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 |
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.
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