United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Brian Duguay

Timothy M Davis

Brian Barainca

Sarah J Zecha

Uriah C Noble

Michael S Stevens

Jose R Paulino

Dmitriy A Romanov

Neil L Tatman

Joseph D Drescher

Jeremy Drake

Brian C McLaughlin

Russell E Keene

Christine F McGinnis

Erik M Pedersen

Judith F Brooks

Dairus Deylan McDowell

Tomasz Pelic

Kamiko L Darrow

Brian Ricciardelli

Danielle N Balzano

Major D Jones

Ryan M Kohn

An improved stator assembly for use in a gas-turbine engine is disclosed. The stator assembly may comprise a vane, an inner diameter (ID) ring, an outer diameter (OD) ring, a vane disposed between the ID ring and the OD ring, a potting component coupling the vane to at least one of the OD ring or the ID ring, and a potting embedded component disposed within the potting component. The potting embedded component may prevent disbond of the potting component during operation of the gas-turbine engine.

System for an improved stator assembly

A method is provided for inspecting a device comprising a plurality of bristles. During this method, image data provided from an electronic optical sensor is received. The image data is indicative of an image of at least a portion of the bristles. A bristle configuration (e.g., an angle) of at least one of the bristles (e.g., an average bristle) in the image is determined by processing the image data with a computer processor.

Systems and methods for inspecting bristles using a digital camera

An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a multiple of rotary ramps. Each of the multiple of rotary ramps is associated with one of the multiple of blade outer air seal assemblies. A method of active blade tip clearance control for a gas turbine engine is provided. The method includes rotating a multiple of rotary ramps to control a continuously adjustable radial position for each of a respective multiple of blade outer air seal assemblies.

Gas turbine engine ramped rapid response clearance control system

A method of actuating a Blade Outer Air Seal (BOAS) includes moving a retractor against a portion of a BOAS segment to move the BOAS segment from a first position to a second position that is radially outside the first position. The BOAS segment is seated against a support structure when in the first position and spaced from the support structure when in the second position.

Actuator for gas turbine engine blade outer air seal

A heat shield vane support may have a structure including at least one of a cylindrical and a frustoconical portion with an outboard diameter and an inboard diameter extending about an axis and extending axially between a forward face and an aft face and may comprise a flange extending circumferentially about the aft face radially inward from the inboard diameter, a plurality of anti-rotation features distributed circumferentially about the inboard diameter extending radially inward from the inboard diameter and extending axially with respect to the cylindrical structure between a forward edge and an aft edge defining a length L, and a plurality of teeth distributed circumferentially about the forward face and extending axially from the forward face.

Support ring with thermal heat shield for case flange

An active clearance control system for a gas turbine engine includes a ring seal engageable with a multiple of air seal segments.

Ring seal for blade outer air seal gas turbine engine rapid response clearance control system

A blade tip clearance system includes first and second control rings. The first control ring has a first coefficient of thermal expansion (CTE) and a first thermal response rate. The second control ring is located radially outward of and operatively connected to the first control ring and has a second CTE that is different from the first CTE and a second thermal response rate that is different from the first thermal response rate. Thermal expansion and contraction of the first and the second control rings controls a radial position of the blade tip clearance system relative to a rotating blade component.

Blade tip clearance systems

An active clearance control system for a gas turbine engine includes an air seal segment and a puller engageable with the air seal segment.

Rapid response clearance control system for gas turbine engine

An active clearance control system of a gas turbine engine includes a multiple of blade outer air seal assemblies and a sync ring with a multiple of graduation sets. Each of the graduation sets is associated with one of the multiple of blade outer air seal assemblies. An active clearance control system of a gas turbine engine includes a sync ring with a multiple of graduation sets. Each of the graduation sets includes a multiple of graduations to define an associated radial position for each of a respective multiple of blade outer air seal assemblies.

Gas turbine engine rapid response clearance control system

A blade outer air seal (BOAS) actuator assembly, according to an exemplary aspect of the present disclosure includes, among other things, an actuator member; and a retractor configured to move with the actuator member to move a BOAS segment from a first position to a second position that is radially outside the first position, the BOAS segment seated against a support structure when in the first position and spaced from the support structure when in the second position.

A method of assembling a gas turbine engine is provided that includes locating a consumable assembly tool within the engine. The consumable assembly tool is attached to another component of the gas turbine engine. The engine is run to vaporize the consumable assembly tool.

Consumable assembly tool for a gas turbine engine

An active clearance control system of a gas turbine engine includes an actuation cylinder, a puller engaged with an air seal segment and damped with respect to the actuation cylinder, and a full-hoop thermal control ring that at least partially supports the air seal segment. The puller may move the air seal segment between an extended radially contracted BOAS position and a retracted radially expanded BOAS position.

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Berwick, ME, United States of America

Brian Duguay