Hartford, CT, United States

United Technologies

www.utc.com
Hartford, CT, United States

United Technologies Corporation is an American multinational conglomerate headquartered in the United Technologies Building in Hartford, Connecticut. It researches, develops, and manufactures high-technology products in numerous areas, including aircraft engines, helicopters, HVAC, fuel cells, elevators and escalators, fire and security, building systems, and industrial products, among others. UTC is also a large military contractor, producing missile systems and military helicopters, most notably the UH-60 Black Hawk helicopter. Gregory Hayes is the current CEO. Wikipedia.

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Patent
United Technologies | Date: 2017-01-11

An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10 to 20 in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span.


Patent
United Technologies | Date: 2017-02-15

A method of additive manufacturing comprises determining a first resonant frequency of an unflawed reference workpiece at a first partial stage of completion, fabricating a production workpiece to the first partial stage of completion via additive manufacture, sensing a second resonant frequency of the production workpiece in-situ at the first partial stage of completion, during the fabrication, analyzing the workpiece for flaws based on comparison of the first and second resonant frequencies, and providing an output indicative of production workpiece condition, based on the analysis. An additive manufacturing system comprises an additive manufacturing tool, a sensor, and a controller. The additive manufacturing tool is disposed to construct a workpiece via iterative layer deposition. The sensor is disposed to determine a resonant frequency of the workpiece in-situ at the additive manufacturing tool, during fabrication. The controller is configured to terminate manufacture of the workpiece if the resonant frequency differs substantially from a reference frequency.


Patent
United Technologies | Date: 2017-01-27

A method of managing a gas turbine engine variable area fan nozzle includes the steps of operating a variable area fan nozzle according to a first operating schedule. An icing condition input is evaluated to determine the likelihood of ice presence. The first operating schedule is altered to provide a variable area fan nozzle position if ice is likely present or actually present to provide an icing operating schedule different than the first operating schedule. The first operating schedule corresponds to the flaps at least partially open at air speeds below a first airspeed. The altering step includes closing the flaps below the first airspeed as part of the icing operating schedule. The variable area fan nozzle position is adjusted according to the icing operating schedule. A fan is arranged in a fan nacelle that includes a flap configured to be movable between first and second positions. An actuator is operatively coupled to the flap.


Patent
United Technologies | Date: 2017-01-31

A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.


Patent
United Technologies | Date: 2017-05-17

An airfoil (201) of a gas turbine engine (20) is provided. The airfoil includes an airfoil body (209) having at least one internal flow passage (218), the body having a first surface (214) and a second surface (216), the first surface defining a wall of the at least one internal flow passage and a bleed port (219) fluidly connecting the at least one internal flow passage to the second surface. The bleed port includes a bleed orifice (220) extending from the second surface toward the internal flow passage and a bleed port cavity (226) extending from the first surface toward the second surface, the bleed port cavity and the bleed orifice fluidly connected. The bleed port cavity is defined by a bleed port cavity wall and a base wall surrounding the bleed orifice. The bleed port cavity wall extends from the first surface to the base wall.


Patent
United Technologies | Date: 2017-04-26

A drainage assembly (68) includes a first segment (70A) with a first inner tube (76A) defining a first inner tube passage (78A), a first outer tube (72A) concentrically disposed around the first inner tube (76A) and defining a first outer tube passage (74A), and a first fitting (80A) disposed on an end of the first segment (70A). The first fitting (80A) has a first inner passage (82A) in fluid communication with the first inner tube passage (78A) and a first outer passage (84A) in fluid communication with the first outer tube passage (74A). A plate (88) is positioned adjacent the first fitting (80A). The plate (88) has a second inner passage (90) in fluid communication with the first inner passage (82A) on one side, and a second outer passage (92) in fluid communication with the first outer passage (84A) on the one side. Also included is a drainage line (104) in fluid communication with the first outer tube passage (74A).


Patent
United Technologies | Date: 2017-09-20

A disc of a gas turbine engine (10) system with particular retaining ring (210; 310; 510; 610) placement and engagement implementation are provided. For example, the disc includes a disc hub (203; 403; 603) including a groove (233; 333; 533; 633) formed on an axially extending surface of the disc hub, wherein the groove includes a forward surface (213; 313; 413; 513; 613) that extends radially into the disc hub to a groove floor (214; 314; 414; 514; 614) that is cut into the disc hub, and wherein the groove extends axially to an aft surface (216; 316; 416; 516; 616) that extends radially outward to at least the axially extending surface of the disc hub, and a disc web (202; 602) that extends radially outward from the disc hub, relative to an axis of rotation of the gas turbine engine.


Patent
United Technologies | Date: 2017-09-20

According to one or more embodiments, a cover plate (206; 406; 506; 660) for a gas turbine engine (10) is provided. The cover plate includes a cover plate body that extends from a disc blade attachment (204; 604) radially along an outside surface of a disc web (202; 602) to a disc hub (203; 403; 603) of a disc creating a cavity between the cover plate body and the disc web of the disc, and an attachment protrusion (661) extending from the inner most end of the cover plate body toward the disc hub, and wherein the attachment protrusion is configured to engage with a retaining ring (210; 310; 510; 610).


Patent
United Technologies | Date: 2017-09-20

A seal assembly includes a seal arc segment (66) that defines first and second seal supports (70a, 70b) and radially inner and outer sides (R_(1), R_(2)) with the radially outer side (R_(2)) including radially-extending sidewalls (74) and a radially inner surface (76) that joins the radially-extending sidewalls. The radially-extending sidewalls and the radially inner surface define a pocket (78). The seal assembly includes a carriage (68) that defines first and second support members (68a, 68b) with the first support member (68a) supporting the seal arc segment in a first ramped interface (72a) and the second support member (68b) supporting the seal arc segment in a second ramped interface (72b). The radially inner surface has a higher surface roughness than the radially extending sidewalls.


Patent
United Technologies | Date: 2017-09-27

A link setting assembly (112) permitting to set the length of links for variable vanes of a gas turbine engine, before assembly to the engine. The links setting assembly according to an exemplary aspect of the present disclosure includes a fixture (114) including at least one platform mount (118, 120) and at least one linkage mount (126, 128, 130, 132). The at least one linkage mount (126...132) is spaced-apart from the platform mount (118, 120) by a distance corresponding to a predetermined link length.

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