United Technologies Corporation

Raytheon Technologies Corporation

Rtx Corporation

Graham Ryan Philbrick

Patrick D Couture

Jonathan Jeffery Eastwood

Ken Robert Lagueux

Joseph F Englehart

Jason Arnold

Allison Zywiak

ChaiDee Woods Brown

Michael G McCaffrey

Bret M Teller

David Richard Griffin

James P Chrisikos

Henry K Webster

Richard Seleski

Joseph E Barker

Jon P Heslin

The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a rotary seal element, the rotary seal element configured to rotate during operation of a gas turbine engine, and a stationary seal element having an annular seal surface. The stationary seal element includes a first area of the annular seal surface configured to engage with the rotary seal element, and the stationary seal element includes a second area of the annular seal surface configured to provide reduced resistance to the rotary seal element during a flight windmilling event.

Seal configuration to prevent rotor lock

An active clearance control manifold assembly includes multiple arcuate manifold segments each having multiple circumferential channels axially spaced apart from one another. The circumferential channels include cooling holes facing radially inward. A tube at least partially circumscribes and fluidly interconnects the manifold segments.

Active clearance control system and manifold for gas turbine engine

Aspects of the disclosure are directed to an active clearance control system for an engine of an aircraft, comprising: a collector that is configured to receive a cooling fluid, at least two manifolds coupled to the collector, where a first of the manifolds is configured to receive at least a first portion of the cooling fluid from the collector and a second of the manifolds is configured to receive at least a second portion of the cooling fluid from the collector, and an insert coupled to the collector and the manifolds, where the insert is configured to seal an interface between the collector and the at least two manifolds over an operating range of the engine.

Active clearance control collector to manifold insert

A turbine section for a gas turbine engine includes blade outer air seals and stator vanes that provide a core flow path. A turbine case supports blade outer air seals and stator vanes. An annular cavity is provided between an interior surface of the turbine case and the blade outer air seals and the stator vanes. A hole extends through the turbine case from an exterior surface to the interior surface. The annular cavity extends axially to an exit. A manifold circumscribes the exterior surface of the turbine case and provides an annular space therebetween. The annular space is in fluid communication with the exit of the annular cavity via the hole.

Gas turbine engine active clearance control system using inlet particle separator

A fastener assembly for a gas turbine engine, and method of assembly, includes a first body having a first surface and a recess communicating through the first surface. The recess may be defined by a bottom surface and a side face spanning between the first and bottom surfaces. A shank of the assembly is generally engaged between the first body and a second body and includes opposite first and second end portions. The first end portion is located in the recess and the second end portion is engaged to the second body. A filler of the assembly is generally located in the recess to cover the first end portion. To reduce windage, the filler has an outer surface that is substantially flush with the first surface.

Reduced windage fastener assembly for a gas turbine engine

Disclosed is an active tip clearance control system (ATCCS) for a gas turbine engine, having an electronically controlled regulating valve directing cooling airflow to a turbine case, and an engine electronic control (EEC), controlling the electronically controlled regulating valve, wherein the EEC controls the electronically controlled regulating valve to regulate cooling airflow according to a selected target blade tip clearance schedule, and wherein the selected target blade tip clearance schedule is selected before or after an engine cycle, from of a plurality of target blade tip clearance schedules, each correlating to one of a plurality of thrust rating applications for the engine.

Thrust rating dependent active tip clearance control system

Aspects of the disclosure are directed to systems and methods for receiving operating state parameters associated with an operative state of an aircraft, determining a clearance value between a first structure of the engine and a second structure of the engine, where the clearance value is determined based on the operating state parameters and a passive clearance model that includes a specification of an uncertainty in the clearance value, determining that the clearance value deviates from a clearance target in an amount that is greater than a threshold, and engaging an active clearance control (ACC) mechanism based on the deviation.

Active clearance control for a turbine and case

A turbomachine seal plate includes a substrate with a first material that defines a surface having a substrate width. The substrate includes a first terminus extension that is raised and extends from a terminus portion of the substrate. The first terminus extension extends outwardly relative to the surface up to a terminus extension height. The turbomachine seal plate also includes a coating having a second material that covers the surface of the substrate and defines a coating width. The coating abuts a side of the first terminus extension. The coating width can be substantially equal to the terminus extension height.

Turbomachinery blade outer air seal

A gas turbine engine, system, and method with clearance control are provided. For example, the gas turbine engine includes a static component, and a rotating component that shifts axially in one of an aft direction and a forward direction in relation to the static component during a first operating condition of the gas turbine engine, and shifts axially in the other of the aft direction and the forward direction in relation to the static component during a second operating condition of the gas turbine engine. The first operating condition is when a rotating component growth and a static component growth change at different rates. The second operating condition is when the rotating component growth and static component growth normalize.

Method for clearance control in a gas turbine engine

A gas turbine engine component according to an exemplary aspect of this disclosure includes a peripheral portion defining an internal cooling passage and a recess in fluid communication with the internal cooling passage. The peripheral portion includes an outer wear surface, and the recess tapers toward the outer wear surface.

Engine component with wear surface protection

A process for machining a turbine engine blade outer air seal in situ, the process comprising replacing a blade with a cutting tool assembly proximate a blade outer air seal, wherein the blade outer air seal is assembled in a gas turbine engine case. The process includes coupling a blower to the blade outer air seal. The blade outer air seal comprises at least one flow path. The process includes creating a purge air stream with the blower through the blade outer air seal. The process includes machining the blade outer air seal, wherein particulate is formed from the machining. The process includes preventing the particulate from blocking the at least one flow path of the blade outer air seal.

Growing community of inventors

Durham, CT, United States of America

Graham Ryan Philbrick