United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

John R Farris

Michael G McCaffrey

Edwin Otero

Jeffrey Michael Jacques

Ross Wilson

Elizabeth F Vinson

John E Paul

Theodore W Hall

John J Korzendorfer

Alan W Stoner

Paul M Lutjen

Eric A Hudson

John A Sharon

Mark Borja

Brandon T Rouse

Thomas Almy

Igor S Garcia

Matthew A Devore

Brian T Hazel

Mario P Bochiechio

James F Wiedenhoefer

Brian R Pelletier

Ronald R Gagnon, Jr

Thomas N Slavens

Marc J Muldoon

Mosheshe Camara-Khary Blake

Tracy A Propheter-Hinckley

Christopher W Strock

Raymond C Surace

John Joseph Marcin

Dilip M Shah

Alan David Cetel

Joel H Wagner

Thomas J Praisner

Matthew S Gleiner

Douglas C Jenne

George T Suljak, Jr

Arnab Roy

Peter H Thomas

John W Korzendorfer

Connor Wiese

Michael G Mccaffrey

John R Korzendorfer

Jr George T Suljak

A method of assembling a part is provided and includes forming a first section of the part, defining, in the first section, passages with dimensions as small as 0.005 inches (0.127 mm), forming a second section of the part, metallurgically bonding the first and second sections whereby the passages are delimited by the first and second sections and executing the metallurgically bonding without modifying a condition of the passages.

Hybrid bonded configuration for blade outer air seal (BOAS)

A blade outer air seal assembly includes a plurality of seal segments circumferentially disposed about an array of blades rotatable about an axis, each of the plurality of seal segments having a radially inner surface facing a tip of each blade of the array of blades, the radially inner surface having an arrangement of trenches formed therein, and a radially outer surface opposite the radially inner surface. The arrangement of trenches is disposed between 30% and 80% of a chord of a blade of the array of blades as taken at the respective tip, and the arrangement of trenches is aperiodic in the axial direction.

Life and performance improvement trenches

In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

Multi-zone blade fabrication

An example method for manufacturing a component of a gas turbine engine is provide. The method includes forming a tow of filaments of a fiber material. The method further includes weaving the tow together with other tows to form a sheet of the fiber material. The method further includes forming the component from the sheet of fiber material, the component comprising a designated surface area having a unique pattern created from properties of the fiber material.

Composite material marking and identification

An article comprises a first portion comprising a first alloy and a second portion comprising a second alloy that is metallurgically bonded to the first portion to form a monolithic article. The metallurgical bonding involves the application of an electrical current across the bond line and results in a retention of a metallurgical structure of the first portion and of a metallurgical structure of the second portion immediately adjacent to a bond line. The first portion has a first dominant property and the second portion has a second dominant property. The first dominant property is different from the second dominant property. The first dominant property is selected to handle operating conditions at a first position of the article where the first portion is located and the second dominant property is selected to handle operating conditions at a second position of the article where the second portion is located.

Hybrid superalloy article and method of manufacture thereof

An advanced passive clearance control (APCC) control ring is provided. The APCC control ring includes first and second cover sections, first and second wall sections and a control ring. At least one of the first and second cover sections is bonded to corresponding edges of the first and second wall sections by field assisted sintering technology (FAST) processing along a bond surface to form an enclosure for the control ring.

Advanced passive clearance control (APCC) control ring produced by field assisted sintering technology (FAST)

A hybrid electric engine including a gas turbine engine including a low speed spool, a high speed spool a fan section, a compressor section, a combustor section, and a turbine section. The hybrid electric engine further includes an electric generator configured to convert rotational power of the high or low speed spool to electricity and a variable area turbine control system electrically connected to the electric generator. The variable area turbine control system being configured to adjust a cross-sectional area of a core flow path of the hybrid electric engine. The variable area turbine control system including a plurality of variable turbine vanes located in the turbine section and a variable area turbine actuator configured to rotate each of the plurality of variable turbine vanes to adjust the cross-sectional area of the core flow path of the hybrid electric engine. The variable area turbine actuator is an electromechanical actuator.

Hybrid electric variable area turbine

A hybrid electric propulsion system including: a gas turbine engine comprising a low speed spool and a high speed spool, the low speed spool comprising a low pressure compressor and a low pressure turbine, and the high speed spool comprising a high pressure compressor and a high pressure turbine; an electric motor configured to augment rotational power of the high speed spool or the low speed spool; at least one blade outer air seal positioned between an outer case of the high pressure turbine and a plurality of blades of the high pressure turbine; a clearance control system operably coupled to the at least one blade outer air seal, the clearance control system configured to vary a position of the at least one blade outer air seal with respect to the plurality of blades of the high pressure turbine; and a controller operably coupled to the electric motor and the clearance control system, wherein the controller is configured to operate the clearance control system based upon an operational state of the electric motor.

Hybrid electric engine with electric tip clearance mechanism

A method of forming a coating includes disposing a substrate having a plurality of protrusions on a seal and layering a topcoat over the protrusions. The method of forming a coating also includes creating a wear pattern and converting the topcoat. A turbine section includes a casing, a plurality of blades within the casing, and a substrate deposited on the casing having a plurality of protrusions. The turbine also includes an unconverted topcoat disposed over the plurality of protrusions, the topcoat having segmented portions defining a plurality of faults extending from the protrusions through the topcoat. A method of forming a coating includes creating a channel in the coating during an initial rub event and converting the coating during a high-temperature event. Converting the coating includes preserving the channel created during the initial rub event.

Seal coating

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 gas turbine engine including a compressor section, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a plurality of gas path components exposed to a primary fluid flowpath through the compressor section, the combustor section and the turbine section. At least one of the gas path components includes an exterior facing surface, a lattice structure extending outward from the exterior facing surface, the lattice structure being integral to the exterior facing surface, and a thermal barrier coating adhered to at least a portion of the exterior facing surface and the lattice structure.

Enhanced adhesion thermal barrier coating

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 semi-autonomous rapid response active clearance control system for a gas turbine engine includes an outer case, a carrier for a blade outer airseal positioned radially inward of the outer case, a blade outer airseal positioned radially inward of and mounted to the carrier, at least one electromechanical actuator attached to the outer case and selectively operable to move the carrier, and a sensing system. The sensing system includes a maneuver sensor housed within the actuator and configured to output a first signal, a position sensor mounted proximate to the blade outer airseal and configured to output a second signal, and a control means in communication with the maneuver sensor and the position sensor.

Semi-autonomous rapid response active clearance control system

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.

Growing community of inventors

Bolton, CT, United States of America

John R Farris