United Technologies Corporation

Raytheon Technologies Corporation

John E Paul

Michael G McCaffrey

Bryan P Dube

Jeffrey Michael Jacques

John R Farris

Edwin Otero

Ross Wilson

Elizabeth F Vinson

Theodore W Hall

John J Korzendorfer

Alan W Stoner

Darren M Wind

Robert Kujawa

Conway Chuong

William M Proscia

Kyle C Lana

Alex J Simpson

Mohamed Hassan

Charles Thistle

Carlos Calixtro

Christopher W Robak

Caroline Karanian

Kristine Marie Carnavos

Joseph D Evetts

Vladimir Skidelsky

Jagannath Pranatharthikaran

Matthew B DeGostin

Purity Dele-Oni

John W Korzendorfer

John R Korzendorfer

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

A rotational equipment assembly includes a plurality of seal shoes, a seal base, a plurality of spring elements and a secondary seal assembly. The seal shoes are arranged circumferentially around an axial centerline and include a first seal shoe. The first seal shoe includes a first seal shoe base and a first seal shoe rib that projects axially out from the first seal shoe base to an axial distal end of the first seal shoe rib. The seal base extends circumferentially around the axial centerline. The spring elements include a first spring element that connects and extends between the first seal shoe and the seal base. The secondary seal assembly is configured to seal a gap between the seal base and the seal shoes. The secondary seal assembly includes a free floating seal plate that axially contacts and is configured to slide radially along the first seal shoe rib.

Controlled contact surface for a secondary seal in a non-contact seal assembly

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

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 brush seal plate may comprise a flat ring with bristles protruding from an inner diameter of the flat ring. The brush seal plate may have a racetrack slot to allow the flat ring to move in a radial direction relative to a retention pin. The bristles may protrude from the inner diameter of the flat ring at an angle. A slot may be formed through the flat ring, and the slot may be angled. The flat ring may be circumferentially discontinuous. The flat ring may further comprise a retention opening configured to fix the flat ring in place relative to a retention pin.

Brush seal plate

A damper seal received in a cavity of a turbine blade includes a central body with two ends and a two sides. A portion extends from each end, one side has a faceted edge, and a projection extends from the other side to receive a lug of the turbine blade to align the damper seal relative to the turbine blade.

Faceted turbine blade damper-seal

A system and method for performing stress measurement on rotating parts is disclosed. The system may include a laser assembly configured to emit a plurality of laser beams having different wavelengths, and a probe assembly mounted proximal to a rotatable part in a device. The probe assembly may be configured to output a reflected laser beam onto a first target on the rotatable part. The probe assembly may be configured to output another reflected laser beam onto a second target on the rotatable part. The probe assembly may include a redirector, and a lens assembly mounted proximal to the redirector and configured to converge the laser beams. The redirector may be configured to change the direction of each emitted laser beam.

Multiple laser time of arrival probe

A system and method for performing stress measurement on rotating parts is disclosed. The system may include a laser assembly configured to emit a laser beam, and a probe assembly mounted proximal to a rotatable part in a device. The probe assembly may be configured to output a reflected laser beam onto a first target on the rotatable part. The probe assembly may further be configured to move the reflected laser beam from the first target to a second target on the rotatable part. The probe assembly may include a redirector moveable from a first position to a second position, and a lens mounted proximal to the redirector and configured to focus the laser beam. The redirector may be configured to change the laser beam direction from a first direction to a second direction when moved from the first position to the second position.

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Portland, CT, United States of America

John E Paul