General Electric Company

Other

Ning Fang

Mahmut Faruk Aksit

Abdul-Azeez Mohammed-Fakir

Ahmad Safi

Srikanth Vedantam

Duane Howard Anstead

Kyle Robert Snow

Brandon Wayne Miller

Mohammed El Hacin Sennoun

Gary Paul Moscarino

Adam Mitchell Record

Ray Harris Kinnaird

Brian Peter Arness

Gert Johannes Van Der Merwe

Donald Albert Bradley

John Ellington Greene

Bala Corattiyil

Prasad Laxman Kane

Jonothan Allen Scheetz

Wei-Ming Chi

Gayle Hobbs Goetze

Robert Proctor

Kenneth Lee Fisher

William Joseph Bowden

Pradeep Hemant Sangli

Jacob Patrick Miller

Scott Francis Wolfer

Jonathan K Remer

Mark Eden Zentgraf

Guohua Zhong

Daryl Scott Schneider

Donald James Welty

Bin Dong

Edward William Grace

David William Pugh

Kuangcai Chen

Bartosz Karbowski

Fei Zhao

Benjamin Joseph Simpson

Dave William Pugh

An integrated spectro-microscopic system for multimodality imaging on a sample includes a reflected differential interference contrast (RDIC) microscope, a Raman spectroscope optically coupled with the RDIC microscope and a total internal reflection fluorescence/scattering (TIRF/TIRS) microscope optically coupled with the RDIC microscope such that the integrated spectro-microscopic system is capable of simultaneously acquiring both the RDIC images, the Raman spectra and TIRF/TIRS images on the same sample.

Integration system of Raman spectroscopy with advanced light microscopy and applications of same

A system for managing thermal transfer in at least one of an aircraft or a gas turbine engine includes a first engine system utilizing an oil for heat transfer. The oil of the first system has a temperature limit of at least about 500&#xb0; F. The system additionally includes a fuel system having a deoxygenation unit for deoxygenating fuel in the fuel system, as well as a fuel-oil heat exchanger located downstream of the deoxygenation unit. The fuel-oil heat exchanger is in thermal communication with the oil in the first engine system and the fuel in the fuel system for transferring heat from the oil in the first engine system to the fuel in the fuel system.

Thermal management system

A lubrication system for a gas turbine engine includes a tank, a circulation pump, and a heat exchanger. The circulation pump generates a flow of lubricant from the tank to, e.g., a power gear box of the gas turbine engine and the heat exchanger removes an amount of heat from such flow of lubricant provided to the power gear box. The lubrication system also includes one or more valves in the flow of lubricant for controlling a flowrate and/or temperature of the lubricant provided to, e.g., the power gear box to increase an efficiency and/or durability of the power gear box.

Lubrication system for a turbine engine

A gas turbine engine having a core engine. The core engine includes an inlet, a compressor section, a combustion section, a turbine section, and an exhaust. The gas turbine engine also includes a bearing sump arranged in the core engine for containing lubrication, the bearing sump and lubrication having an operational range between at least about 0&#xb0; F. and about 550&#xb0; F.

Gas turbine engine bearing sump and lubricant drain line from cooling passage

A turbofan engine includes a core engine, a fan, a fan bypass duct partially surrounding the core engine and the fan, and a bleed system. The bleed system includes a first bleed circuit configured to bleed pressurized air from the core engine and channel the flow to a first circuit of a heat exchanger, and a second bleed circuit configured to bleed fan air from the fan bypass duct and channel the flow to a second circuit of the heat exchanger. The second bleed circuit includes a bleed duct including a duct inlet and a duct outlet coupled in flow communication with the heat exchanger through a valve. The bleed duct also includes an acoustic suppression conduit extending from the bleed duct upstream of the valve to the fan bypass duct and sized to suppress pressure oscillations inside the second bleed circuit when the valve is at least partially closed.

Method and system for mitigation of cavity resonance

In one aspect, the present disclosure is directed to a bearing compartment sealing system including a bearing for supporting a shaft. A housing encloses the bearing and defines a compartment for holding lubricant therein. At least two seals are located between the shaft and the housing. The at least two seals, the housing, and the shaft collectively enclose the compartment. Only one of the at least two seals is a hydrodynamic seal.

