General Electric Company

Victor Hugo Silva Correia

Robert Francis Manning

Jared Peter Buhler

Corey Bourassa

Robert Proctor

Ronald Scott Bunker

Gregory Michael Laskowski

Byron Andrew Pritchard, Jr

Jonathan Russell Ratzlaff

Robert Carl Murray

Curtis Walton Stover

Brian Kenneth Corsetti

Timothy Deryck Stone

George Joe-Kueng Chan

Mark Broomer

Bhanu Mahasamudram Reddy

Christopher Charles Glynn

Jason David Shapiro

Jonathan David Baldiga

Monty Lee Shelton

David Vickery Parker

William Collins Vining

Michael Elia Hayek

James Earl Kopriva

John Howard Starkweather

David Scott Stapleton

Daniel Edward Demers

Tyler Frederick Hooper

David Andrew Hannwacker

Hojjat Nasr

Wilhelm Ramon Hernandez

Donald Brett Desander

Marshall Scott Allen

Christopher Michael Ceglio

Stephen Kin-Keung Tung

Shawn Patrick Duffen

Robert Alan Jacobson

Christopher Kanoa Hoffman

Troy Todd Dennis

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft. A bypass conduit couples the compressor section to the turbine section. At least one centrifugal separator is fluidly coupled to the bypass stream, where the at least one centrifugal separator includes a body, a center body, a separator inlet, and a separator outlet fluidly coupled with the turbine section to output a reduced-particle stream that is provided to the turbine section for cooling. The centrifugal separator includes an angular velocity increaser, a flow splitter, a first outlet passage defined by an inner annular wall that receives the reduced-particle stream, and an angular velocity decreaser located downstream of the flow splitter. A second outlet passage receives the concentrated-particle stream.

Inducer assembly for a turbine engine

An airfoil for a turbine engine includes a body defining a pressure side and a suction side, the body extending between a leading edge and a trailing edge and also extending radially to define an outer edge. A radially-extending plenum can be disposed at the outer edge of the airfoil. A flared portion can be disposed at the outer edge of the body extending from the suction side.

Airfoils for gas turbine engines

A turbine engine having a compressor section, a combustor section, a turbine section, and a rotatable drive shaft that couples a portion of the turbine section and a portion of the compressor section. A bypass conduit couples the compressor section to the turbine section while bypassing at least the combustion section. At least one particle separator is located in the turbine engine having a separator inlet that receives a bypass stream, a separator outlet that receives a reduced-particle stream flows, and a particle outlet that receives a concentrated-particle stream comprising separated particles. A conduit, fluidly coupled to the particle outlet, extends through an interior of at least one stationary vane.

An airfoil for a gas turbine engine defining a radial direction and an axial direction, the airfoil including: a flared portion extending from a suction surface of the airfoil at an outer edge of the airfoil along the radial direction; and a plenum disposed at the outer edge of the airfoil, the plenum having a suction-side sidewall and a pressure-side sidewall, wherein the suction-side sidewall has a first sidewall portion adjacent to a second sidewall portion disposed outside of the first sidewall portion along the radial direction, wherein the first sidewall portion defines a first angle, wherein the second sidewall portion defines a second angle, and wherein the first angle is greater than the second angle.

A turbomachinery component with a surface that includes a bounded wear coat, the component includes: a body; a contact surface defined by the body; a recess extending into the body and communicating with the contact surface; and a wear coat positioned in the recess.

Turbine component with bounded wear coat

A turbine engine having an inducer assembly. The inducer assembly includes a centrifugal separator fluidly coupled to an inducer with an inducer inlet and an inducer outlet. The centrifugal separator includes a body, an angular velocity increaser to form a concentrated-particle stream and a reduced-particle stream, a flow splitter, and an exit conduit fluidly coupled to the body to receive the reduced-particle stream and define a separator outlet.

The disclosure relates to a gas turbine engine and a method of controlling an upstream extent of a bow wave from an airfoil having a pressure side and a suction side in the turbine engine. In one aspect, the method includes forming a vortex at a leading edge of the airfoil.

Turbine engine airfoil and method

An assembly for removing particles from a fluid stream includes a first particle remover having a main flow outlet emitting a first reduced-particle stream and a scavenge flow outlet emitting a particle-laden stream, as well as a second particle remover fluidly coupled to the scavenge flow outlet and emitting a second reduced-particle stream.

