General Electric Company

Jonathan Russell Ratzlaff

Robert Proctor

Corey Bourassa

Jared Peter Buhler

Robert Carl Murray

Byron Andrew Pritchard, Jr

Robert Francis Manning

Victor Hugo Silva Correia

Steven Douglas Johnson

Curtis Walton Stover

Gregory Michael Laskowski

Timothy Deryck Stone

Kirk Douglas Gallier

Daniel Endecott Osgood

Aaron Ezekiel Smith

Michael Hogan

Prateek Jalan

Julius John Montgomery

Ravindra Shankar Ganiger

Ronald Scott Bunker

Steven Robert Brassfield

Rahul Anil Bidkar

Rajesh Kumar

Craig Alan Gonyou

John Howard Starkweather

Erich Alois Krammer

Kevin Samuel Klasing

David Vickery Parker

John Joseph Rahaim

William Collins Vining

Christophe Jude Day

Anthony Paul Greenwood

Alok Kumar

Uttara Vijay Kumar

Thomas Alan Wall

Kelli Marie Fishback

Kurt Thomas Whittington

Tajinder Singh

Jeremy Kevin Payne

Thomas Matthew Doerflein

John Wilbur Acree

Anthony James Bailey

Satyambabu Kalyani

Michael Alan Zupancic

Kevin William Caldwell

Ajay Kumar Verma

Sanjay Raju

Lucas Parisot

A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A seal assembly defines a primary seal at an interface of the rotor and the stator and separates an inlet plenum from an outlet plenum. The seal assembly includes one or more aspiration conduits fluidly connected to the primary seal. One or more flingers are positioned at least partially between the seal assembly and the inlet plenum that define one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits. The flingers are positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.

Seal assembly for a gas turbine engine

A cyclonic separator for a gas turbine engine includes a housing, a fluid inlet, a first fluid outlet, a second fluid outlet, and a particle separator. The housing includes a first end, a second end, and an outer wall extending between the first end and the second end. The fluid inlet is disposed at the first end of the housing. The first fluid outlet is disposed at the second end of the housing. The second fluid outlet is disposed in the outer wall downstream of the first end of the housing and extends outward at least partially in the radial direction. The particle separator is disposed in the housing between the first end and the second end inward of the outer wall in the radial direction and extends in the circumferential direction. The particle separator defines a plurality of openings extending in the radial direction.

Cyclonic separator for gas turbine engine

A rotary machine includes a stator and a rotor configured to rotate with respect to the stator. The rotor is arranged with the stator at a rotor-stator interface and defines a rotor face. The rotary machine also includes a seal assembly at the rotor-stator interface. The seal assembly includes a seal rotor, a seal stator, a seal slider, and a seal defined by a rotor face of the seal rotor and a slider face of the seal slider. Further, the seal assembly includes a flexible joint connected between the slider face and a primary seal body of the seal slider. The flexible joint is configured to locally decouple movement of the slider face from the seal slider to allow the slider face to track movement of the rotor apart from the primary seal body.

Seal assembly for a rotary machine having a flexible joint

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

A thermal management system for a gas turbine engine includes a heat exchanger including first and second sides, with the first side in contact with flow path air flowing through a flow path of the engine. Furthermore, the system includes a housing positioned relative to the heat exchanger such that the housing and the second side of the heat exchanger define a plenum configured to receive bleed air from the engine. Moreover, the system includes and at least one of a plurality of fins extending outward from the second side of the heat exchanger in a radial direction into the plenum and along the second surface of the heat exchanger in the circumferential direction or an impingement plate defining a plurality of impingement apertures, with each impingement aperture configured to direct an impingement jet of the bleed air within the plenum onto the second side of the heat exchanger.

Thermal management system for a gas turbine engine

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.

A component for a turbine engine includes a body having an outer surface confronting a combustion air flow path and defining an interior, as well as a first cooling passage having at least a portion supplying cooling air to the interior of the body. The component also includes a cyclone separator having a cooling air inlet, a clean air outlet, and a dirty air outlet.

Turbine engine component and method of cooling

A gas turbine engine includes a combustion section, a turbine section, and a compressor section. The combustion section includes a combustor casing, a combustor, a cooling duct, and an outer duct. The combustor casing defines at least in part a diffuser cavity and a fluid inlet. The combustor disposed is in the diffuser cavity. The cooling duct is in fluid communication with the fluid inlet in the combustor casing and is configured to transport a flow of cooled air. The outer duct surrounds at least a portion of the cooling duct and extends along a portion of an entire length of the cooling duct. The outer duct defines a gap with the cooling duct and is configured to transport a flow of buffer air. The turbine section is disposed downstream from the combustion section. The cooling duct is in fluid communication with the turbine section.

Cooling air delivery assembly

A hanger for a turbine engine can include a first surface confronting a cooling airflow, a second surface facing a heated airflow, and a third surface radially outward of the first surface. The hanger can also include a cyclonic separator with a dirty air inlet and a clean air outlet, as well as a cooling air circuit extending through the cyclonic separator.

Turbine engine hanger

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.

A component for a turbine engine includes a body having a wall at least partially defining an interior and separating a combustion air flow path from a cooling air flow path. The component also includes at least one fluid inlet supplying cooling air to the interior of the body, as well as a cyclone separator.

An airfoil assembly for a turbine engine that includes a platform, a dovetail, an airfoil. The airfoil assembly can further include a cooling air circuit that fluidly connects to a platform cooling passage. The cooling air circuit and platform cooling passage can be contained within or housed at least in part by the platform, the dovetail, or the airfoil. The cooling air circuit can also include a deflector.

Engine component with cooling hole

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

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Loveland, OH, United States of America

Jonathan Russell Ratzlaff