Mid-section of a can-annular gas turbine engine with an improved rotation of air flow from the compressor to the turbine
US9291063B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 29, 2012 |
| Grant date | Mar 22, 2016 |
| Priority date | — |
| Expiry date | Jul 31, 2033 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF23R3/425
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A midframe portion (313) of a gas turbine engine (310) is presented and includes a compressor section with a last stage blade to orient an air flow (311) at a first angle (372). The midframe portion (313) further includes a turbine section with a first stage blade to receive the air flow (311) oriented at a second angle (374). The midframe portion (313) further includes a manifold (314) to directly couple the air flow (311) from the compressor section to a combustor head (318) upstream of the turbine section. The combustor head (318) introduces an offset angle in the air flow (311) from the first angle (372) to the second angle (374) to discharge the air flow (311) from the combustor head (318) at the second angle (374). While introducing the offset angle, the combustor head (318) at least maintains or augments the first angle (372).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.