General Electric Company

Ge Avio S.r.l.

Nuovo Pignone Spa

Ge Aviation Czech S.r.o.

General Electric Technology Gmbh

Bugra Han Ertas

Brandon Wayne Miller

Andrea Piazza

Ravindra Shankar Ganiger

Joshua Tyler Mook

Darren Lee Hallman

Jason Joseph Bellardi

Arthur William Sibbach

Donald Albert Bradley

Daniel Alan Niergarth

Xiaohua Zhang

Flavia Turi

Deepak Trivedi

Rahul Anil Bidkar

Adolfo Delgado Marquez

Norman Arnold Turnquist

Douglas Carl Hofer

Walter John Smith

Miriam Manzoni

Gontla Nagashiresha

Fulton Jose Lopez

Narayanan Payyoor

Eric Richard Westervelt

Weize Kang

Kenneth Lee Fisher

Joseph Robert Dickman

Kedar S Vaidya

William Dwight Gerstler

Christopher Edward Wolfe

Randy M Vondrell

Trevor Howard Wood

Daniel Jason Erno

David Allan Torrey

Richard Ludwig Schmidt

Nathan Evan McCurdy Gibson

Robert Michael Zirin

Eyitayo James Owoeye

Suryarghya Chakrabarti

Adam Joseph Wangler

Lana Maria Osusky

Sanjeev Kumar Jha

Fabio Nonato De Paula

Joseph Herbert Fields

Ahmet Dindar

Andrew Kevin Winn

Thomas Lee Becker

Nicholas Joseph Kray

Jie Jerry Liu

Anil Raj Duggal

Kishore Ramakrishnan

Scott Alan Schimmels

Hua Xia

Andrew Lee Trimmer

Changjie Sun

Weijun Yin

Adam Daniel Minadeo

Narendra Anand Hardikar

Younkoo Jeong

Eric John Ruggiero

Peeyush Pankaj

Juraj Hrubec

George Hanna Ghanime

Li Zheng

Kyle Robert Snow

Gabriele Mariotti

Massimo Camatti

Leonardo Coviello

Sergio Palomba

Nathan EvanMcCurdy Gibson

Michael Colan Moscinski

Pei-Hsin Kuo

John Malott Cottrill

Matthew Kaminske

Veera Venkata Amarnath Manem

Lokaditya Ryali

Adolfo Delgado

Michael John Wittbrodt

Douglas C Hofer

A seal monitoring apparatus is provided. The seal monitoring apparatus includes a temperature sensor and a controller in communication with the temperature sensor. The temperature sensor is mounted at a seal of a device. The controller is configured to receive measured temperature data from the temperature sensor and calculate expected temperature data for the seal based at least in part on operating conditions of the device. The controller is configured to determine a condition of the seal based at least in part on a temperature difference of the measured temperature data from the expected temperature data.

Seal monitoring apparatus

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gear includes a first gear that is a split sun gear including a forward sun gear and an aft sun gear separate from the forward sun gear. The forward sun gear and the aft sun gear are each rotationally coupled to a rotating shaft of the gas turbine engine.

Mounting assembly for a gearbox assembly

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by Vis a gutter volume of the gutter and Vis a gearbox volume of the gearbox. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a tank that stores a lubricant therein, one or more lubricant pumps for generating a flow of lubricant from the tank to the gearbox assembly, and a flow rate control valve. The flow rate control valve has a flow inlet and a flow outlet and defines a variable throughput from the flow inlet to the flow outlet for controlling a flowrate of the lubricant to the gearbox assembly.

Gearbox assembly with lubricant extraction volume ratio

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine includes an electric power system including at least one electric machine. The electric power system includes a plurality of power converters and a plurality of power distribution management units. At least two of the plurality of power converters or the plurality of power distribution management units are integrated together in a single housing.

This disclosure is directed to seal assemblies for a turbomachine. The seal assemblies include one or more paired rotors and stators and at least one interface between the rotors and the stators. The components of the stator may be axially and radially movable by vibrations and other mechanical interference. The stators comprise a sealing element, a seal housing, and a stator interface connected to the engine housing. In some examples, seal assembly includes a damping element to isolate one or more of the rotating components from vibrations mechanical interference that might misalign the rotating components from the stationary components while the turbomachine is operational. In some examples, the damping element is positioned between the seal housing and the stator interface. In other examples, the damping element is positioned between the stator interface and the engine housing.

Seal assembly for a turbomachine

A mounting assembly for a gearbox assembly of a gas turbine engine includes at least one mounting member configured to mount a gear of the gearbox assembly to a component of the gas turbine engine, the at least one mounting member characterized by a lateral impedance parameter, a bending impedance parameter, and a torsional impedance parameter. A gas turbine engine includes the mounting assembly. The at least one mounting member may be a flex mount, a fan frame, or a flex coupling. The gas turbine engine also includes a heat exchanger including an inner peripheral wall and an outer peripheral wall extending between an inlet and an outlet. The inner peripheral wall and the outer peripheral wall define a flow channel therebetween. The heat exchanger includes a plurality of fins disposed in the flow channel and dividing the flow channel into a plurality of flow passages.

