Anti-icing core inlet stator assembly for a gas turbine engine
US11391205B2 · kind B2 · utility
0Cited by
14References
5Claims
0Family size
Assignee
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Key dates
| Filing date | Dec 4, 2015 |
| Grant date | Jul 19, 2022 |
| Priority date | — |
| Expiry date | Mar 6, 2041 |
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.