RTX Corporation Patente

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A switch housing body (41) has a base (48) and a sidewall (50) having an axis (510) and extending from the base (48) to a rim (52) and having a pair of axial slots (70). A switch cap (34) has: a cap body (80) having a top web (82); and a sidewall (84) extending from the top web (82) to a rim (86) and having a pair of holes (106). A shaft (120) passes through the pair of axial slots (70) and pair of holes (106). A spring (42) biases the cap (34) axially away from the housing (40) from a compressed condition to an extended condition. A cap electrical contact (142) and a housing electrical contact (140) have an electrically closed condition at the compressed condition.

An assembly for use with a gas turbine engine (20) includes a block housing (74), a main bell crank (90), a bell crank (130), and a sync rod (94). The main bell crank extends between a main bell crank first end (100) and a main bell crank second end (102) that is connected to an actuator (72). The bell crank (130) extends between a bell crank first end (132) and a bell crank second end (134) that is pivotally supported by the block housing. The sync rod is connected the main bell crank first end and the bell crank first end. The sync rod defines a first tab (180) disposed proximate a first side and extends beyond a face of the sync rod.

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A system (64) of a machine includes a network of nodes (68a, 68b) distributed throughout the machine. Each of the nodes (68a, 68b) is operable to communicate through electromagnetic signals. The system (64) also includes a radio frequency transceiver (204), a first antenna (206) coupled to the radio frequency transceiver (204), a second antenna (208) coupled to one or more sensor nodes (68b), and a controller (66) coupled to the radio frequency transceiver (204). The controller (66) is configured to select at least one sensor node (68b) to interrogate, transmit one or more interrogation frequencies from the radio frequency transceiver (204) through the first antenna (206) to the second antenna (208), receive one or more sensor frequencies at the first antenna (206) broadcast from the second antenna (208) based on a frequency response of the at least one sensor node (68b) to the one or more interrogation frequencies, and determine one or more sensed values based on the sensor frequencies received at the radio frequency transceiver (204) through the first antenna (206).

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An assembly (60) and a method for forming a gas turbine engine (20) includes a layup tool (62) including a main body (MB) extending along a longitudinal axis (X) and a flange (68) extending radially from the main body (MB), the flange (68) defining an edge face (68E) slopes towards the main body (MB) to an axial face (68A). At least one compression tool (64) has a tool body (70) having a first tool section (72) and a second tool section (74) extending transversely from the first tool section (72). The first tool section (72) is translatable along a retention member (76) in a first direction (D1) substantially perpendicular to the edge face (68E) such that relative movement causes the second tool section (74) to apply a first compressive force (CI) on a composite article trapped between the axial face (68A) of the flange (68) and the second tool section (74).

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An apparatus for sealing a circumferential gap between a stationary component and a rotating member (303) is disclosed. The rotating member (303) is configured to rotate about a longitudinal axis (X-X') and has a radially outer surface (368) disposed at a first non-zero angle (370) with respect to the longitudinal axis (X-X'). The apparatus includes a stator disposed circumferentially about the longitudinal axis (X-X') and a shoe (204; 304; 404a) configured for translation in a radial direction with respect to the stator. The shoe (204; 304; 404a, 404b) includes a circumferential surface (364) and a plurality of protrusions (366; 466a, 466b) extending radially inward from the circumferential surface (364)toward the rotating member (303), each one of the plurality of protrusions (366; 466a, 466b) having a length configured to maintain a clearance gap (469a, 469b) with respect to the rotating member (303).

A blade repair apparatus (401) is provided and includes a deposition head (420; 720; 110) which is movable relative to base materials (411; 711; 1112) and configured to execute a repair operation that includes a deposition of additional materials (421; 721; 1121) onto the base materials (411; 711; 1112) during deposition head (420; 720; 110) movements, a temperature control system (430) including a temperature regulating assembly (431) coupled with the deposition head (420; 720; 110) in a trailing position and a controller (440). The controller (440) is operably coupled to the deposition head (420; 720; 110) and the temperature control system (430). The controller (440) is configured to control the deposition head (420; 720; 110) movements and depositional operations of the deposition head (420; 720; 110). The controller (440) is configured to control the temperature control system (430) such that the temperature regulating assembly (431) controls temperatures of at least the base materials (411; 711; 1112) and the additional materials (421; 721; 1121) during at least the deposition head (420; 720; 110) movements and the depositional operations.

A chemical vapor infiltration and deposition (CVI/CVD) reactor assembly (10) includes a CVI/CVD reactor (12) and a reactant gas feed source (48). The CVI/CVD reactor (12) includes a first inlet (14) at a first end of the CVI/CVD reactor (12), a second inlet (16) at a second end of the CVI/CVD reactor (12) opposite the first end, a first outlet (18) at the second end, a second outlet (20) at the first end, and a chamber (22) in fluid communication with the first and second inlets (14, 16) and first and second outlets (18, 20) and configured to hold a substrate (80). The reactant gas feed source (48) is interchangeably and fluidly connected to the first and second inlets (14, 16) by first and second valved gas lines (54, 56), respectively.

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A blade or vane has: an airfoil having an inner diameter (ID) end and an outer diameter (OD) end and having a suction side and a pressure side and a leading edge and a trailing edge; and an inner platform and/or attachment root at the ID end and/or an outer platform at the OD end. At least one of the inner platform, root, and/or outer platform comprises one or more pieces of a first alloy. One or more pieces of a second alloy form a leading edge section of the airfoil. One or more pieces of a third alloy form a trailing edge section of the airfoil. One or more pieces of a fourth alloy form a spar of the airfoil between the leading edge section and trailing edge section and extending into said at least one of the inner platform, root, and/or outer platform.

A gas turbine engine (400) includes a compressor section, a combustor section, a turbine section, a nozzle section, and the compressor section, the combustor section, the turbine section, and the nozzle section define a core flow path that expels through the nozzle section. The gas turbine engine further includes a waste heat recovery system (402) including a heat recovery heat exchanger (432) arranged at the nozzle section, wherein the heat recovery heat exchanger (432) is arranged within the nozzle section such that the heat recovery heat exchanger (432) occupies less than an entire area of an exhaust area (548) of the nozzle section and a heat rejection heat exchanger (428) arranged to reduce a temperature of a working fluid of the waste heat recovery system (402).