Gas turbine engine systems and related methods involving vane-blade count ratios greater than unity
US8468797B2 · kind B2 · utility
4Cited by
16References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 29, 2011 |
| Grant date | Jun 25, 2013 |
| Priority date | — |
| Expiry date | Dec 29, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2260/202
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An exemplary gas turbine engine includes a turbine section operative to impart rotational energy to a compressor section. The turbine section includes at least a low-pressure turbine and a high-pressure turbine, and a ratio of a number of stages in the low-pressure turbine to a number of stages in the high-pressure turbine is 2.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.