RTX Corporation

An assembly includes a first powerplant component (142A), a second powerplant component (142B), a first inter-circuit heat exchanger (152), a first fluid circuit (144A) and a second fluid circuit (144B). The first fluid circuit (144A) is configured to service the first powerplant component (142A) using a first working fluid in the first fluid circuit (144A). The first fluid circuit (144A) includes a first circuit reservoir (150A), a first circuit pump (158A) and a first circuit path (148A) extending through the first circuit reservoir (150A), the first circuit pump (158A) and the first inter-circuit heat exchanger (152). The second fluid circuit (144B) is fluidly independent of the first fluid circuit (144A). The second fluid circuit (144B) is configured to service the second powerplant component (142B) using a second working fluid in the second fluid circuit (144B). The second fluid circuit (144B) includes a second circuit reservoir (150B), a second circuit pump (158B) and a second circuit path (148B) extending through the second circuit reservoir (150B), the second circuit pump (158B) and the first inter-circuit heat exchanger (152).

A method of inspecting a thin walled structure (100) includes the steps of manufacturing, using PBF-L or PBF-EB techniques, a primary structure wall (104) connected to a shielding wall (102) with a plurality of support pins (106) that extend from the shielding wall (102) to the primary structure wall (104), wherein the primary structure wall (104) includes primary structure wall outer and inner surfaces (104a, 104b) and the shielding wall (102) includes shielding wall outer and inner surfaces (102a, 102b); creating, using a vision inspection system, one or more inspection images of the thin walled structure (100), and analyzing the one or more inspection images to determine if any of the shielding wall outer surface (102a) and shielding wall inner surface (102b) and primary structure wall outer surface (104a) and primary structure wall inner surface (104b) exhibit planar surface distortions that exceed tolerances.

An assembly is provided for an aircraft powerplant (20). This assembly includes an engine case (78), an engine core (48), an electric machine (100) and a shield (140). The engine core (48) is housed within the engine case (78). The engine core (48) includes a compressor section (43), a combustor section (44) and a turbine section (45). The electric machine (100) is disposed outboard of and mounted with the engine case (78). The electric machine (100) includes an electric machine rotor (104), an electric machine stator (106) and an electric machine case (108). The electric machine rotor (104) is housed within the electric machine case (108) and is rotatable about an axis (110). The electric machine stator (106) is housed within the electric machine case (108) and is next to the electric machine rotor (104). The shield (140) is disposed between the electric machine case (108) and the engine case (78). The shield (140) extends axially along and partially circumferentially about the electric machine (100).

A fabric reinforced seal assembly, comprising a substrate; a seal (100) comprising a fabric (108) having a first side (102) facing the substrate, a second side (104) facing away from the substrate and a thickness defined between the first side (102) and the second side (104), and an elastomer (106) infiltrated into the fabric (108) from the second side (102) toward the first side (102), wherein the elastomer (106) extends into the fabric (108) from the second side (104) for a distance of less than or equal to 50% of the thickness of the fabric (108).

An assembly for an aircraft powerplant (20) includes a transmission (204), a first powerplant component (142C), a second powerplant component (142D), a first fluid circuit (146A) and a second fluid circuit (146B). The first fluid circuit (146A) is configured to: cool and/or lubricate the first powerplant component (142C); and provide a first working fluid to the transmission (204) to hydraulically actuate the transmission (204). The first fluid circuit (146A) includes a first circuit reservoir (186A), a first circuit pump (194A) and a first circuit path (184A) extending through the first circuit reservoir (186A), the first circuit pump (194A) and the transmission (204). The second fluid circuit (146B) is configured to: cool and/or lubricate the second powerplant component (142D); and provide a second working fluid to the transmission (204) to hydraulically actuate the transmission (204). The second fluid circuit (146B) includes a second circuit reservoir (186B), a second circuit pump (194B) and a second circuit path (184B) extending through the second circuit reservoir (186B), the second circuit pump (194A) and the transmission (204).

An assembly is provided for an aircraft powerplant (20). This assembly includes an electric machine (106A), an electric machine controller (180A), an electric cable (124), a conduit (142) and an air circuit (168). The electric machine controller (108A) is configured to control operation of the electric machine (106A). The electric cable (124) electrically couples the electric machine controller (108A) to the electric machine (106A). The conduit (142) extends longitudinally from a first end (144) of the conduit (142) to a second end (146) of the conduit (142). The electric cable (124) extends longitudinally through a bore of the conduit (142). The air circuit (168) is configured to cool the electric cable (124) within the conduit (142) using a flow of air. The air circuit (168) includes the bore of the conduit (142).

