Hamilton Sundstrand Patente

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A heat exchanger element includes a body (202) and at least one deformable surface feature disposed at an outer body surface (206) of the body. A cross-section of the heat exchanger element is oriented parallel to a cross-sectional plane of the heat exchanger element. At least one of the body (202) and the at least one surface feature is configured to selectively respond to a temperature change such that a physical characteristic of the heat exchanger element changes in response to a temperature change. The physical characteristic is selected from the group consisting of: a shape of the heat exchanger element, a surface area of the heat exchanger element, a surface roughness of the heat exchanger element, and combinations thereof.

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A solid-state power controller (SSPC) system with a built-in-test circuit includes a SSPC field-effect transistor (FET) switch (104). The system includes a current sense resistor (106) electrically connected to the SSPC FET switch in series. A resistor (108) is electrically connected to the current sense resistor in series. A switch (110) is electrically connected to the resistor in series. A method for testing a current sense resistor value in a solid-state power controller (SSPC) system includes determining a cycle count, generating a new bit with a processing unit, and outputting the new bit to a switch operatively connected to the processing unit to at least one of turn the switch on or turn the switch off. The method includes reading a load current with the processing unit to determine whether a current sense resistor electrically coupled to the switch is operating within a desired resistance range.

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An assembly and a method for manufacturing an assembly for transmitting torque to an aircraft actuator. The assembly and method include a torque tube (105) having a longitudinal axis and an end fitting (301). The ending fitting includes a connector portion (303) and an engagement portion (302) that is inserted into the torque tube. The engagement portion includes a first end (304) adjacent the connector portion, a second end (308) opposite the first end, and a coupling region between the first and second end that includes an outer coupling surface having an outer diameter and a continuous groove (307) formed thereon. The continuous groove includes two axial grooves (310) that extend along the outer coupling surface along the longitudinal axis and a first parallel groove (111) that extends circumferentially about the longitudinal axis along the outer coupling surface that joins the two axial grooves.

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A heat exchanger header includes a primary fluid duct (30) extending between a fluid port (13) and a first branched region (32), a plurality of secondary fluid ducts (34) fluidly connected to the primary fluid duct (30) at the first branched region (32), wherein an overhang region (28) is formed laterally between adjacent ones of the plurality of secondary fluid ducts (34), and wherein each of the plurality of secondary fluid ducts (34) extends between the first branched region (32) and a second branched region (36), a plurality of tertiary fluid ducts (38) fluidly connected to each of the plurality of secondary fluid ducts (34) at the second branched regions (36), a primary horn (18) integrally formed with and extending from the overhang region (28), an at least one secondary horn (20) integrally formed with and extending from one of the plurality of tertiary fluid ducts (38), and a sacrificial support structure (22) extending between the primary horn (18) and the at least one secondary horn (20).

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A sealing arrangement for a shaft (214) according to an example of the present disclosure includes a shaft and a sealing assembly. The sealing assembly includes a seal cartridge (302) that has at least one sealing element. The first and second mating rings (306, 308) are configured to axially locate the seal cartridge (302) with respect to the shaft. The second mating ring (308) includes at least one tang (312) that is configured to extend through at least one corresponding slot (313) in the shaft, the at least one tang (312) is configured to engage a retaining ring to axially retain the second mating ring on the shaft. A gearbox/accessory interface assembly and a method of sealing a gearbox with respect to an accessory are also disclosed.

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In accordance with at least one aspect of this disclosure, a flow control device (100, 200, 300, 400, 500) can include, a first plate (102, 202) having one or more windows (104, 204) defining a flow path therethrough, a second plate (108, 208) configured to abut the first plate, and an actuator (110, 210, 510) operatively connected to one or more of the first plate and/or the second plate. The actuator can be configured to drive the first plate and/or the second plate relative to one another to enlarge or reduce the flow path through the one or more windows in the first plate.

An actuator system can include a first actuator (101a), a second actuator (101b), a first actuator control device (103a) configured to control the first actuator, a second actuator control device (103b) configured to control the second actuator, a shared redundant actuator control device (103c), and at least one transfer device (105) operatively connected to the first, second, and shared redundant actuator control devices. The at least one transfer device can be configured to be operated to select between a first control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, a second control mode where the shared redundant actuator control device is operatively connected to the first actuator to control the first actuator and the second actuator control device is operatively connected to the second actuator to control the second actuator, and a third control mode where the first actuator control device is operatively connected to the first actuator to control the first actuator and the shared redundant actuator control device is operatively connected to the second actuator to control the second actuator.

An engine compressor bleed system of an engine for an aircraft is provided including a plurality of compressor pressure ports (204, 206, 208) configured to supply bleed air to satisfy a cooling load for at least a first stage of a flight profile of an aircraft. A first pressure port of the plurality of compressor pressure ports (204, 206, 208) is configured to provide bleed air having a pressure at least equal to a cabin pressure of an aircraft and a temperature that does not exceed a predetermined threshold.

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