Assembly for particle removal

A component assembly for a gas turbine engine having a combustor and defining a core air flowpath includes a first wall and a second wall. The first wall is configured for at least partially defining the core air flowpath at a location downstream of a combustion chamber defined by the combustor of the gas turbine engine. Additionally, the second wall is also configured for at least partially defining the core air flowpath at a location downstream of the combustion chamber, and is located opposite the core air flowpath of the first wall. The second wall includes a plurality of fins extending towards the first wall along the radial direction and spaced along the circumferential direction.

Component assembly for a gas turbine engine

A turbine engine having a bypass fluid conduit coupled to the turbine section includes at least one particle separator located within the bypass fluid conduit to separate particles from a bypass fluid stream prior to the bypass stream reaching the turbine section for cooling. A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser, a particle outlet, an angular velocity decreaser downstream of the angular velocity increaser, and a bend provided between the angular velocity increaser and the angular velocity decreaser.

Turbine engine and particle separators therefore

A centrifugal separator for removing particles from a fluid stream includes an angular velocity increaser configured to increase the angular velocity of a fluid stream, a flow splitter configured to split the fluid stream to form a concentrated-particle stream and a reduced-particle stream, and an exit conduit configured to receive the reduced-particle stream. An inducer assembly for a turbine engine includes an inducer with a flow passage having an inducer inlet and an inducer outlet in fluid communication with a turbine section of the engine, and a particle separator, which includes a particle concentrator that receives a compressed stream from a compressor section of the engine and a flow splitter. A turbine engine includes a cooling air flow circuit which supplies a fluid stream to a turbine section of the engine for cooling, a particle separator located within the cooling air flow circuit, and an inducer forming a portion of the cooling air flow circuit in fluid communication with the particle separator. A method of cooling a rotating blade of a turbine engine having an inducer includes directing a cooling fluid stream from a portion of turbine engine toward the rotating blade, separating particles from the cooling fluid stream by passing the cooling fluid stream through a inertial separator, accelerating a reduced-particle stream emitted from the inertial separator to the speed of the rotating blade, and orienting the reduced-particle stream by emitting the reduced-particle stream from the inertial separator into a cooling passage in the inducer.

Turbine engine, components, and methods of cooling same

A blade for a gas turbine engine comprises an airfoil having a pressure side and a suction side, with a root and a tip wall. The pressure side and suction side extend beyond the tip wall to define a tip channel, defining a plurality of internal and external corners. The corners comprise fillets to define a thickness being greater than the thickness for the pressure, suction, or tip walls. A film hole can extend through the fillet, such that the length of the film hole at the fillet can be increased to define an increased length-to-diameter ratio for the film hole to improve film cooling through the film hole.

Fillet optimization for turbine airfoil

Turbine nozzle segments and systems are provided. For example, a turbine nozzle segment comprises an airfoil extending axially between leading and trailing edges; an inner band defining a portion of a flow path inner boundary; and an outer band defining a portion of a flow path outer boundary. An airfoil trailing edge portion defines the trailing edge and extends axially beyond the inner and outer bands such that the trailing edge is defined axially aft of the inner and outer band aft ends. An exemplary turbine nozzle system comprises the turbine nozzle segment, an outer member positioned aft of the outer band at the trailing edge portion outer end to define the flow path outer boundary along the trailing edge portion, and an inner member positioned aft of the inner band at the trailing edge portion inner end to define the flow path inner boundary along the trailing edge portion.

Turbine nozzle with CMC aft band

An apparatus and method for separating dust from a dirty air flow within an airfoil assembly for a turbine engine. The air foil assembly can include a pair of vanes defining a nozzle through which a flow of air can move. At least one of the vanes can include an insert located within an interior of the vane and having a set of holes.

Engine component with insert

A compliant seal component, a turbomachine including such compliant seal component, and an associated method for cooling the compliant seal component disposed in the turbomachine are disclosed. The compliant seal component includes a convoluted portion and a plurality of end portions spaced apart from each other. The plurality of end portions is joined to the convoluted portion. An end portion of the plurality of end portions includes a first section and a second section, the second section defining a plenum. The end portion further includes a plurality of inlet holes and a plurality of outlet holes. The plurality of inlet holes is configured to direct a portion of a cooling fluid to the plenum. The portion of the cooling fluid in the plenum is configured to cool the end portion. The plurality of outlet holes is configured to discharge the portion of the cooling fluid from the plenum.

Growing community of inventors

Milton Mills, NH, United States of America

Victor Hugo Silva Correia