General Electric Company

Ramon Martinez

Michael Anthony Benjamin

Joshua Tyler Mook

Nicolas Kristopher Sabo

Sean James Henderson

Jeffrey Douglas Rambo

Jared Matthew Wolfe

David Richard Barnhart

Donald Lee Gardner

Raymond Floyd Martell

Mark Richard Shaw

Curt Edward Hogan

Michael Stephen Popp

Neerav Atul Patel

Donald Michael Corsmeier

Gregg Hunt Wilson

Paul Charles Johnson

Benjamin Paul Breig

Alex William Ariapad

Matthew Ryan Johns

Matthew John Hurt

Keith Alan Joerger

Matthew John Hunt

Nicholas Kristopher Sabo

A heat exchanger for a gas turbine engine includes a heat exchanger body having a first surface and a second surface oriented at least partially at an oblique angle relative to the first surface. The heat exchanger body defines a plenum extending between the first and second surfaces. Furthermore, the heat exchanger body defines a fluid passage extending through the second surface such that the fluid passage is in fluid communication with the plenum. The fluid passage, in turn, includes first and second portions. The first portion intersects the plenum at an intersection and defines a line of projection extending normal to the second surface. The second portion defines a line of projection extending normal to the first surface. The fluid passage further includes a curved portion extending from the first portion to the second portion.

Heat exchanger having curved fluid passages for a gas turbine engine

A heat exchanger and heat exchanger core are provided. The heat exchanger core includes a plurality of columnar passages extending between an inlet plenum of the heat exchanger core and an outlet plenum of the heat exchanger core, the columnar passages formed monolithically in a single fabrication process.

Contoured wall heat exchanger

A fuel nozzle apparatus includes: an outer body having an exterior surface and a plurality of openings in the exterior surface. An inner body is disposed inside the outer body, cooperating with the outer body to define an annular space. A main injection ring is disposed in the annular space and includes an array of fuel posts extending outward therefrom, each fuel post including a perimeter wall defining a lateral surface and a recessed floor. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap defined between the opening and the lateral surface. A main fuel gallery extends within the main injection ring. The main injection ring includes plurality of main fuel orifices, each main fuel orifice communicating with the main fuel gallery and extending through one of the fuel posts.

Fuel nozzle structure for air assist injection

A heat exchanger for an aircraft includes an inlet plenum housing defining an inlet plenum configured to receive a fluid and an outlet plenum housing defining an outlet plenum configured to discharge the fluid. Furthermore, the heat exchanger includes a core configured to heat or cool a first portion of the fluid, with the core defining a plurality of fluid passages extending from the inlet plenum to the outlet plenum. Moreover, the heat exchanger includes a passive bypass defining a passive bypass flow path fluidly coupled to and extending between the inlet plenum and the outlet plenum. As such, the passive bypass flow path is in parallel with at least a portion of the core such that a second portion of the fluid bypasses at least a portion of the core and flows continuously and unobstructed through the passive bypass flow path to the outlet plenum.

Heat exchanger for an aircraft

An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.

Fuel nozzle heat shield

A fuel nozzle includes an outer body extending parallel to a centerline axis, having a generally cylindrical exterior surface, forward and aft ends, and a plurality of openings through the exterior surface. The fuel nozzle further includes an inner body inside the outer body, cooperating with the outer body to define an annular space, and a main injection ring inside the annular space, the main injection ring including fuel posts extending therefrom. Each fuel post is aligned with one of the openings and separated from the opening by a perimeter gap which communicates with the annular space. There is a circumferential main fuel gallery in the main injection ring, and a plurality of main fuel orifices, wherein each orifice communicates with the main fuel gallery and extends through one of the fuel posts.

An additively manufactured heat exchanger and a method of manufacturing the same are provided. The heat exchanger includes a plurality of walls spaced apart to define a plurality of fluid passageways and a plurality of flow turbulators extending between two adjacent walls through the fluid passageways. The walls and flow turbulators define one or more internal fluid passageways in thermal communication with the plurality of fluid passageways which receive a flow of auxiliary heat exchange fluid for enhancing the heat transfer efficiency of the heat exchanger.

Additively manufactured heat exchanger including flow turbulators defining internal fluid passageways

A method and a system for a heat exchanger assembly are provided. The heat exchanger assembly includes one or more arcuate heat exchanger segments each including an inlet header configured to extend circumferentially about a circumference of an inner surface of a fluid flow duct, and an outlet header configured to extend circumferentially about the fluid flow duct. The heat exchanger assembly also includes a first serpentine heat exchanger tube extending between the inlet header and the outlet header and including a series of flow path segments having a gradually changing direction defined by a bend radius of the tube such that a direction of flow through the serpentine heat exchanger tube reverses between the inlet and the outlet headers and a second serpentine heat exchanger tube extending between the inlet header and the outlet header, the second serpentine heat exchanger tube co-planar with the first serpentine heat exchanger tube.

Method and system for radial tubular heat exchangers

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Fairfield, OH, United States of America

Ramon Martinez