General Electric Company

Nuovo Pignone Holding S.p.a.

Nuovo Pignone Holdings, S.p.a.

Anthony John Dean

Venkat Eswarlu Tangirala

Adam Rasheed

David Michael Chapin

Narendra Digamber Joshi

Christian Lee Vandervort

Pierre Francois Pinard

Gregory Scot Corman

Keith Robert McManus

Andrew Philip Shapiro

Luciano Mei

James Michael Caldwell

Paul V Heberling

Alessio Miliani

Ivett Alejandra Leyva

Paul R Angel

Kevin Michael Hinckley

Bharat S Bagepalli

Paul Stephen DiMascio

Michael John Bowman

Donnell Eugene Crear

Kapil Kumar Singh

James Fredric Wiedenhoefer

Steven George Goebel

Jonathan Sebastian Janssen

William Theodore Bechtel

Stephen Hugh Black

Simon Ralph Sanderson

Andrei Colibaba-Evulet

Sravan Kumar Dheeraj Kapilavai

Jin Yan

Massoud Mirdamadi

Andrew Luts

Ronald Scott Bunker

Seyed Gholamali Saddoughi

Joel Meier Haynes

Mehmet Muhittin Dede

Leonardo Tognarelli

Jatila Ranasinghe

Himanshu B Vakil

Richard Scott Bourgeois

Lawrence Butler

James Rollins Maughan

Mark Stewart Schroder

Kurt Stockbridge

Andrew Maxwell Peter

Edward Lee McGrath

Thomas Raymond Farrell

Edward Randall Furlong

Sanjay M Correa

Bruce J Badding

Louis Andrew Schick

David Graham Holmes

Chukwueloka Obiora Umeh

Robert Patrick Campbell

Anil Gulati

Ross Hartley Kenyon

Owen James Sullivan Rickey

Owen Graham

Anthony J Loprinzo

Edward Joseph Hall

Shashank Yellapantula

Eayre Bruce Voorhees

Kenneth Lorenzo Parks

Mathew Paul Thariyan

Chih Hsiang Hsu

Mario Pecchioli

Suhui Li

Chris Basil Jiomacas

Gregor Arthur Waldherr

H Lindsay Morton

Geoffrey Gray

Peirre Francois Pinard

Stephen Daniel Myers

Liangyu Wang

Ivett Alejancra Leyva

Bernard Francois Robic

Christopher Nelson Chandler

Keith Robert Mcmanus

Matthew Paul Thariyan

Seyed Gholmali Saddoughi

A supporting member in a sole for an article of footwear including at least a vertical sub-member extending in both a vertical direction and a longitudinal direction that extends along a toe region to a heel region of the sole. Located within or adjacent to a cushioning member, the vertical sub-member has a curvature along the longitudinal direction wherein the curvature is configured to reduce flexion of the cushioning element and/or improve the durability of the supporting member. The supporting member further includes a horizontal sub-member extending from a sidewall of the vertical sub-member in a latitudinal direction of the sole and being angled away from the vertical sub-member and at least a portion of the vertical sub-member being coextensive with the vertical sub-member.

Supporting member for footwear activity economy

A fuel nozzle assembly includes a centerbody including an outer wall. The outer wall defines a plurality of fuel injection apertures. The fuel injection apertures include a first portion of the plurality of fuel injection apertures configured to induce a first fuel flow rate. The fuel injection apertures also include a second portion of the plurality of fuel injection apertures configured to induce a second fuel flow rate. The second fuel flow rate is less than the first fuel flow rate.

Combustors and methods of assembling the same

A gas turbine engine includes a combustor and a turbine. The combustor includes a pre-mixer having a body defining a plurality of fluid passages extending axially through the pre-mixer, wherein a cross-sectional projection of each of the plurality of fluid passages comprises one or more features that form a helical coil about an axis of the fluid passage along a length of the fluid passage, wherein the pre-mixer is configured to receive fuel from a fuel supply, receive air from an air supply, mix the fuel and air by flowing the fuel and air through the plurality of fluid passages, and imparting a swirling motion on the fuel and air, and supply the air-fuel mixture to a combustion zone. The combustor is configured to combust the air-fuel mixture, generating combustion fluids. The turbine is configured to receive the combustion fluids from the combustor and to use the combustion fluids to drive one or more stages of the turbine.

Premixer for gas turbine combustor

The present disclosure relates to a fuel-air premixer for a turbine system. The fuel-air premixer includes a swirler and a centerbody. The swirler is configured to direct a flow of air through the premixer, and the centerbody is configured to inject fuel into the flow of air. Additionally, the centerbody includes an airfoil shape that reduces and/or substantially eliminates recirculation pockets to prevent autoignition and/or flame holding in a combustion chamber. Accordingly, the turbine system may produce fewer NOemissions.

Fuel-air premixer for a gas turbine

A combustor is configured to operate in a rotating detonation mode and a deflagration mode. The combustor includes a housing and at least one initiator. The housing defines at least one combustion chamber and is configured for a deflagration process to occur within the at least one combustion chamber during operation in the deflagration mode and a rotating detonation process to occur within the at least one combustion chamber during operation in the rotating detonation mode. The at least one initiator is configured to initiate the rotating detonation process within the at least one combustion chamber during operation in the rotating detonation mode and to initiate the deflagration process within the at least one combustion chamber during operation in the deflagration mode.

