Hamilton Sundstrand Patente

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A fuel system for a gas turbine engine includes an augmentor pump (102) having an inlet (104) communicating with a fuel supply source and a discharge (106) communicating with an augmentation stage of the engine. An electric motor (108) is operatively connected to drive the augmentor pump for selectively activating and deactivating the augmentor pump.

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A power feeder device (100; 700) can include a base (101; 701) having a mounting portion (103; 703) and a plurality of connector structures (105; 705) extending from the mounting portion and spaced apart relative to each other to form a respective gap (107) therebetween. Each connector structure can be configured to receive a respective pair of terminals (109; 719a, 719b) to electrically connect the respective pair of terminals within connector structures and to block a line of sight between adjacent pairs of terminals. The device can also include a cover (111; 711) configured to mate with the base to enclose each of the plurality of connector structures and to increase a length of a creepage path between each pair of terminals by at least partially inserting into each gap between the connector structures. The base and the cover can be configured to form a terminal opening (113; 713) on each lateral side when assembled to allow pass-through of a conductor and/or portion of each terminal. In certain embodiments, at least one of the terminals of the respective pair of terminals can be a bus bar extending from a bus bar chassis (721) and the base and/or the cover can form a creepage barrier (723a, 723b) that extend into a chassis wall opening (725) of the bus bar chassis to increase a length of a chassis creepage path from the respective pair of terminals to the bus bar chassis.

Provided are embodiments for a circuit (400) including a resolver (402) having a primary winding and a set of secondary windings, wherein the resolver has a resolver shaft, and a polarity detection circuit coupled to the resolver. The circuit can also include a synchronizer circuit coupled to the polarity detection circuit, wherein the synchronizer circuit synchronizes signals from the positive polarity detection circuit; and a controller configured to determine a direction of the resolver shaft using an output of the synchronizer circuit. Also provided are embodiments of a method for determining the resolver rotation direction using non-analog means.

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An electrical power unit cooling system including at least one cooling fin (108) configured to be thermally connected to a bus housing (106) of the electrical power unit, the bus housing being configured to be attached to a surface (112) of an aircraft fan housing such that the at least one cooling fin protrudes through the fan housing in order to be cooled by air flow within the fan housing.

A fuel system with integrated thrust control malfunction and overspeed protection includes a centrifugal pump (102) for receiving filtered fuel and supplying fuel to a metering and pressure regulating valve, the metering and pressure regulating valve (106) for metering discharge of filtered fuel flow to a gas turbine engine burner, a shut off valve (110) downstream of the metering and pressure regulating valve movable from an open position to either a fully closed position configured for providing rapid shutoff or a partially closed position configured for reduction of fuel flow to the gas turbine engine burner, and a first solenoid (112) and a second solenoid (114) for controlling the shut off valve position.

A generator shaft assembly including a primary shaft (106), a disconnect shaft (108) housed within the primary shaft, where a first end of the disconnect shaft is configured to couple with the primary mover and a second end of the disconnect shaft is configured to mate with the generator. A retainer ring (116) housed within the primary shaft having at least a landing (118) and a groove (120) on an inner surface thereof and a retainer member (124) positioned between the landing of the retainer ring and an outer surface of the disconnect shaft configured to limit axial motion of the disconnect shaft relative to the primary shaft.

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A fuel flow system (10) for a gas turbine includes a first pump (20), a main fuel flow path (12c) and a second pump (20). The first pump (20) is connected to an actuator and a metering valve (26). The main fuel flow path (12c) is formed between the first pump (20) and the metering valve (26). The second pump (30) is connected to the main fuel flow path (12c) and supplements the fuel flow from the first pump (20) under certain conditions. The second pump (30) and first pump (20) are in parallel.

An insert (230) for a condensing heat exchanger (110), having: a body (230C) extending aft from a forward end (230A) to an aft end (230B), and defining: a body exterior surface (230D); a forward segment (240) that extends aft from the forward end of the insert to a first axial location (240A) between the forward and aft ends of the insert, along the forward segment the body exterior surface is without openings; a middle segment (250) that extends aft from the first axial location to a second axial location (250A), along the middle segment the body exterior surface is cylindrical; and an aft segment (260) that extends aft from the second axial location to the aft end of the insert, along the aft segment the body exterior surface of the body is cylindrical and defines axially extending grooves (270), and the grooves are spaced apart from each other and extend forward from the aft end of the insert to the middle segment.

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An environmental control system (12) for an aircraft according to an example of the present disclosure includes a first turbine (T1) coupled to an engine (10) and a second turbine (T2) coupled to a compressor (C). One or more ducts (16) are configured to provide bleed air from the engine to the first and second turbines and the compressor such that the first and second turbines and the compressor condition the bleed air. A method of conditioning air is also disclosed.

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