公开(公告)号：US12246845B2

公开(公告)日：2025-03-11

申请号：US18246478

申请日：2021-05-20

Applicant: General Electric Company ,  Safran Aircraft Engines

Inventor： Michael Cline ,  Jonathan E. Coleman ,  Craig W. Higgins ,  Daniel E. Mollmann ,  Mark E. Linz ,  Guillaume Glemarec ,  Valerio Capasso ,  Jean-Baptiste Manuel Nicolas Vignes ,  Nicolas Maurice Hervé Aussedat ,  Francois Gallet

IPC: B64D27/40

Abstract: Methods, apparatus, systems and articles of manufacture for mounting a gas turbine engine are described. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.

公开(公告)号：US20230272744A1

公开(公告)日：2023-08-31

申请号：US17826321

申请日：2022-05-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Joseph G. Rose ,  Atanu Saha ,  Bhaskar Nanda Mondal ,  Craig W. Higgins ,  Darek Zatorski ,  Vaibhav Deshmukh M

IPC: F02C7/06 ,  F02C3/06

CPC classification number: F02C7/06 ,  F02C3/06 ,  F05D2240/52 ,  F05D2260/15 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/605 ,  F05D2260/607

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

公开(公告)号：US20250122849A1

公开(公告)日：2025-04-17

申请号：US18991142

申请日：2024-12-20

Applicant: General Electric Company

Inventor： Brandon W. Miller ,  Randy M. Vondrell ,  David M. Ostdiek ,  Craig W. Higgins ,  Alexander Simpson ,  William Bowden

IPC: F02K3/065 ,  F02C3/06

Abstract: A gas turbine engine includes a turbomachine defining an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct; a primary fan driven by the turbomachine; and a secondary fan located downstream of the primary fan within the inlet duct. The gas turbine engine defines a thrust to power airflow ratio between 3.5 and 100 and a core bypass ratio between 0.1 and 10. The thrust to power airflow ratio is a ratio of airflow through a bypass passage over the turbomachine plus airflow through the fan duct to airflow through the core duct. The core bypass ratio is a ratio of airflow through the fan duct to airflow through the core duct. The fan duct includes an exhaust nozzle having a plurality of chevrons disposed at its aft end to define an exhaust outlet.

公开(公告)号：US11859547B2

公开(公告)日：2024-01-02

申请号：US17826321

申请日：2022-05-27

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Joseph G. Rose ,  Atanu Saha ,  Bhaskar Nanda Mondal ,  Craig W. Higgins ,  Darek Zatorski ,  Vaibhav Deshmukh M

IPC: F02C7/06 ,  F02C3/06

CPC classification number: F02C7/06 ,  F02C3/06 ,  F05D2240/52 ,  F05D2260/15 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/605 ,  F05D2260/607

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

公开(公告)号：US20230356853A1

公开(公告)日：2023-11-09

申请号：US18246478

申请日：2021-05-20

Applicant: General Electric Company ,  Safran Aircraft Engines

Inventor： Michael Cline ,  Jonathan E. Coleman ,  Craig W. Higgins ,  Daniel E. Mollman ,  Mark E. Linz ,  Guillaume Glemarec ,  Valerio Capasso ,  Jean-Baptiste Manuel Nicolas Vignes ,  Nicolas Maurice Hervé Aussedat ,  Francois Gallet

IPC: B64D27/26

CPC classification number: B64D27/26 ,  B64D2027/268

Abstract: Methods, apparatus, systems and articles of manufacture are disclosed. An apparatus for mounting a gas turbine engine to a pylon, the gas turbine including an upstream section and a downstream section, the gas turbine defining a roll axis, a yaw axis, and a pitch axis, the apparatus including: a first mount to couple the upstream section of the gas turbine engine to the pylon; a second mount to couple the upstream section of the gas turbine engine to the pylon, the second mount downstream of the first mount; a thrust linkage to couple the upstream section to the pylon, wherein the downstream section is decouplable from the upstream section without decoupling the first mount, the second mount, and the thrust linkage.