Multistage gas turbine engine with differential drive of compressor
US11448125B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Aug 21, 2020 |
| Grant date | Sep 20, 2022 |
| Priority date | — |
| Expiry date | Dec 24, 2040 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/76
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
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.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.