RTX Corporation

A system for traceability of manufacturing data may include one or more processors coupled to memory. The one or more processors may be collectively operable to execute a mapping environment. The mapping environment may be operable to access a production set of manufacturing instructions associated with a component design. The mapping environment may be operable to access real manufacturing data associated with execution of the production set of manufacturing instructions. The mapping environment may be operable to generate an evaluation set of manufacturing instructions associated with respective unique identifiers. The unique identifiers may be assigned to respective geometric features of the component design. The mapping environment may be operable to generate a mapped set of manufacturing instructions including the unique identifiers assigned to respective portions of the production set of manufacturing instructions based on the evaluation set of manufacturing instructions.

A test rig with a multi-specimen fixture system including an actuator including a central shaft; a moving component in operative communication with the central shaft; a stationary component located proximate the moving component arrayed around the central shaft; a first connector coupled to the stationary component, the first connector configured to secure a test specimen; a second connector coupled to the moving component, the second connector configured to secure the test specimen; a load cell in operative communication with at least one of the first connector or the second connector; and at least one compliant element in operative communication with the moving component, wherein the at least one compliant element is configured to produce an independent load to the test specimen.

An apparatus is provided for an aircraft. This apparatus includes an electric machine (100A; 100B) and an air cooling circuit (134). The electric machine (100A; 100B) includes an electric machine rotor and an electric machine stator. The electric machine (100A; 100B) is configured to generate an electromagnetic field with the electric machine rotor and the electric machine stator. The electric machine rotor is configured to rotate about an axis (109A; 109B). The air cooling circuit (134) includes a cooling boot (142A; 142B). The air cooling circuit (134) is configured to direct air from an air source into the cooling boot (142A; 142B). The cooling boot (142A; 142B) forms an air plenum (166) with an exterior surface (174) of the electric machine (100A; 100B). The cooling boot (142A: 142B) includes a plurality of air outlets (178). The cooling boot (142A; 142B) is configured to direct the air through the air outlets (178) and into the air plenum (166) to air cool the electric machine (10A; 100B).

An apparatus is provided for an aircraft. This apparatus includes an electric machine controller (102A; 102B) and an air cooling circuit (134). The electric machine controller (102A; 102B) includes controller circuitry (114A; 114B) and a controller housing (112A; 112B). The controller circuitry (114A; 114B) is disposed within an interior of the controller housing (112A; 112B). The air cooling circuit (134) includes a cooling boot (142A; 142B). The air cooling circuit (134) is configured to direct air from an air source into the cooling boot (142A; 142B). The cooling boot (142A; 142B) forms an air plenum (168) with the electric machine controller (102A; 102B). The cooling boot (142A; 142B) includes a plurality of air outlets (172). The cooling boot (142A; 142B) is configured to direct the air through the air outlets (172) and into the air plenum (168) to air cool the electric machine controller (102A; 102B).

An aircraft assembly includes a first electric cable (124A) and an electric device (122). The electric device (122) includes a device housing (126) and a first electric terminal (156A) disposed within an internal volume (130) of the device housing (126). The device housing (126) includes a first metal sidewall (140A), a first wall cable port (150) and an open first wall aperture (152A-C) next to the first wall cable port (150). The first metal sidewall (140A) is between and borders the internal volume (130) and an external environment (148). The first wall cable port (150) projects through the first metal sidewall (140A) from the external environment (148) to the internal volume (130). The open first wall aperture (152A-C) projects through the first metal sidewall (140A) from the external environment (148) to the internal volume (130). The first electric cable (124A) projects longitudinally through the first wall cable port (150) into the internal volume (130). The first electric cable (124A) is received by and is electrically coupled to the first electric terminal (156A) within the internal volume (130).

An aircraft assembly includes a turbine engine (24), a first electric machine (100A), a first controller (102A), an electric machine fluid circuit (134A) and a controller fluid circuit (134B). The turbine engine includes a compressor section (45), a combustor section (46), a turbine section (47), a flowpath (84) and a first rotating structure (60A). The first rotating structure includes a first bladed rotor disposed in one of the compressor section or the turbine section. The first electric machine includes a first electric machine rotor (104A). The first electric machine rotor is operatively coupled to the first rotating structure. The first controller is configured to electrically couple the first electric machine to an electrical system (98). The electric machine fluid circuit is configured to circulate a first liquid and service the first electric machine. The controller fluid circuit is configured to circulate a second liquid and service the first controller. The controller fluid circuit is fluidly discrete from the electric machine fluid circuit.

An apparatus is provided for an aircraft. This apparatus includes a turbine engine (24), a first electric machine (100A), a first controller (102A), a second electric machine (102A), a second controller (102B) and a first fluid circuit (134). The first electric machine is operatively coupled to the turbine engine. The first controller is configured to control operation of the first electric machine. The second electric machine is operatively coupled to the turbine engine. The second controller is configured to control operation of the second electric machine. The first fluid circuit is configured to circulate a first liquid to cool and/or lubricate the first electric machine, the first controller, the second electric machine and the second controller.

A method for oxide formation on the surface of a ring includes: mounting a ring in a fixture (312); driving rotation of the ring about a first axis (314); contacting an outer diameter surface of the ring with a roller (340); and laser heating the outer diameter surface of the ring to form an oxide layer. The rotation causes compaction of the oxide by the roller (340).

An aircraft apparatus includes a turbine engine (24), a first electric machine (100A), a first controller (102A), a first fluid circuit (134A), a second electric machine (100B), a second controller (102B) and a second fluid circuit (134B). The turbine engine includes a first rotating structure (60A) and a second rotating structure (60B). The first electric machine is operatively coupled to the first rotating structure. The first controller is configured to control operation of the first electric machine. The first fluid circuit is configured to circulate a first liquid and service the first electric machine and the first controller. The second electric machine is operatively coupled to the second rotating structure. The second controller is configured to control operation of the second electric machine. The second fluid circuit is configured to circulate a second liquid and service the second electric machine and the second controller. The second fluid circuit is fluidly discrete from the first fluid circuit.

An aircraft assembly (20) is provided that includes a propulsor rotor, a turbine engine core (44), an inner case, a first gearbox (108A), a second gearbox (108B), a first electric machine (96A) and a second electric machine (96B). The turbine engine core (44) includes a first rotating structure (54A) and a second rotating structure (54B). The first gearbox (108A) is mounted with the inner case. The second gearbox (108B) is located remote from the inner case. The first electric machine (96A) is operatively coupled to the first rotating structure (54A) through the first gearbox (108A). The second electric machine (96B) is operatively coupled to the second rotating structure (54B) through the second gearbox (108B). The first electric machine (96A) may be configurable as a first electric motor and/or a first electric generator. In addition or alternatively, the second electric machine (96B) may be configurable as a second electric motor and/or a second electric generator.