Turbine engine including a continuous wave detonation chamber and cooling bypass flow and aircraft provided with such a turbine engine
US9556794B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | May 9, 2012 |
| Grant date | Jan 31, 2017 |
| Priority date | — |
| Expiry date | Dec 29, 2032 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The chamber (4) of the turbine engine (1) comprises a continuous detonation wave engine (6) provided with an annular detonation chamber (7) and associated means (8, 9) that can be used to generate a continuous production of hot gases from a detonation mixture of fuel and air. The continuous detonation wave engine (6) is arranged such as to form, from a flow of incoming air (E), a first flow (F1) which enters the detonation chamber (7) and which is used by the engine (6) and a second flow (F2) which bypasses the chamber. The turbine engine (1) also includes auxiliary means (10) for mixing the hot gases (F3) leaving the detonation chamber (7) with the second flow of air (F2) before directing same towards the turbine (5). A plurality of detonation chambers (7) are arranged concentrically to one another relative to the axis of the turbine engine.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.