-
公开(公告)号：US20230145878A1
公开(公告)日：2023-05-11
申请号：US17877566
申请日：2022-07-29
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Gary D. Roberge
CPC classification number: F02C7/22 , F02C3/22 , F02C9/30 , F04B9/113 , F04B15/08 , F02C7/224 , F04B2203/0903
Abstract: A fuel power transfer system for an engine may include a cryogenic fuel supply, a fuel pump in fluid communication with the cryogenic fuel supply, a multi-position valve in fluid communication with the fuel pump and a combustion chamber of the engine, a fuel turbine operatively coupled to the fuel pump and having a primary discharge port in fluid communication with the combustion chamber, a primary heat exchanger in fluid communication between the multi-position valve and the fuel turbine, and a gearbox operatively coupled to the fuel turbine and the fuel pump and configured to transfer power from the fuel turbine to the engine.
-
公开(公告)号：US20230122298A1
公开(公告)日：2023-04-20
申请号：US18068660
申请日：2022-12-20
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a propulsor section and a speed change mechanism for driving the propulsor section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers extending from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first propulsor section support bearing is mounted on a first axial side of the speed change mechanism and a second propulsor section support bearing is mounted on the bearing support on a second axial side of the speed change mechanism. The second propulsor section support bearing is a propulsor thrust bearing. Each of the plurality of fingers include a pin opening with a pin extending through the pin opening and into the epicyclic gear train.
-
公开(公告)号：US20230058015A1
公开(公告)日：2023-02-23
申请号：US17979393
申请日：2022-11-02
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A thermal management system for a gas turbine engine includes an additively manufactured nacelle component, at least a portion of the additively manufactured nacelle component forming an additively manufactured heat exchanger that extends into a fan bypass flow.
-
公开(公告)号：US11261827B2
公开(公告)日：2022-03-01
申请号：US16521970
申请日：2019-07-25
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge
IPC: F02K3/075 , F02C9/18 , F02K3/077 , F02C3/13 , F02C7/36 , F02K3/10 , F02K3/02 , F02K3/00 , F02C7/18 , F02C7/141 , F02K3/06 , F02K1/08 , F02K3/11
Abstract: A gas turbine engine has a fan rotor including at least one stage, with the at least one stage delivering a portion of air into a low pressure duct, and another portion of air into a compressor. The compressor is driven by a turbine rotor, and the fan rotor is driven by a fan drive turbine. A channel selectively communicates air from the low pressure duct across a boost compressor.
-
公开(公告)号：US11149645B2
公开(公告)日：2021-10-19
申请号：US16426260
申请日：2019-05-30
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section where the turbine section is downstream of the combustor section. A shaft connects the turbine section to the compressor section. A bore tube is disposed within the shaft downstream of the compressor section. The bore tube includes an inlet connected to an air source for passing cooling air in an upstream direction of the shaft.
-
Patent Agency Ranking
公开(公告)号：US11560852B2
公开(公告)日：2023-01-24
申请号：US17484331
申请日：2021-09-24
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
-
公开(公告)号：US11530616B2
公开(公告)日：2022-12-20
申请号：US17022650
申请日：2020-09-16
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge
Abstract: A seal assembly for a gas turbine engine, including: a first finger seal assembly, the first finger seal assembly including two layers each being secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the first finger seal assembly are secured to each other; a second finger seal assembly, the second finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the second finger seal assembly are secured to each other; and an arc-shaped segment finger seal assembly located between the first finger seal assembly and the second finger seal assembly, the arc-shaped finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the arc-shaped finger seal assembly are secured to each other.
-
公开(公告)号：US20220082026A1
公开(公告)日：2022-03-17
申请号：US17022650
申请日：2020-09-16
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge
IPC: F01D11/00
Abstract: A seal assembly for a gas turbine engine, including: a first finger seal assembly, the first finger seal assembly including two layers each being secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the first finger seal assembly are secured to each other; a second finger seal assembly, the second finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the second finger seal assembly are secured to each other; and an arc-shaped segment finger seal assembly located between the first finger seal assembly and the second finger seal assembly, the arc-shaped finger seal assembly including two layers each secured to each other, the two layers each having a plurality of slots that are offset from each other when the two layers of the arc-shaped finger seal assembly are secured to each other.
-
公开(公告)号：US20220010736A1
公开(公告)日：2022-01-13
申请号：US17484331
申请日：2021-09-24
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a fan section. A speed change mechanism drives the fan section. The speed change mechanism is an epicyclic gear train. A torque frame includes a ring and a plurality of fingers that extend from the ring with the plurality of fingers surrounding the speed change mechanism. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted on a first axial side of the speed change mechanism and a second fan section bearing is mounted on a second axial side of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
-
公开(公告)号：US11156166B2
公开(公告)日：2021-10-26
申请号：US16180548
申请日：2018-11-05
Applicant: Raytheon Technologies Corporation
Inventor： Gary D. Roberge , Michael E. McCune , William G. Sheridan
Abstract: A gas turbine engine includes a fan section and a speed change mechanism for driving the fan section. The speed change mechanism is an epicyclic gear train. A torque frame surrounds the speed change mechanism and includes a plurality of fingers. A bearing support is attached to the plurality of fingers. A first fan section support bearing is mounted forward of the speed change mechanism and a second fan section bearing is mounted on the bearing support aft of the speed change mechanism. The second fan section bearing is a fan thrust bearing.
-
-
-
-
-
-
-
-
-
Search Results
23
records
(took 0.018 seconds)
