General Electric Company

Bradley Willis Fintel

Robert Proctor

Kevin Samuel Klasing

Brandon Wayne Miller

Jeffrey Douglas Rambo

Steven Douglas Johnson

Richard William Albrecht, Jr

John Carl Glessner

Andrew J Lammas

Bala Corattiyil

Christopher Jon Potokar

Julius John Montgomery

William F McGreehan

Scott Francis Wolfer

Jeffrey Lee Mason

Brian Richard Green

Christina Granger Morrissey Haugen

Rebecca J Schmidt

Richard William Albrecht

Rebecca Jean Schmidt

A system for controlling blade clearances within a gas turbine engine includes a rotor disk and a rotor blade coupled to the rotor disk. Additionally, the system includes an outer turbine component positioned outward of the rotor blade such that a clearance is defined between the rotor blade and the outer turbine component. Furthermore, the system includes a heat exchanger configured to receive a flow of cooling air bled from the gas turbine engine and transfer heat from the received flow of the cooling air to a flow of coolant to generate cooled cooling air. Moreover, the system includes a valve configured to control the flow of the coolant to the heat exchanger. In this respect, the cooled cooling air is supplied to at least one of the rotor disk or the rotor blade to adjust the clearance between the rotor blade and the outer turbine component.

System for controlling blade clearances within a gas turbine engine

Louver systems for gas turbine bleed air systems are disclosed. An example louver system may include a bleed system discharge opening arranged to vent bleed air from a bleed flow conduit and a plurality of pivotable louvers disposed proximate the discharge opening, the pivotable louvers being pivotable between a shut position and an open position. In the shut position, individual louvers may at least partially obstruct the discharge opening. In the open position, individual louvers may at least partially control a direction of flow of the bleed air exiting the discharge opening.

Modular louver system

A sump pressurization system for a gas turbine engine comprises a first hollow shaft and a second hollow shaft disposed within the first hollow shaft and defining a cavity therebetween. Each of the first and second hollow shafts has a common axis of rotation. Also included is a source of pressurized air to pressurize the cavity and a plurality of hollow tubes disposed in the cavity. The tubes are oriented perpendicular to the axis of rotation and are connected to and rotatable with the first hollow shaft. A plurality of apertures in the second hollow shaft are in fluid communication with the tubes, such that pressurized air flowing through the tubes passes through the apertures into the interior of the second hollow shaft.

Gas turbine engine sump pressurization system

A system for venting a high-pressure flow stream is disclosed, the system comprising a device having a plurality of orifice plates, each orifice plate having a plurality of orifices, wherein the plurality of orifice plates are oriented relative to each other such that the pressure of the flow stream substantially drops.

High pressure drop muffling system

A high pressure compressor flowpath bleed extraction slot is provided wherein an articulated portion of the outer band of the compressor forms a slot for providing efficient conversion of core air to diffuser air while retaining substantial pressure and velocity energies. The diffuser slot can be applied to an earlier compressor stage with improved performance.

High pressure compressor flowpath bleed valve extraction slot

Growing community of inventors

West Chester, OH, United States of America

Bradley Willis Fintel