Recovered-cycle turboshaft engine
US12305570B2 · kind B2 · utility
0Cited by
4References
13Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jan 2, 2023 |
| Grant date | May 20, 2025 |
| Priority date | — |
| Expiry date | Jan 2, 2043 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/76
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turboshaft engine for an air-craft including a gas generator including a compressor, a combustion chamber and an expansion turbine; a power turbine rotating a power take-off by a reduction gear; a heat exchanger including a first circuit and a second circuit. The compressor includes a first shaft rotated by a second shaft of the expansion turbine by a trans-mission mechanism, the transmission mechanism and the reduc-tion gear forming part of a gearbox which is arranged axially at a front end of the turboshaft engine, such that the compressor is arranged axially between the gearbox and the power turbine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.