United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Scott Daniel Virkler

Michael G McCaffrey

Jonathan Perry Sandoval

Russell J Bergman

James F Wiedenhoefer

Raymond S Hummel

Matthew P Ricker

William D Blickenstaff

Eric A Hudson

Edwin Otero

David Wasserman

Ross Wilson

Daniel A Snyder

Kyle C Lana

William P Stillman

Patrick M Hart

Gordon Kinkade

Stanley J Funk

Daniel E Kane

David Richard Griffin

Julian Partyka

Jason Arnold

Jason D Himes

Tuan David Vo

Roger Gates

Dwayne K Mecklenburg

Virginia L Ross

Jason David Liles

Christopher M Juh

Jaimie Taraskevich

Jaimie Schweitzer

Ryan W Brandt

Jordan Tresser

David J Wasserman

Kyle Charles Lana

A heat exchanger for providing thermal energy transfer between first and second flows along first and second flowpaths has a plate bank having a plurality of plates. Each plate has: opposite first and second faces and leading and trailing edges along the second flowpath; a proximal edge having along the first flowpath: at least one inlet port; at least one outlet port; and at least one passageway. An inlet manifold has at least one inlet port and at least one outlet port. An outlet manifold has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold. A shroud links distal portions of the plates.

Aircraft heat exchanger panel array interconnection

A heat exchanger for providing thermal energy transfer between a first flow along a first flowpath and a second flow along a second flowpath has a plate bank having a plurality of plates, each plate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. An inlet manifold has at least one inlet port and at least one outlet port. An outlet manifold has at least one outlet port and at least one inlet port. The first flowpath passes from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold.

Aircraft heat exchanger assembly

A heat exchanger plate for provides heat transfer between a first flow along a first flowpath and a second flow along a second flowpath. The heat exchanger plate comprised a body having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath. Along a proximal portion, the first face and the second face converge at a first angle. Along a distal portion, the first face and the second face converge at a second angle less than the first angle.

Aircraft heat exchangers and plates

A rotor disk for a gas turbine engine is disclosed and formed to enable operation at high rotational speeds in a high temperature environment. The rotor disk is formed to include a bore, a live rim diameter and an outer diameter related to each other according to defined relationships.

High pressure rotor disk

A hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components. The seal includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a first beam operatively coupling the shoe to the base, the first beam having a first thickness. The seal yet further includes a second beam operatively coupling the shoe to the base, the second beam having at least a portion thereof with a second thickness that is less than the first thickness.

Hydrostatic seal with asymmetric beams for anti-tipping

A rotor assembly is provided for a piece of rotational equipment. This rotor assembly includes a rotor disk, a rotor blade and a seal element. The rotor disk is configured to rotate about a rotational axis. The rotor disk extends axially along the rotational axis to a rotor disk end face. The rotor blade includes an attachment. The attachment attaches the rotor blade to the rotor disk. The seal element is configured to seal a gap between the rotor disk and the attachment. The seal element has a longitudinal centerline that extends along an interface between the rotor disk and the attachment at the rotor disk end face.

Seal element for sealing a joint between a rotor blade and a rotor disk

A method of assembling a portion of a gas turbine engine, includes assembling a plurality of static structure rings; attaching a plurality of support straps to an outer diameter of the plurality of static structure rings to form a cartridge; inserting the cartridge at least partially into an outer case assembly along an engine axis.

Support straps and method of assembly for gas turbine engine

A hydrostatic advanced low leakage seal configured to be disposed relatively rotatable components includes a base. The seal also includes a shoe extending circumferentially. The seal further includes a beam operatively coupling the shoe to the base, the beam having a beam length that is substantially equal to or greater than a circumferential pitch of the shoe.

Hydrostatic seal with increased design space

A method of manufacturing a hydrostatic advanced low leakage seal configured to be disposed between relatively rotatable components is provided. The method includes manufacturing a plurality of separate, independent components of the seal. The method also includes assembling the plurality of separate, independent components to form the seal.

Multi-component assembled hydrostatic seal

A power turbine rotor assembly including a rotor shaft. The assembly also includes a rotor stack surrounding the rotor shaft. The assembly further includes a nut axially retaining the rotor stack. The assembly yet further includes a Vernier ring engaged with the nut and the rotor shaft, the Vernier ring having an inner ring, a plurality of inner tabs extending radially inward from the inner ring, and a plurality of outer tabs extending radially outward from the inner ring, the Vernier ring formed of at least two ring segments.

Split vernier ring for turbine rotor stack assembly

A method for assembling a seal arrangement may comprise applying an adhesive to a seal, applying a force to a shoe of the seal, and removing the force from the shoe, wherein the adhesive secures the shoe with respect to a static structure in response to the force being removed.

HALO seal build clearance methods

An example turbine includes a turbine disk and a turbine blade. The turbine disk includes a plurality of lugs and a plurality of slots. Each of the plurality of lugs is located between two of the plurality of slots. Each of the plurality of lugs includes a tab that extends radially outwardly from an end of the lug. The tab has a first section having an upper surface and a second section having an upper surface. The upper surface of the first section is inclined greater than the upper surface of the second section, and the upper surface of the first section of the tab defines a contour. The turbine blade includes a root received in one of the plurality of slots and a platform, and the platform has a lower surface defining a contour. When the turbine blade is received in one of the plurality of slots, the lower surface of the platform is located above a portion of the upper surface of the first section of the tab, and the contour of the upper surface of the first section of the tab matches the contour of the lower surface of the platform.

Turbine blade damper seal

A curvic seal for a gas turbine engine includes a cylindrical seal with a retention feature.

Curvic seal for gas turbine engine

The present disclosure provides an assembly for a gas turbine engine. The assembly may comprise a tierod, a bearing mounting ring, and a joint coupling the tierod to the bearing mounting ring. The joint may be configured to increase a volume of a bearing compartment on an inner surface of the bearing mounting ring. A coefficient of thermal expansion of the bearing mounting ring may be substantially the same as the coefficient of thermal expansion of the tierod.

Growing community of inventors

Ellington, CT, United States of America

Scott Daniel Virkler