Gas turbine engine
US11976611B2 · kind B2 · utility
0Cited by
13References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Sep 8, 2022 |
| Grant date | May 7, 2024 |
| Priority date | — |
| Expiry date | Sep 8, 2042 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module, with a first electric machine being rotationally connected to the turbine module. The first electrical machine is configured to generate a maximum electrical power PEM1 (W), and the gas turbine engine is configured to generate a maximum dry thrust T (N); and a ratio S of: is in a range of between 2.0 and 10.0.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.