United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Jeffrey Michael Jacques

Edwin Otero

John E Paul

Michael G McCaffrey

John R Farris

Ross Wilson

Elizabeth F Vinson

Theodore W Hall

Jeffrey S Beattie

John J Korzendorfer

Alan W Stoner

Scott D Lewis

Bret M Teller

Brandon M Rapp

Mark F Zelesky

Ricardo Trindade

Benjamin F Hagan

Emma J Place

Mohamed Hassan

Bryan P Dube

Russell J Bergman

Matthew Andrew Hough

Ryan Alan Waite

Justin D Piggush

Francis R Moon

Daniel P Preuss

Charles Thistle

Peter Balawajder

Nicholas J Madonna

Justin M Aniello

Kristopher K Anderson

Carlos Calixtro

Claude I Barnett

Max Asterlin

Vladimir Skidelsky

Matthew B DeGostin

Pedro D Laureano

Daniel Belotto

John W Korzendorfer

Anthony C Evans

Joshua W Richards

Andrew Correia

Bernard Joseph Reilly, Iii

Christina A Ryan

William R Hackbarth, Ii

Melissa Shallcross

John R Korzendorfer

An attachment root for a blade includes a symmetric serration profile with multiple lobes. Contact surfaces of each lobe form equal contact angles with a line normal to a symmetry plane of the serration profile. Non-contact surfaces of lobes form angles greater than three degrees relative to the line that increase in a radially inward direction.

Turbine airfoil attachment with serration profile

A damper seal for a gas turbine engine includes a damper body extending in a first direction between a leading edge portion and a trailing edge portion, extending in a second direction between first and second sidewalls, and extending in a third direction between a convex outer damper face and a concave inner damper face. The inner damper face establishes a damper pocket. The leading and trailing edge portions slope inwardly from opposite ends of the damper body to bound the damper pocket in the first direction. The first and second sidewalls extend from the leading edge portion to the trailing edge portion and slope inwardly from opposite sides of the damper body to bound the damper pocket in the second direction. The outer damper face is pre-formed according to a first predetermined geometry that substantially corresponds to a second predetermined geometry of a platform undersurface bounding a neck pocket of an airfoil. A method of damping for a gas turbine engine is also disclosed.

Bathtub damper seal arrangement for gas turbine engine

A seal for a gas turbine engine includes a full hoop outer ring, a shoe coupled to the full hoop outer ring via an inner beam and an outer beam, and a wave spring in contact with at least one of the inner beam or the outer beam.

Non-contacting dynamic seal

A damper seal for a turbine blade of a gas turbine engine, the damper seal having: an upper portion; a first downwardly curved portion; and a second downwardly curved portion, the first downwardly curved portion and the second downwardly curved portion extend from opposing end regions of the upper portion, the upper portion having a length extending between the opposing end regions of the upper portion and a width transverse to the length, wherein the upper portion is curved along the entire width as it extends along the length.

Pre-formed faceted turbine blade damper seal

A seal support structure is provided for a circumferential seal. In one embodiment, the seal support structure includes an engine support structure, a seal support, and a shoulder joining the engine support and seal support. The shoulder offsets the engine support from the seal support, and the shoulder and the seal support structure are configured to dampen vibration for the circumferential seal. The seal support structure may employ one or more dampening elements or materials to interoperate with a seal support structure to dampen vibration to a seal system.

Seal support structure for a circumferential seal of a gas turbine engine

A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.

Seal ring

Vane assemblies are described. The vane assemblies include a platform, an airfoil extending from the platform, a forward rail extending from the platform and arranged along a forward side of the platform, and an aft rail extending from the platform and arranged along an aft side of the platform. At least one support beam is provided extending in a forward-aft direction between the forward rail and the aft rail and separated from the platform by a first distance. The at least one support beam has a thickness in a radial direction of 40% or less of a total radial extent from the platform to an outer diameter edge of at least one of the forward rail and the aft rail and the at least one support beam has a thickness in a circumferential direction of 30% or less of a total circumferential extent of vane assembly.

Rail support beams

Non-contacting dynamic seals having wave springs are disclosed herein. A non-contacting dynamic seal may have a shoe coupled to an outer ring by an inner beam and an outer beam. A wave spring may be located between the inner beam and the outer beam, between the shoe and the inner beam, or between the outer beam and the outer ring. The wave spring may damp vibrations in the inner beam and the outer beam.

The present disclosure relates to sealing systems for gas turbine engines. In one embodiment, a seal support structure for a gas turbine engine includes a seal support configured to retain a circumferential seal and an engine support configured for mounting the seal support structure to a gas turbine engine mount. The engine support includes at least one channel configured to provide radial movement of the seal support structure and circumferential retention of the seal support. Another embodiment is directed to a sealing system including a circumferential seal and seal support structure configured to provide radial movement.

Seal support structure

A vane assembly for a gas turbine engine includes an outer platform, an inner platform, a vane, and a seal. The outer platform is disposed proximate a case. The outer platform has a first rail extending towards the case. The first rail has a first face, a second face disposed opposite the first face, and a first opening extending from the first face towards the second face. The inner platform is disposed opposite the outer platform. The vane extends between the inner platform and the outer platform. The seal is received within a slotted region that is disposed between the first face and the second face.

Gas turbine engine having a vane assembly

The present disclosure relates generally to a hydrostatic advanced low leakage seal having a shoe supported by at least two beams. An anti-vibration beam spacer is disposed in contact with two adjacent beams and operative to mitigate an externally induced vibratory response of the beams.

Gas turbine engine and seal assembly therefore

A turbine vane for a gas turbine engine includes an outer platform including a first side spaced circumferentially apart from a second side, a forward end and an aft end. The first side includes a first gusset extending between the forward end and the aft end. The first gusset defines a first radius beginning at the forward end that transitions into an elliptical curve toward the aft end. An inner platform is also included. An airfoil extends between the outer platform and the inner platform. A gas turbine engine is also disclosed.

Turbine vane gusset

A seal damper system includes a plurality of circumferentially spaced blades that each include a platform and an airfoil that extends radially outwardly from the platform. A pocket is arranged circumferentially intermediate the blades and radially inwardly of the platform. A seal damper is arranged in the pocket. The seal damper includes a base section that extends along an axial dimension from a first axial end to an opposing second axial end. The base section joins a first arm that extends radially inwardly from the first axial end and a second arm that extends radially inwardly from the second axial end. The first arm includes a free end having a pair of spaced apart shoulders.

Seal damper with improved retention

A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform that axially extends between a leading edge and a trailing edge, circumferentially extends between a first mate face and a second mate face, and includes a gas path surface and a non-gas path surface. The component defines at least one cavity that extends at least partially inside of the component. A first plurality of cooling holes extends from the at least one cavity to at least one of the first mate face and the second mate face and a second plurality of cooling holes extends from either the at least one cavity or the non-gas path surface to the gas path surface.

Gas turbine engine component with combined mate face and platform cooling

Growing community of inventors

East Hartford, CT, United States of America

Jeffrey Michael Jacques