turbine engine includes a gas path surface exposed to exhaust gas, a first side extending radially outward from the gas path surface, a second side extending radially outward from the gas path surface, an axially forward side and an axially aft side extending radially outward from the gas path surface. A plurality of film cooling holes disposed on at least one of the gas path surface, the first side, the second side, and the aft side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.

Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge, and at least one cooling cavity disposed within the platform. A pair of circumferential edges connects the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A support hook protrudes radially outward from a leading edge of the platform. A boss structure protrudes radially outward from the platform and defining a solid kinetic energy path from an inner diameter of the platform to a radially outward facing surface of the boss structure, wherein the boss structure extends less than a circumferential length of the platform.

Abstract: A blade outer air seal for a gas turbine engine includes a platform having a leading edge and a trailing edge. A pair of circumferential edges connect the leading edge and the trailing edge. An end wall protrudes radially outward from the platform at the trailing edge. A first support rib connects one of the circumferential edges to the end wall and structurally supports the end wall. A first boss portion extends axially forward from the end wall and is disposed radially outward of the first support rib.

Abstract: A blade outer air seal for a gas turbine engine is provided. The blade outer air seal having: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.

Abstract: A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.

Abstract: An assembly for use in a turbine section of a gas turbine engine, the assembly including: a blade outer air seal having a forward end and opposite aft end and a pair of opposing sides extending between the forward end and the opposite aft end; a blade outer air seal support, the blade outer air seal support having a rail with at least one scalloped opening, the rail engaging a hook located at the forward end of the blade outer air seal when the blade outer air seal is secured to the blade outer air seal support, wherein two points of contact are made between the hook and the rail of the blade outer air seal support when the blade outer air seal is secured to the blade outer air seal support; and a vane platform, that receives and supports a rail of the blade outer air seal, the rail being located at the aft end of the blade outer air seal and the rail extends continuously between the pair of opposing sides of the blade outer air seal, wherein a single point of contact is made between the rail of the blade out

Abstract: A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.

Abstract: A blade outer air seal for a gas turbine engine is provided. The blade outer air seal having: a gas path surface exposed to exhaust gas flow; a first side extending radially outward from the gas path surface; a second side extending radially outward from the gas path surface; and a plurality of film cooling holes disposed on at least one of the gas path surface, the first side and the second side, the film cooling holes disposed at locations described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate, a circumferential coordinate and a radial coordinate relative to a defined point of origin.