公开(公告)号：US11753990B2

公开(公告)日：2023-09-12

申请号：US17864982

申请日：2022-07-14

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

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

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

CPC classification number: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00 ,  F05D2220/32

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：US11448125B2

公开(公告)日：2022-09-20

申请号：US16999408

申请日：2020-08-21

Applicant: RAYTHEON TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Mark Tu ,  Paul R Hanrahan ,  Arthur M. Salve, Jr.

IPC: F02C3/113 ,  F02C3/14 ,  F02C9/56 ,  F02K3/10 ,  F02C9/00

Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a high pressure turbine having a first stage and a second stage, 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; a high pressure compressor connected to a high pressure compressor spool; and a 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 connected to the high pressure compressor spool.

公开(公告)号：US11193425B2

公开(公告)日：2021-12-07

申请号：US16445469

申请日：2019-06-19

Applicant: Raytheon Technologies Corporation

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

IPC: F02C7/36 ,  F02C7/32 ,  F02C6/08

Abstract: A turbine engine includes a core engine including a first spool and a second spool rotatable about a main engine longitudinal axis, a boost spool powered by a secondary drive system, and an accessory gearbox coupled to the core engine and the boost spool. A differential gear system is coupled between the core engine, the boost spool and the accessory gearbox for distributing power between the boost spool, the core engine and the accessory gearbox.