Anti-icing core inlet stator assembly for a gas turbine engine
US9291064B2 · kind B2 · utility
3Cited by
12References
3Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 6, 2012 |
| Grant date | Mar 22, 2016 |
| Priority date | — |
| Expiry date | Mar 18, 2034 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/32
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine is defined wherein the inlet guide vanes leading into a core engine flow path are sized and positioned such that flow paths positioned circumferentially intermediate the vane are sufficiently large that a hydraulic diameter of greater than or equal to about 1.5 is achieved. This will likely reduce the detrimental effect of icing.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.