An assembly is provided for an aircraft powerplant (20). This assembly includes a first powerplant component (106A; 108A), a second powerplant component (106B; 108B), a third powerplant component (144) and a fluid system (36). The fluid system (36) includes a first fluid circuit (142A), a second fluid circuit (142B), a third fluid circuit (142C) and a heat exchanger (154). The first fluid circuit (142A) extends through the heat exchanger (154) and is configured to service the first powerplant component (106A; 108A). The second fluid circuit (142B) extends through the heat exchanger (154) and is configured to service the second powerplant component (106b; 108B). The third fluid circuit (142C) extends through the heat exchanger (154) and is configured to service the third powerplant component (144). The heat exchanger (154) is configured as or otherwise includes a radiator (162).

An air-cooled turbine component (88) includes a body (90) extending between and to a first radial surface (112) and a second radial surface (114) relative to a centerline axis (74). The body includes an outer passage wall (126) and an inner passage wall (128) forming an internal cooling passage (116) between the first radial surface and the second radial surface. The internal cooling passage extends lengthwise through the body between and to an upstream end (120) of the internal cooling passage and a downstream end (122) of the internal cooling passage along a lengthwise axis (118) of the internal cooling passage. The internal cooling passage includes a first passage segment (132) and at least one second passage segment (130). The first passage segment has a first height (H2) between the outer passage wall and the inner passage wall. The at least one second passage segment has a second height (H1) between the outer passage wall and the inner passage wall. The second height is greater than the first height. The at least one second passage segment is disposed on one or both of the upstream end or the downstream end.A blade outer air seal (BOAS) segment (88) is the air-cooled turbine component.A method is provided for forming an outlet aperture (140) of the BOAS segment (88).

An air-cooled turbine component includes a body (90) extending between and to a first radial surface (114) and a second radial surface (112) relative to a centerline axis (74). The body forms an internal cooling passage (116), a supply orifice (130), and a supply plenum (132) interconnected in fluid communication. The internal cooling passage is disposed between the first radial surface and the second radial surface. The internal cooling passage is formed by and radially between an inner passage wall (120) and an outer passage wall (118) of the body. The internal cooling passage includes an enclosed passage segment (122) and a downstream passage segment (126), the enclosed passage segment extending to a terminal end (124) formed by the body. The supply orifice extends between and to an inlet (136) of the supply orifice and an outlet (138) of the supply orifice along an orifice axis (134). The inlet is disposed at the second radial surface. The outlet is disposed at the supply plenum. The orifice axis extends obliquely relative to the inner passage wall and the outer passage wall, the orifice axis extending toward the enclosed passage segment in a direction from the inlet to the outlet. The supply plenum is disposed between and connects the internal cooling passage and the supply orifice together in fluid communication. The supply plenum is disposed between the enclosed passage segment and the downstream passage segment. A blade outer air seal (BOAS) (86) include a plurality of BOAS segments (88) assembled together in circumferential series about a BOAS axis (74), each of the BOAS segments being the air-cooled turbine component. A turbine section (60) of a gas turbine engine (22) includes a bladed turbine rotor (66) configured for rotation about a rotational axis (74), the bladed turbine rotor including a rotor stage (76), the rotor stage including a plurality of rotor blades (80); and the BOAS.

An air-cooled turbine component (80) includes a body (90) extending between and to a first radial surface (112) and a second radial surface (114) relative to a centerline axis (74). The body (90) includes an outer passage wall (126) and an inner passage wall (128) forming an internal cooling passage (116) between the first radial surface (112) and the second radial surface (114). The internal cooling passage (116) extends lengthwise through the body between and to an upstream end (120) of the internal cooling passage (116) and a downstream end (122) of the internal cooling passage (116) along a lengthwise axis (118) of the internal cooling passage (116). The body forms a flow augmentation feature assembly (134) at the inner passage wall (128) within the internal cooling passage (116). The flow augmentation feature assembly (134) includes a plurality of trip strips (144) arranged in a lattice pattern (146) along the inner passage wall (128).Blade outer air seal (BOAS) segments are provided as the air-cooled turbine component.