Rolls-royce North American Technologies Inc.

Rolls-royce Corporation

Allison Advanced Development Company

Allison Engine Company, Inc.

Other

James Christopher Muskat

Sean Andrew Morgan

Timothy Unton

Alan W Smith

Charles J Teague

Adam Lagrange

Christine M Frasier

Douglas David Dierksmeier

James Carl Loebig

Christopher D Hall

Eric Sean Donovan

Todd S Taylor

Tab Michael Heffernan

Samuel J Lacombe

Christopher Dwayne DeBruhl

Steven Lester Grant

Joseph Benjamin LaBelle

Mike Nesteroff

Joshua M Peters

In some examples, a system including a gas turbine engine, the engine including a high-pressure (HP) shaft; HP compressor; HP turbine, second shaft; second compressor; second turbine, the second turbine being coupled to the second compressor via the second shaft (e.g., LP shaft); and a generator coupled to the LP shaft. The generator is configured to generate electrical power from rotation of the LP shaft, and increase electrical power generated by the generator to increase a torque applied to the LP shaft by the generator, e.g., in combination with reduction in engine thrust, or in response to the detection of a stall and/or surge of the engine. The increase in torque applied to the second shaft is configured to increase a rate at which a rotational speed of the second shaft decreases, e.g., in combination with the reduction in engine thrust or during the stall/surge of the engine.

Gas turbine engine system with generator

In some examples, a gas turbine engine including a high-pressure (HP) spool assembly including a HP shaft, a HP compressor and HP turbine; a lower pressure (LP) spool assembly including a LP shaft and LP turbine; a motor-generator coupled to the LP shaft; and a controller. The controller is configured to control the motor-generator to operate in a motor mode to apply torque the LP shaft during a starting of the HP spool assembly, and control the motor-generator to operate in a generator mode for a least a period of time following the starting of the HP spool assembly.

Gas turbine engine system with motor-generator

The disclosure describes an apparatus for sealing a rotating machine, such as an electric machine or gas turbine engine. The apparatus includes a brush seal. The brush seal includes a plurality of first filaments and a plurality of electrically conductive filaments. The first filaments are configured to seal a lubricant within a bearing chamber or sump of the rotating machine. The plurality of electrically conductive filaments is configured to contact a shaft of the rotating machine and discharge a shaft voltage-induced current from the shaft to an external ground of the rotating machine.

Grounding brush seals

A member may have a primary major surface and a secondary major surface. The member may form an array of apertures extending from the primary major surface to the secondary major surface. The array of apertures includes at least one aperture comprising two or more conduits. The axis of each conduit intersects the axis of each other conduit in the aperture. The cross-section of at least one of the conduits perpendicular to its axis may be circular. In some embodiments, an aperture may comprise two or three conduits.

Coverage cooling holes

Systems and methods for suppressing infrared radiation generated by a turbine engine. A system comprises a primary assembly having a center body, a plurality of vanes extending from the center body, an outer radial duct with the plurality of vanes extending therethrough, a structural baffle, and a mixer. The primary assembly is disposed in the exhaust flow path of a turbine engine and encased in ducting and/or an airfoil. An air flow path defined between the center body and outer radial duct is axially spit by an interface rim and flow segregator. The flow segregator segregates engine core flow from ambient air flow.

Flow segregator for infrared exhaust suppressor

A retention pin assembly may include a stud having a head, a shaft, and a deformable end. The shaft may include a stepped surface having a greater diameter than the deformable end. The assembly may include a support member having an opening for receiving the deformable end. The support member may include a pocket. The stepped surface of the shaft may position the stud in relation to the support member. The deformable end of the stud may be operable to be melted to form a mechanical retainer within the pocket without forming a metallurgical joint between the stud and the pocket.

Retention pin and method of forming

A unique compressor includes a rotating compressor blade having a blade tip; a compressor case having a blade track disposed opposite the blade tip; and a tip clearance control system including a fluid impingement structure. This structure has a plurality of openings to impinge a fluid received from a diffuser onto the compressor case. The tip clearance control system is configured to control a clearance between the blade tip and the blade track by impinging the fluid onto the compressor case and modulating the same with a valve in fluid communication with the diffuser. A further form includes a unique gas turbine engine having a compressor with a compressor blade tip, a compressor case disposed opposite the blade tip, and a fluid impingement structure having openings to impinge a fluid onto the case. Also included are other apparatuses, systems, devices, hardware, methods, and combinations for compressor blade tip clearance control.

Compressor tip clearance control and gas turbine engine

An improved retention pin assembly and method of forming a pin assembly that uses a melt in a pocket without a metallurgical joint having been formed. The assembly can be generated by a method of forming a joint which includes providing a metal shaft and a member that is operable to receive the shaft. A pocket is formed within the member which operates to receive a melt pool. Next the shaft is inserted into apertures in the member. A welding or melting operation is then performed to create a melted portion that occupies the pocket. A joint is created using a retention pin.

A disk for a turbine engine is disclosed herein. The disk includes a rotatable body extending along a longitudinal axis between a forward side and an aft side. The disk also includes a plurality of slots disposed about a periphery of the body. Each of the slots extends between the forward and aft sides along a respective slot axis. The sides of each of the slots are asymmetrical relative to one another in a cross-section normal to the slot axis.

Disk for turbine engine

The clearances between an array of turbine blades and its surrounding blade track may be controlled by an expansion control material system supporting the blade tracks. The blade track support hoop is placed in tension by the expansion control material placed therein and the expansion control material is placed in compression.

Blade track assembly

A lightweight high temperature multiproperty rotor disk and method of manufacture for use in a gas turbine engine. The rotor disk of a nickel super alloy and having a plurality of lightweight high temperature single crystal blade attachment lugs bonded thereto. The single crystal high temperature rotor blade attachment lugs being cast in a substantially rectangular shape and bonded to the circumference of the disk. A method of manufacturing the rotor includes positioning the plurality of single crystal attachment lugs on a positioning ring that has locating nests formed thereon. Subsequently, the rotor disk is placed within the bonding ring and a restraining ring is placed around the entire subassembly. Upon subjecting the assembly to high temperature the rotor disk, having a coefficient of thermal expansion greater than the coefficient of thermal expansion of the restraining member, forces the components into a mating relationship. Upon completion of the bonding cycle, the restraining ring is removed from the assembly and the bonding ring is machined away.

Growing community of inventors

Mooresville, IN, United States of America

James Christopher Muskat