United Technologies Corporation

Raytheon Technologies Corporation

Pw Power Systems, Inc.

John J Korzendorfer

Michael G McCaffrey

John R Farris

Edwin Otero

Ross Wilson

Jeffrey Michael Jacques

Elizabeth F Vinson

John E Paul

Theodore W Hall

Alan W Stoner

Paul W Palmer

Fabian D Betancourt

Peter Balawajder

Fernando K Grant

Mahamoud Coulibaly

Nicholas Lefevre

Paul J Colucci

Alan J Goetschius

Jeffrey D Melman

Charles C Wu

David J Sander

Henry K Webster

William A Daniels

Andrew P Boursy

Scott A Ladd

Christopher William Moore

Witt C Guinn

Kelly A Vanston

Alexander Sankovich

David A Debyah

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 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

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.

A seal system for a gas turbine engine includes a cover plate with a radial flange; a seal carrier adjacent the cover plate; an outer compliant seal supported by the seal carrier; an inner compliant seal supported by the seal carrier, the inner compliant seal engaged with the radial flange; and a spring between the cover plate and the seal carrier.

Duct blocker seal assembly for a gas turbine engine

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 power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support, the heat shield assembly forms an outer diameter directed toward an inner vane platform of the power turbine vane array.

Power turbine heat shield architecture

A power turbine section for a gas turbine engine includes a heat shield assembly mounted to a bearing support to form a first annular compartment and a second annular compartment.

Power turbine cooling air metering ring

An exemplary laser instrumentation bracket includes a support structure providing a recess configured to receive a collar of a laser housing. The laser housing has a main body extending axially through an aperture of the support structure when the recess receives the collar.

Laser instrumentation bracket

A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.

An exhaust duct comprises a shroud body, a forward flange assembly, an aft flange assembly, an intermediate flange assembly, and a first plurality of bleed ports. The forward flange assembly extends radially inward from a forward shroud end for securing the forward shroud end downstream of a final turbine stage. The aft flange assembly extends circumferentially around and radially inward from an aft shroud end for securing the aft shroud end to an engine tail cone. The intermediate flange assembly is disposed forward of the aft flange assembly, and extends circumferentially around and radially inward from the shroud body for securing the shroud body to an engine bearing housing. The first plurality of bleed ports is disposed around the shroud body forward of a junction with the intermediate flange.

Turbine exhaust case duct

A premixing, tangential entry fuel injector (10) for a gas turbine engine features a secondary fuel-air injection insert (40) positively secured to a centerbody shell (38) by a braze joint (98). A secondary fuel supply tube (42), positively secured to both a centerbody base (36) and to the insert (40), is curved in at least two dimensions. In an exemplary embodiment, the tube is coiled into a spiral shape covering a single 360.degree. cycle. During engine operation, the centerbody expands axially in response to elevated temperatures in the engine's interior, causing the insert (40) to be displaced away from the base (36). The curvature of the tube allows the tube to flex slightly to accommodate the displacement. Ideally the curvature of the tube is such that the tube's natural frequency is well above the maximum vibratory frequency that the tube will experience during engine operation.

Growing community of inventors

Glastonbury, CT, United States of America

John J Korzendorfer