公开(公告)号：US20240076050A1

公开(公告)日：2024-03-07

申请号：US18215394

申请日：2023-06-28

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06

CPC classification number: B64D27/26 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06 ,  B64D2027/266 ,  B64D2027/268 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a gear train, a compressor section and a turbine section. A static structure includes a first case and a second case. The first case includes a first engine mount location. The second case includes a second engine mount location. The first engine mount location is axially near the gear train.

公开(公告)号：US11286883B2

公开(公告)日：2022-03-29

申请号：US16405149

申请日：2019-05-07

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06 ,  B64D27/26 ,  F02C7/36 ,  F02C3/107 ,  F01D5/06 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F02K1/15 ,  F02C9/20 ,  F02C9/18 ,  F01D9/02 ,  F01D15/12 ,  F01D1/12

Abstract: A gas turbine engine includes, among other things, a fan section including a fan rotor, a gear train defined about an engine axis of rotation, a high spool, and a low spool including a low pressure turbine that drives the fan rotor through the gear train. A static structure includes a first engine mount location and a second engine mount location.

公开(公告)号：US20210372349A1

公开(公告)日：2021-12-02

申请号：US17395553

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02C9/20 ,  F02C9/18 ,  B64D27/26 ,  F02C7/36 ,  F02C3/107 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C7/20 ,  F02K1/15

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.

公开(公告)号：US20220195928A1

公开(公告)日：2022-06-23

申请号：US17132080

申请日：2020-12-23

Applicant: Raytheon Technologies Corporation

Inventor： Steven B. Johnson ,  Andrew J. Murphy

IPC: F02C7/224 ,  F02C7/16 ,  F02C7/141 ,  F02C3/22 ,  F02C7/06 ,  B64D37/30 ,  B64D37/34

Abstract: Turbine engine systems and aircraft having such systems are described. The turbine engine systems include a combustor arranged along a core flow path of the turbine engine, a drive shaft having at least a compressor section and a turbine section coupled thereto, a cryogenic fuel tank configured to supply a fuel to the combustor, and an expansion turbine mechanically coupled to the drive shaft, the expansion turbine configured to receive fuel from the cryogenic fuel tank and expand said fuel, wherein expansion of said fuel by the expansion turbine drives rotation of the expansion turbine to provide power input to the drive shaft.

公开(公告)号：US11731773B2

公开(公告)日：2023-08-22

申请号：US17395553

申请日：2021-08-06

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Christopher M. Dye ,  Steven B. Johnson ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F01D25/28 ,  F02C7/20 ,  F02K3/06 ,  F02C9/20 ,  F02C9/18 ,  F02C7/36 ,  F02C3/107 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F02K1/15

CPC classification number: B64D27/26 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06 ,  B64D2027/266 ,  B64D2027/268 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2270/42

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor, a gear train, a low spool and a high spool. A static structure includes a first case and a second case. A mount system includes a forward mount and an aft mount arranged in a plane containing an engine axis of rotation. The forward mount is secured to the first case. The aft mount is secured to the second case.