RTX Corporation Patente

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Aircraft engines include a turbine engine (400) comprising a compressor section (404), a burner section (406), and a turbine section (408) arranged along a shaft (420), with a core flow path (420) through the turbine engine (400) such that exhaust from the burner section (406) passes through the turbine section (408), a condensing assembly (416) arranged downstream of the turbine section (408) of the turbine engine (400) along the core flow path (420), and an exhaust compressor (432) arranged downstream of the condensing assembly (416) along the core flow path (420). The condensing assembly (416) is configured to reduce a mass flow of the exhaust compressor (432) by condensing water vapor from the core flow (420) and removing liquid water from the core flow.

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An aerospace part (10), which is made from a base material, repairing using directed energy deposition (DED) techniques. The aerospace part (10) is inspected to identify a worn or defective repair region (24) on a repair feature (14) that requires repair. An intervening feature (12) that blocks line-of-sight from a DED laser/powder head (18) to the repair region (24) on the repair feature (14) is removed such that after removal of the intervening feature (12) there is line-of-sight from the DED laser/powder head (18) to the repair region (24) on the repair feature (14). a repair procedure is performed on the repair region (24) of the repair feature (14) using the DED laser/powder head (18). A replacement intervening feature (12) is obtained and attached to the aerospace part (10) to complete a desired repair. The aerospace part (10) is returned to service after completion of the desired repair.

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An engine system includes a gas turbine engine and an actuation system (26). The gas turbine engine includes a compressor section, a combustor section, a turbine section (39) and a flowpath (34) extending through the compressor section, the combustor section and the turbine section (39). The actuation system (26) includes a fluid reservoir (108), a flow regulator (112) and a flow circuit (110). The flow regulator (112) is configured as or otherwise includes a barrier between the fluid reservoir (108) and the flow circuit (110). The flow regulator (112) is configured to fluidly decouple the fluid reservoir (108) from the flow circuit (110) when the barrier is intact. The flow regulator (112) is configured to fluidly couple the fluid reservoir (108) with the flow circuit (110) when the barrier breaks. The flow circuit (110) is configured to direct gas from the fluid reservoir (108) into the flowpath (34) when the barrier breaks.

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An apparatus measures clearances between a rotating structure (102) within a fixed surrounding structure (106). A position detector (234) determines when at least one portion of the rotating structure (102) rotates past a hole (216) defined in the fixed surrounding structure (106) and generates an actuation signal responsive to rotation of the at least one portion of the rotating structure (102) past the hole (216) defined in the fixed surrounding structure (106). White light interferometer circuitry reflects a white light beam (208) off of at least one portion of the rotating structure (102) responsive to the actuation signal to determine a clearance between the at least one portion of the rotating structure (102) and an inner surface (112) of the fixed structure (106). The actuation signal actuates the white light interferometer circuitry to reflect the white light beam (208) off of the at least one portion of the rotating structure (102) through the hole (216) defined in the fixed surrounding structure (102).

An inspection method is provided during which a distal end (62) of a guide tube (56) is inserted into an interior (26) of a powerplant (24). The powerplant (24) includes a component (22) within the interior (26) of the powerplant (24). A flexible section (70) of the guide tube (56) is bent within the interior (26) of the powerplant (24). An inspection scope (28) is passed longitudinally through a bore of the guide tube (56), and a head (40) of the inspection scope (28) is abutted against a surface (54) of the component (22). The head (40) of the inspection scope (28) includes an actuator (42). The distal end (62) of the guide tube (56) is spaced from the surface (54) of the component (22). Vibrations are induced in the component (22) using the actuator (42). A vibratory response is measured in the component (22) excited by the vibrations using a sensor (44) to provide sensor data.

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A method of weld repairing an original part (28) includes inspecting the original part (28) to identify a worn or defective feature requiring repair, removing from the original part (28) the worn or defective feature requiring repair, fabricating a replacement feature (26), joining the replacement feature (26) to the original part (28) to complete a desired repair, and returning the original part (28) to service after completion of the desired repair. The replacement part is made with a powder beam fusion (PBF) technique. The replacement feature (26) is joined to the original part (28) using a directed energy deposition (DED) joining technique. The original part (28) and replacement feature (26) are made from a base material. The DED joining technique uses the base material to join the replacement feature (26) to the original part.

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An aircraft propulsion system includes aircraft systems (304) having at least one hydrogen tank (332) and an aircraft-systems heat exchanger (358) and engine systems having at least a main engine core, a high pressure pump (316), a hydrogen-air heat exchanger (324), and a turbo expander assembly. The main engine core includes a compressor section, a combustor section having a burner (310), and a turbine section. Fuel is supplied from the at least one fuel tank (332) through a fuel flow path (344), passing through the aircraft-systems heat exchanger (358), the high pressure pump (316), the hydrogen-air heat exchanger (324), and selectively through the turbo expander assembly, prior to being injected into the burner (310) for combustion. The turbo expander assembly is operably coupled to at least two load sources through a selective coupler and configured to selectively drive operation of the at least two load sources.

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