公开(公告)号：US12179929B2

公开(公告)日：2024-12-31

申请号：US18215394

申请日：2023-06-28

Applicant: RTX CORPORATION

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

IPC: B64D27/40 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06

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：US11773782B2

公开(公告)日：2023-10-03

申请号：US17132080

申请日：2020-12-23

Applicant: RTX Corporation

Inventor： Steven B. Johnson ,  Andrew J. Murphy

IPC: F02C7/224 ,  F02C3/22 ,  F02C7/141 ,  F02C7/16

CPC classification number: F02C7/224 ,  F02C3/22 ,  F02C7/141 ,  F02C7/16 ,  F05D2260/213 ,  F05D2260/232

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：US20250058887A1

公开(公告)日：2025-02-20

申请号：US18937193

申请日：2024-11-05

Applicant: RTX CORPORATION

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

IPC: B64D27/40 ,  F01D5/06 ,  F01D9/02 ,  F01D15/12 ,  F01D25/24 ,  F01D25/28 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02C9/18 ,  F02C9/20 ,  F02K1/15 ,  F02K3/06

Abstract: A gas turbine engine includes, among other things, a propulsor section including a rotor and blades, a geared architecture including 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 geared architecture.