Combustor for rotating detonation engine and method of operating same

A pulse detonation device contains a pulse detonation combustor which detonates a mixture of oxidizer and fuel. The fuel is supplied through fuel ducts and the fuel flow is controlled by fuel flow control devices. Oxidizer flow is provided through a main inlet portion and a flow control device directs the oxidizer flow to either the combustor or to a bypass duct, or both. The combustor further contains an ignition source. Each of the flow control devices, fuel flow control devices and ignition source are controlled by a control system to optimize performance at different thrust/power settings for the device.

System and method for passive valving for pulse detonation combustors

A detonation device cleaning system includes a vessel having a main body including an outer surface and an inner surface that collectively define an interior chamber. A detonation combustor cleaning device is mounted to the vessel. The detonation combustor cleaning device includes at least one combustion chamber that defines a combustion flow path. The at least one combustion chamber includes a deflection member arranged along the combustion flow path. An ignition device is operatively connected to the at least one combustion chamber. The ignition device is selectively activated to ignite fuel within the at least one combustion chamber to produce a shockwave that moves in a first direction along the combustion flow path, is redirected back along the flow path within the at least one combustion chamber, and passes into the interior chamber to dislodge particles clinging to the inner surface of the vessel.

Detonation combustor cleaning device and method of cleaning a vessel with a detonation combustor cleaning device

A detonation combustor cleaning device includes at least one combustion chamber having combustion flow path and including a deflection member. An ignition device is operatively connected to the at least one combustion chamber is selectively activated to ignite a combustible fuel within the at least one combustion chamber to produce a shockwave that moves in a first direction along the combustion flow path, impacts the deflection member, reverses direction and passes into a vessel to dislodge particles clinging to inner surfaces thereof.

A flow control device for use with a pulse detonation chamber including an inlet coupled in flow communication with a source of compressed air. The inlet extends at least partially into the chamber to facilitate controlling air flow into the chamber. The device also includes a body portion extending downstream from and circumferentially around the inlet, wherein the body portion is positioned in flow communication with the inlet.

Methods and apparatus for controlling air flow within a pulse detonation engine

A pulsed detonation combustor (PDC) is described. The PDC includes an outer casing defining a first hollow chamber configured to receive a flow and an inner liner. The inner liner includes at least one portion positioned within the first hollow chamber and configured to receive the flow from a plenum formed between the outer casing and inner liner. The PDC further includes a flow turning device with geometric features configured to direct the flow from the plenum to a second hollow chamber defined within the inner liner. The PDC also includes at least one fuel injection port located downstream of an inlet to the outer casing and an ignition device located downstream of the at least one fuel injection port and configured to periodically ignite fuel.

Pulse detonation combustor with folded flow path

A dual mode combustor of a gas turbine engine contains at least one dual mode combustor device having a combustion chamber, a fuel air mixing element, a high frequency solenoid valve and a fuel injector. During a first mode of operation the dual mode combustor device operates in a steady, constant pressure deflagration mode, receiving its fuel from the fuel injector. In a second mode of operation the dual mode combustor device operates in a pulse detonation mode, receiving its fuel from the high frequency solenoid valve.

Dual mode combustion operation of a pulse detonation combustor in a hybrid engine

A pulse detonation engine contains a mechanically driven timing device coupled with a stator device, where the timing device has both an opening portion and a blocking portion. The opening and blocking portions open and close air flow access to a detonation chamber of the pulse detonation engine at appropriate times during the pulse detonation cycle.

Inlet airflow management system for a pulse detonation engine for supersonic applications

An engine contains at least one pulse detonation combustor which is surrounded by a bypass flow air duct, through which bypass air flow is directed. The bypass air duct contains at least one converging-diverging structure to dampen or choke the upstream propagation of shock waves from the pulse detonation combustor through the bypass flow air duct. The bypass air also serves to cool the outer surfaces of the pulse detonation combustor. The bypass air flow is controlled in tandem with the heat release from the PDC to provide the appropriate amount of thermal energy to a downstream energy conversion device, such as a turbine. A mixing plenum is positioned downstream of the pulse detonation combustor and bypass flow air duct.

Pulse detonation engine bypass and cooling flow with downstream mixing volume

A method for operating a pulse detonation engine, wherein the method includes channeling air flow from a pulse detonation combustor into a flow mixer having an inlet portion, an outlet portion, and a body portion extending therebetween. The method also includes channeling ambient air past the flow mixer and mixing the air flow discharged from the pulse detonation combustor with the ambient air flow such that a combined flow is generated from the flow mixer that has less flow variations than the air flow discharged from the pulse detonation combustor.

Methods and apparatus for operating a pulse detonation engine

A pulse detonation device for dividing a pulse detonation shock wave into an primary and control portion to reduce the strength of a propagating shock wave and/or change its direction. The device contains a flow separator which directs a portion of the shock wave into itself, thus reducing the shock wave's strength. In one configuration, the control region converges in cross-sectional area so as to accelerate the flow in the control region, while the primary region diverges to slow the flow in the primary region. The flow in the control region is directed, at an angle, into the flow of the primary region to impede and/or redirect the flow of the primary region.

Naturally aspirated fluidic control for diverting strong pressure waves

Growing community of inventors

Scotia, NY, United States of America

Anthony John Dean