United Technologies Corporation

Other

Raytheon Technologies Corporation

Rtx Corporation

David A Krause

Mark F Zelesky

Dominic J Mongillo, Jr

John Joseph Marcin

Carl R Verner

Joel H Wagner

Theodore W Hall

Ben S Reinert

Raymond C Surace

Jesse R Boyer

Shawn J Gregg

Jeffrey S Beattie

Daniel A Snyder

Friedrich O Soechting

Randall Joyner

Robert E Erickson

James Romanelli

John W Magowan

Kun Tong

Frank Thomas Cucinella

A casting core assembly is disclosed herein. The casting core assembly comprises a casting core and a bumper assembly. The bumper assembly is disposed on an outer surface of the casting core. The bumper assembly comprises a receptacle and a metal apparatus. The metal apparatus may be a pin, a sphere, or the like.

Integral core bumpers

A method of making an airfoil includes making a refractory metal core that defines an interior of the airfoil by a tomo-lithographic process, making a mold that defines an exterior of the airfoil, inserting the refractory metal core into the mold, and pouring an airfoil material between the refractory metal core and the mold to cast the airfoil.

Method of making airfoils

A method of making a refractory metal core includes forming two layers of the core out of a material. The layers are bonded together to form a laminate master pattern, and a flexible mold is formed around the pattern. The pattern is removed from the flexible mold, and pulverulent refractory metal material is poured into the flexible mold. The pulverulent refractory metal material is sintered to form the refractory metal core.

Apparatus for and method of making multi-walled passages in components

A method is provided for inspecting a plurality of parts with an electronic measurement device and a processing system. The method includes a step of creating surface geometry maps of the parts utilizing the electronic measurement device, where each part was manufactured utilizing the manufacturing device. Geometric part models of the parts are generated from the surface geometry maps. The part models can subsequently be analyzed to determine whether a manufacturing device that manufactured the plurality of parts manufactures parts that comply with a part design specification.

Method for inspecting a manufacturing device

A knee brace having a hinge assembly comprising an upper segment; a lower segment; a middle linking segment coupled to the upper and lower segments to permit pivotal movement of the upper segment relative to the lower segment; and one or more biasing members anchored to the upper and middle linking segments to resiliently bias the upper and middle segments toward a predetermined alignment. A series of straps connected to the hinge assembly allow attachment of the knee brace to the wearer's leg.

Knee brace

A rotor blade is provided having a hollow airfoil with a cavity and an attached root. The root has a leading edge conduit, at least one mid-body conduit, and a trailing edge conduit. Each conduit has a centerline. The leading edge conduit includes an inlet having a forward side, a suction side, and a pressure side that diverge from the centerline of the leading edge conduit, and an aft side. Each of the mid-body conduits includes an inlet having a suction side and a pressure side that diverge from the centerline of the mid-body conduit, and an aft side and a forward side. The trailing edge conduit includes an inlet having a suction side and a pressure side that diverge from the centerline of the trailing edge conduit. The trailing edge conduit inlet further includes a forward side and an aft side.

Cooled rotor blade

A blade or vane for a gas turbine engine includes a primary cooling system (42) with a series of medial passages (44, 46a, 46b, 46c, 48) and an auxiliary cooling system (92) with a series of cooling conduits (94). The conduits of the auxiliary cooling system are parallel to and radially coextensive with the medial passages and are disposed in the peripheral wall (16) of the airfoil between the medial passages and the airfoil external surface (28). The conduits are chordwisely situated in a zone of high heat load (104, 106) so that their effectiveness is optimized. The conduits may also be chordwisely coextensive with some of the medial passages so that coolant in the medial passages is protected from excessive temperature rise. The chordwise dimension C of the conduits is limited so that potentially damaging temperature gradients do not develop in the airfoil wall (16).

Turbomachinery airfoil with optimized heat transfer

A combined ski locking device and safety strap assembly that includes a riser strap affixed to the ski, a loop strap that is arranged to be closed about the skier's leg by any conventional fastener means, and a lock that cojoins the riser strap and the loop strap. In assembly, the loop strap is received in close sliding relationship within the lock and contains a pair of stop members that are spaced apart along its length to limit the extent of travel afforded the strap within the lock. A link is also secured to one end of the strap that can be united with the shackle of the lock. In practice, when used as a security device, the loop strap is first pulled to a fully extended position in the lock and the extended strap passed through the ski equipment and around a fixed object. The link is then clasped in the lock to secure the equipment.

Combination ski lock and safety strap

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Tolland, CT, United States of America

David A Krause