A windage cover for a plurality of fasteners coupling a ring gear assembly to an output shaft. The windage cover includes a clip retention member abutting an integral cover shell of the output shaft, and a foot portion configured to be inserted into a pilot groove between an integral lip and an arm portion of the output shaft. The windage cover also includes a wall portion connected to the foot portion, the wall portion being retained at one end of the wall portion by the clip retention member. The windage cover is configured to cover the plurality of fasteners.

Windage cover that covers fasteners coupling a ring gear assembly to an output shaft

A turbofan engine having one or more heat exchangers tied to a power gearbox is provided. The power gearbox mechanically couples a low pressure spool and a fan of the turbofan engine. The one or more heat exchangers have a heat exchanger capacity defined by a resultant heat transfer surface area density associated with the one or more heat exchangers multiplied by a heat conductance factor that relates a power gearbox heat load, a fan power consumption function, a fan diameter of the fan, and a bypass ratio of the turbofan engine. The heat exchanger capacity is between 0.77 and 298.17 for a rotational speed of the low pressure spool between 2,000 and 16,000 revolutions per minute at one hundred percent capacity and a resultant heat transfer surface area density being between 3,000 m/mand 13,000 m/m.

Heat exchanger capacity for one or more heat exchangers associated with a power gearbox of a turbofan engine

A differential gearbox assembly for a turbine engine having a fan shaft and a drive shaft. The differential gearbox assembly includes an epicyclic gear assembly coupling the fan shaft to the drive shaft. The epicyclic gear assembly includes a sun gear, a planet gear constrained by a planet carrier, and a ring gear. The sun gear is coupled to the drive shaft and the planet carrier is coupled to the fan shaft. The sun gear, the planet gear, and the ring gear all rotate about the drive shaft. The differential gearbox assembly includes an electric machine assembly that includes an input coupled to the epicyclic gear assembly. The electric machine assembly provides mechanical power to the fan shaft through the epicyclic gear assembly.

Differential gearbox assembly for a turbine engine

Methods and systems of electrochemically machining a component are provided. The method may include applying two or more potentials to a tool electrode comprising an array of two or more individual electrodes to generate two or more electric fields in between the tool electrode and a workpiece opposite of the tool electrode, wherein each of the two or more electric fields is generated by one of the array of two or more individual electrodes.

Methods and systems of electrochemical machining

A gearbox assembly includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, and given by Vis a gutter volume of the gutter and Vis a gearbox volume. A gas turbine engine includes a combustion section and the gearbox assembly. A fuel delivery system includes a fuel supply line for delivering fuel to the combustion section. A lubrication system includes a lubricant supply line for delivering lubricant to the gearbox assembly. A thermal management system includes a fuel-lubricant heat exchanger for cooling the lubricant with the fuel. The thermal management system selectively directs the fuel through fuel bypass lines or the lubricant through lubricant bypass lines to bypass the fuel-lubricant heat exchanger based on a fuel temperature or a lubricant temperature.

A gas turbine engine includes a gearbox assembly that includes a gearbox and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio defined by: is a gutter volume of the gutter and Vis a gearbox volume. The gas turbine engine includes a lubricant flow control system that includes a variable flow lubricant pump that generates a pump variable flow of lubricant to the gearbox assembly. The gearbox assembly has a variable consumption demand for delivery of lubricant. A lubricant flow controller is configured to generate a pump control command for the variable flow lubricant pump to produce the pump variable flow of lubricant based on the variable consumption demand.

A gearbox assembly includes a gearbox having a gear assembly and a gutter for collecting a gearbox lubricant scavenge flow from the gearbox. The gutter is characterized by a lubricant extraction volume ratio between 0.01 and 0.3, inclusive of the endpoints. The lubricant extraction volume ratio is defined by is a gutter volume of the gutter and Vis a gearbox volume. A gas turbine engine includes the gearbox assembly and a lubrication system. The lubrication system includes a sump that is a primary reservoir having a first lubricant level and a secondary reservoir in the gearbox assembly. The secondary reservoir has a second lubricant level. The lubrication system fills the secondary reservoir with a lubricant between the first lubricant level and the second lubricant level. The gear assembly collects the lubricant in the secondary reservoir to supply the lubricant to the gear assembly.

Methods, apparatus, systems, and articles of manufacture are disclosed to reduce failure to bearings in a pump system. Disclosed herein is a pump system comprising a shaft connected to an impeller of the pump system, and a bearing to provide a dampening to the shaft, the bearing including a journal lining, the journal lining supported in the pump system, a spring-loaded foil to separate the shaft from the journal lining, an inner lining between the shaft and the spring-loaded foil, and a deformation limiter located between the spring-loaded foil and the journal lining.

Apparatus to reduce bearing failure

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Niskayuna, NY, United States of America

Bugra Han Ertas