公开(公告)号：US20240191659A1

公开(公告)日：2024-06-13

申请号：US18183758

申请日：2023-03-14

Applicant: General Electric Company

Inventor： Robert B. Brown ,  Brian Devendorf ,  Stephen G. Matava ,  Emma Lebwohl ,  Michael T. Hogan ,  Susan Frances Redus

IPC: F02C7/14 ,  F02C7/055 ,  F02C7/18

CPC classification number: F02C7/14 ,  F02C7/055 ,  F02C7/18 ,  F02C7/08

Abstract: Example systems and methods for integrating an air-cooled oil cooler into an inlet frame of an engine are provided. An example gas turbine engine comprises an inlet frame including an inlet plenum at a first end of an inlet frame flow path, the inlet frame defining an airflow entrance to a compressor; the compressor to provide an airflow through the inlet frame; a pump to circulate a fluid; a plurality of struts supporting the inlet frame flow path; and a fluid core connected to the pump and built at least partially into the inlet frame of the gas turbine engine, the fluid core to route the fluid through the inlet plenum.

公开(公告)号：US20250075662A1

公开(公告)日：2025-03-06

申请号：US18461078

申请日：2023-09-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： John Carl Glessner ,  Stephen G. Matava

IPC: F02C7/32 ,  F02C3/06

Abstract: A turbine engine having an inner cowl that circumscribes at least a portion of an engine core, where the inner cowl is radially spaced from the engine core to define an inner cowl space. An outer cowl circumscribes at least a portion of the inner cowl where the outer cowl includes a radially outer surface spaced from a radially inner surface to define an outer cowl space. A fairing extends radially between the inner cowl and the outer cowl. A first accessory gearbox is located in the inner cowl space and the fairing. A second accessory gearbox is located in the outer cowl space and operably couples to the first accessory gearbox.

公开(公告)号：US12228075B2

公开(公告)日：2025-02-18

申请号：US18183758

申请日：2023-03-14

Applicant: General Electric Company

Inventor： Robert B. Brown ,  Brian Devendorf ,  Stephen G. Matava ,  Emma Lebwohl ,  Michael T. Hogan ,  Susan Frances Redus

IPC: F02C7/14 ,  F02C7/055 ,  F02C7/18 ,  F02C7/08

Abstract: Example systems and methods for integrating an air-cooled oil cooler into an inlet frame of an engine are provided. An example gas turbine engine comprises an inlet frame including an inlet plenum at a first end of an inlet frame flow path, the inlet frame defining an airflow entrance to a compressor; the compressor to provide an airflow through the inlet frame; a pump to circulate a fluid; a plurality of struts supporting the inlet frame flow path; and a fluid core connected to the pump and built at least partially into the inlet frame of the gas turbine engine, the fluid core to route the fluid through the inlet plenum.

公开(公告)号：US12129767B1

公开(公告)日：2024-10-29

申请号：US18333328

申请日：2023-06-12

Applicant: General Electric Company

Inventor： Patrick S. Sage ,  Steven M. McDonough ,  Mahesh Khandeparker ,  Stephen G. Matava ,  Shashi Alok

IPC: B64D27/12 ,  F01D25/28

CPC classification number: F01D25/28 ,  F05D2220/323

Abstract: Gas turbine mounting configurations for backbone bending mitigations are described herein. An example gas turbine engine disclosed herein includes a pylon, an inlet to be subjected to an inlet load along an inlet load axis, a case assembly including a first case portion and a second case portion, a forward mount coupling the first case portion to the pylon, the coupling of the forward mount to the pylon defining a first line of action, an aft mount, and a thrust link coupling the second case portion to the pylon, the thrust link defining a second line of action, an intersection of the first line of action and the second line of action disposed at least one of: (1) on the inlet load axis and the centerline, (2) downstream of the inlet load axis and beneath the centerline, and (3) upstream of the inlet load axis and above the centerline.