Gas turbines with multiple gas flow paths
US8104265B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Jun 28, 2007 |
| Grant date | Jan 31, 2012 |
| Priority date | — |
| Expiry date | Nov 30, 2030 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/4031
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor blades, a second set of high pressure compressor blades, a combustion section and a high pressure turbine, positioned along the first gas flow path; and in series order, the multi-stage fan and radially outboard portions of the first set of high pressure compressor blades, positioned along the second gas flow path such that the inboard portions of the first set of high pressure compressor blades, the second set of high pressure compressor blades, the combustion section and the high pressure turbine are not positioned along the second gas flow path.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.