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.