Constant-volume combustion module for a turbine engine
US10662874B2 · kind B2 · utility
0Cited by
4References
7Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Jan 25, 2016 |
| Grant date | May 26, 2020 |
| Priority date | — |
| Expiry date | Nov 24, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/35
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A combustion module of a turbine engine, in particular of an aircraft, is configured for carrying out constant-volume combustion. The module includes a plurality of combustion chambers angularly distributed in a regular manner around an axis. Each chamber has an intake port for pressurized gas and an exhaust port for combustion gases. Each intake/exhaust port is configured to be opened or closed by a corresponding common rotating intake/exhaust valve which is coaxial with the axis.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.