US 11,753,990 B2
Augmented drive of compressors via differential and multistage turbine
Daniel Bernard Kupratis, Wallingford, CT (US); Paul R. Hanrahan, Sedona, AZ (US); and Arthur M. Salve, Jr., Tolland, CT (US)
Assigned to RTX Corporation, Farmington, CT (US)
Filed by RAYTHEON TECHNOLOGIES CORPORATION, Farmington, CT (US)
Filed on Jul. 14, 2022, as Appl. No. 17/864,982.
Application 17/864,982 is a division of application No. 16/656,931, filed on Oct. 18, 2019, granted, now 11,421,590.
Claims priority of provisional application 62/890,825, filed on Aug. 23, 2019.
Claims priority of provisional application 62/890,848, filed on Aug. 23, 2019.
Claims priority of provisional application 62/890,836, filed on Aug. 23, 2019.
Prior Publication US 2022/0349341 A1, Nov. 3, 2022
Int. Cl. F02C 3/113 (2006.01); F02C 3/14 (2006.01); F02C 9/56 (2006.01); F02K 3/10 (2006.01); F02C 9/00 (2006.01)
CPC F02C 3/113 (2013.01) [F02C 3/14 (2013.01); F02C 9/56 (2013.01); F02K 3/10 (2013.01); F02C 9/00 (2013.01); F05D 2220/32 (2013.01)] 6 Claims
OG exemplary drawing
 
1. A gas turbine engine, comprising:
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;
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, an output gear assembly connected to the high pressure compressor spool, and a shaft connecting the output gear assembly, the first stage input gear, and the second stage input gear; and
an augmentation system configured to input power into at least one of the high pressure compressor spool and the high pressure turbine.