Unison Industries, Inc.

General Electric Company

Derek Thomas Dreischarf

Bernard Albert Luschek

Scott Patrick Ryczek

Walter Arthur Hundley

Dennis Alan McQueen

Jason Levi Burdette

Daniel Scott McCann

Courtland Earl Pegan, Jr

Dattu G V Jonnalagadda

Michael Ralph Storage

Joseph Richard Schmitt

Dattu Gv Jonnalagadda

Kurt Thomas Hildebrand

David Bruce Rader

David William Millward

Walter Arthur Hundley, Jr

Mark Phillip Drake

Jayme Lee Carper

Anthony Lynn Lighthill

Courtland Earl Pegan

Daniel Scott Mccann

Jr Courtland Earl Pegan

A turbine engine for an aircraft can includes a casing. The casing can be a fan casing surrounding a fan assembly for drawing air into the turbine engine. The fan casing can have a peripheral wall. A surface cooler can be provided in the turbine engine confronting the peripheral wall of the fan casing. The surface cooler can have a mounting bracket for mounting the surface cooler to the fan casing.

Fan casing and mount bracket for oil cooler

A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and a mounting assembly having a lower portion generally retained between the first surface of the annular surface cooler and the peripheral wall and having a floating body extending through the set of fan casing fastener openings and an upper portion located radially exterior of the annular fan casing and operably coupled to the lower portion.

Mounting assembly and fan casing assembly

A heat exchanger including a manifold body having at least one fluid passage, a cooling passage section having a body including a set of fluid passages extending through at least a portion of the cooling passage section, and a weld joint fluidly sealing the manifold body and the cooling passage such that at least one of the set of fluid passages is fluidly coupled to the at least one fluid passage of the manifold body and methods of forming.

Heat exchanger and methods of forming

A surface cooler assembly includes at least one surface cooler comprising surface cooler hook rails extending circumferentially the length of the surface cooler and including axially extending and radially extending portions. The surface cooler assembly also includes at least one support bracket comprising bracket hook rails extending circumferentially the length of the support bracket and including axially extending and radially extending portions. The support bracket and surface cooler are contoured in a circumferential direction. Each of the surface cooler hook rails contacts a bracket hook rail.

Integral preloaded formed bracket for attachment of heat exchangers

A turbine engine with a casing including opposing surfaces and a manifold opening passing through the surfaces. A surface cooler is provided adjacent one of the surfaces. A cooler manifold passes through the manifold opening. A seal is provided between the surface cooler and the casing. At least one bolt is used to secure the surface cooler to the casing with the seal in between.

Turbine engine thermal seal

A fan casing assembly for a turbine engine including a casing having an annular fan cooler. The annular fan cooler includes first and second connection assemblies to fix movement of the fan cooler during engine operation, while permitting circumferential thermal growth of the fan cooler without suffering from high cycle fatigue.

Turbine engine cooler assembly

A fan casing assembly for a turbine engine including a fan casing having a peripheral wall, a surface cooler having a first surface confronting the peripheral wall and forward and aft projections, which are radially spaced from the first surface and located between the peripheral wall and the first surface, and a mounting bracket to mount the surface cooler to the fan casing and a method of mounting a surface cooler to a fan casing of a turbine engine.

Fan casing assemblies and method of mounting a cooler to a fan casing

A system for use in limiting axial movement between a hanger and a fairing assembly within a turbine assembly is provided. The hanger includes an inner radial hanger bend portion that defines a hook channel therein. The fairing assembly includes an outer surface, a hook member extending from the outer surface to mate with the hook channel, and a circumferential groove defined in the outer surface such that at least a portion of the hanger bend portion is positioned between the circumferential groove and the hook member. The system includes a retention member sized for insertion into the circumferential groove, wherein the retention member is configured to extend from the circumferential groove and press against the hanger bend portion to facilitate maintaining the hook member within the hook channel.

System and method of limiting axial movement between components in a turbine assembly

A fairing for a turbine engine strut includes: inner and outer bands; a vane extending between the bands; the fairing is split along a generally transverse plane passing through the bands and the vane, defining nose and tail pieces; wherein the vane is defined by spaced-apart sidewalls extending between a leading edge and a trailing edge, each sidewall split into forward and aft portions by the transverse plane; wherein each sidewall portion carries a radially-inwardly extending post, the posts positioned such that pairs of the posts lie adjacent to each other when the nose piece and tail piece are assembled, wherein each pair of adjacent posts includes at least two non-parallel faces; and a pair of slotted buckles, wherein each slotted buckle surrounds and clamps together a pair of the posts, wherein each pair of adjacent posts contacts a slot of the corresponding buckle in a tripod contact configuration.

Tripod buckle for split fairing of a gas turbine engine

A surface heat exchanger is provided which utilizes forward and aft brackets to retain the heat exchanger in position. The surface heat exchanger includes a plurality of core cooling channels as well as fins which are disposed for air flow through the gas turbine engine. The brackets include a low-friction wear material as well as an isolator sheet which provides some spring force on the heat exchanger.

Surface cooler support mechanism

Gas turbine engine frames are disclosed. An example gas turbine engine frame may include a generally annular outer casing disposed coaxially about a hub; a plurality of circumferentially spaced apart struts joined to the hub and the outer casing, individual struts extending radially outwardly from the hub to the outer casing; and a stiffening rail monolithically formed with the outer casing circumferentially between two of the struts. The stiffening rail may extend radially inward beyond the inner surface of the outer casing between the struts.

Growing community of inventors

Bellbrook, OH, United States of America

Derek Thomas Dreischarf