Micro reaction turbine with integrated combustion chamber and rotor
US8333060B2 · kind B2 · utility
6Cited by
5References
11Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Apr 24, 2008 |
| Grant date | Dec 18, 2012 |
| Priority date | — |
| Expiry date | Dec 10, 2029 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/82
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
When the compressor is a multistage compressor, each compression space includes an inlet arranged in the vicinity of the center axis and an outlet arranged in the vicinity of the outer circumference of the turbine wheel, and there is a connecting conduit between the outlet of a first compressor stage and the inlet of a second compressor stage. The connecting conduit is delimited by a first wall of the space of the first compressor stage and a second wall of the space of the second compressor stage. Each wall can be a friction disk.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.