High pressure ratio gas turbine engine
US11629668B2 · kind B2 · utility
0Cited by
5References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 9, 2021 |
| Grant date | Apr 18, 2023 |
| Priority date | — |
| Expiry date | Mar 9, 2041 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine including: a high pressure turbine, a low pressure turbine, a high pressure compressor coupled to the high pressure turbine by a high pressure shaft, a propulsor and a low pressure compressor coupled to the low pressure turbine via a low pressure shaft and a reduction gearbox; wherein the high pressure compressor defines an average stage pressure ratio at cruise conditions of between 1.25 and 1.35 and consists of 10 or 11 stages; and the high pressure compressor and low pressure compressor together define a core overall pressure ratio at cruise conditions of between 40:1 and 60:1.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.