公开(公告)号：US20240052787A1

公开(公告)日：2024-02-15

申请号：US18233636

申请日：2023-08-14

Applicant: RTX Corporation

Inventor： Paul R. Hanrahan ,  David A. Stachowiak

IPC: F02C7/36 ,  B64D35/04

CPC classification number: F02C7/36 ,  B64D35/04 ,  F05D2260/4031 ,  F05D2260/902

Abstract: A first gear system includes a first sun gear, a first ring gear, first intermediate gears and a first carrier. The first intermediate gears are between and meshed with the first sun gear and the first ring gear. Each first intermediate gear is rotatably mounted to the first carrier. A second gear system includes a second sun gear, a second ring gear, second intermediate gears and a second carrier. The second ring gear is coupled to the first carrier. The second intermediate gears are between and meshed with the second sun gear and the second ring gear. Each second intermediate gear is rotatably mounted to the second carrier. A first propulsor rotor is coupled to the first carrier. A rotating structure is coupled to the first ring gear and includes a turbine rotor. The rotating structure is configured to drive rotation of the first propulsor rotor through the geartrain.

公开(公告)号：US20240018901A1

公开(公告)日：2024-01-18

申请号：US18364422

申请日：2023-08-02

Applicant: RTX CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan ,  Arthur M. Salve, JR.

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10

CPC classification number: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

公开(公告)号：US20230407817A1

公开(公告)日：2023-12-21

申请号：US18461709

申请日：2023-09-06

Applicant: RTX CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02K3/077 ,  F02K3/075

CPC classification number: F02K3/077 ,  F02K3/075 ,  F02K1/72

Abstract: A section for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor including a row of blades extending in a radial direction outwardly from a hub. The row of blades deliver flow to a bypass flow path, an intermediate flow path, and a core flow path. A first case surrounds the row of blades to establish the bypass flow path. A first flow splitter divides flow between the bypass flow path and a second duct. An aftmost row of guide vanes extends in the radial direction across the bypass flow path. A second flow splitter radially inboard of the first flow splitter divides flow from the second duct between the intermediate flow path and the core flow path. A bypass port interconnects the intermediate and bypass flow paths.