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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.


Patent
United Technologies | Date: 2015-06-10

An airfoil for a gas turbine engine is disclosed. The airfoil may include a leading edge, a sheath on the leading edge; and a grounding element connected to the sheath. The grounding element may have a radially extending tab, and may be configured for connection to a component of the gas turbine engine to form a ground path from the sheath to the component.


Patent
United Technologies | Date: 2015-06-08

The gas turbine component showerhead cooling hole layouts described herein include minimal lateral cooling hole exit diffusion on the middle showerhead cooling hole rows and interior facing sides of outer rows. In this way, rows of cooling holes may be placed close together. Stated another way, the outer showerhead cooling hole rows substantially only include lateral cooling hole exit diffusion in the direction away from the other rows to again allow the rows to be placed close together.


Patent
United Technologies | Date: 2015-07-16

A gas turbine engine component has a cooling hole with a metering section. The metering section includes a convex surface and a concave surface, with a first arcuate channel connecting an end of the convex surface and an end of the concave surface. The end of the convex surface and the end of the concave surface define a dimension that is smaller than a diameter of the arcuate channel.


Patent
United Technologies | Date: 2015-07-08

A gas turbine engine blade containment system is disclosed. The blade containment system may include a generally cylindrical casing being made of a first material, and a generally cylindrical ring being made of a second material coaxially surrounding the casing, at least some portion of the ring metallurgically bonded to the casing.


Patent
United Technologies | Date: 2015-07-20

A turbomachine blade can include a blade root defining a plurality of feather seal slots on a lateral portion thereof. The plurality of seal slots includes two leg slots, each leg slot extending radially, and a cross member slot extending axially. An airfoil portion extends radially from the blade root.

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