Hydrodynamic seals in bearing compartments of gas turbine engines

An apparatus is provided having a first zone with a fluid flow at a first pressure, and a second zone with a fluid flow at a second pressure. A sump cavity is provided in fluid communication with the first zone and a sump vent. An eductor system may be provided with a fluid flow path therethrough and in fluid communication with the second zone and the sump vent. The eductor system may be provided with an altitude sensing valve and may also be provided with gage pressure sensing valve. The eductor system may further be provided with a second gage pressure sensing valve and may also be provided with an orifice plate. The gage pressure sensing valves may react to the gage pressure of the second zone.

Adaptive eductor system

A gas turbine engine oil supply and scavenge apparatus includes: a stationary first frame comprising a first hub and a first outer ring interconnected by an array of radially-extending hollow first struts; a forward wet cavity defined radially inboard of the first frame, having a first rolling element bearing disposed therein; a supply line extending from the first outer ring through one of the first struts and communicating with the forward wet cavity, the supply line adapted to discharge oil to the forward wet cavity; a stationary second frame comprising a second hub and a second outer ring interconnected by an array of radially-extending hollow second struts, the second frame disposed aft of the first frame; and a scavenge path communicating with the forward wet cavity and adapted to remove oil-air mist from the forward wet cavity, the scavenge path defined at least in part by the second frame.

Method and apparatus for segregated oil supply and scavenge in a gas turbine engine

A gas turbine engine bearing cage assembly includes: a first bearing cage having: an annular first bearing support ring; an annular first mounting flange; and an annular array of axially-extending first spring arms interconnecting the first bearing support ring and the first mounting flange, the first spring arms defining an outer diameter; and a second bearing cage having: an annular second bearing support ring; an annular second mounting ring, the second mounting ring defining an inner diameter greater that the outer diameter; and an annular array of axially-extending second spring arms interconnecting the second bearing support ring and the second mounting ring, the second spring arms defining spaces therebetween. The bearing cages are sized such that the first bearing cage can be received within the second bearing cage. The spaces are positioned to receive the first spring arms, permitting independent flexing motion of the first and second spring arms.

Nested bearing cages

A rotating seal for a gas turbine engine includes: (a) an annular seal body; (b) a sealing component carried by the seal body which is adapted to form one-half of a rotating seal interface; and (c) an impeller carried by the seal body which comprises a plurality of radially-inwardly-extending impeller blades.

Dynamic impeller oil seal

The present invention provides a vortex generator that may be used in systems for separating oil from air oil mixtures. The vortex generator comprises a rotating disk having a rim having a plurality of passages extending through it and a cavity formed by the rotating disk and a cavity wall wherein a vortex is created when there is a flow through the plurality of passages into the cavity.

Vortex air-oil separator system

In a gas turbine, a supplemental seal is provided between an annular axially facing sealing surface of a nozzle support ring and an annular axially opposed sealing surface formed by circumferentially adjacent nozzle segments. Each segment carries an inner rail mounting a chordal hinge seal which engages the sealing surface of the nozzle support ring. That seal is supplemented by a generally arcuate V-shaped seal between the sealing surfaces which opens radially inwardly toward a high pressure leakage path past the chordal hinge seal. The supplemental seal is initially compressed and maintained in a compressed condition during installation by application of a solder. At operating temperature, the solder melts away, releasing the supplemental seal to seal between the nozzle support ring and nozzle segments.

Supplemental seal for the chordal hinge seals in a gas turbine and methods of installation

In a gas turbine having a chordal hinge seal between an inner rail of each nozzle segment and an annular axially facing sealing surface of a nozzle support ring, a supplemental seal is disposed between the support ring and inner bands of the nozzle segments on a lower pressure side of the chordal hinge seals. To minimize or prevent leakage flow across the chordal hinge seals, a generally U-shaped supplemental seal having reversely folded U-shaped marginal portions is received in a cavity formed in the axially extending sealing surface of the inner rail of the nozzle segment. At operating conditions, the marginal portions seal against the base of the cavity and the annular sealing surface of the nozzle support ring to prevent leakage flow past the chordal hinge seal from entering the hot gas path. To install the supplemental seal, the seal is first compressed and maintained in a compressed state by applying one or more wraps about the supplemental seal or an epoxy to secure the seal when compressed in the cavity. At operating temperatures, the retention means releases the seal to engage marginal portions against opposite sealing surfaces of the nozzle segment and support ring.

Supplemental seal for the chordal hinge seals in a gas turbine

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Mason, OH, United States of America

Ning Fang