Device for deicing a splitter nose and inlet guide vanes of an aviation turbine engine
US10738650B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jan 10, 2017 |
| Grant date | Aug 11, 2020 |
| Priority date | — |
| Expiry date | Jul 6, 2037 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/121
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A deicer device deices both a splitter nose and inlet guide vanes of an aviation turbine engine. The device includes a splitter nose to split a stream coming from the fan into primary and secondary stream flow channels of annular shape and an inner shroud to which inlet guide vanes are fastened and including a hook that holds the inner shroud axially at its upstream end against the inner annular wall. An outer surface facing of the hook forms an angle of less than 90° with an injection orifice such that the outer surface comes progressively closer to the outer annular wall on going away from the injection orifice. The outer surface of the hook presents a minimum amount of clearance J relative to the outer annular wall such that 0.2≤J/D≤0.6 where D is the hydraulic diameter of an injection orifice.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.