Supersonic air inlet of an aircraft propelling assembly comprising a support arm de-icing device and de-icing method
US12037940B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 1, 2021 |
| Grant date | Jul 16, 2024 |
| Priority date | — |
| Expiry date | Oct 1, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2220/80
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A supersonic air intake of an aircraft propulsion assembly comprises: •⋅ pipe with a longitudinal axis configured to guide the flow of air into the turbine engine, •⋅ a speed reducer fixedly mounted inside the pipe along the longitudinal axis, •⋅ at least one support arm linking the speed reducer to the pipe and having an upstream outer wall and a downstream outer wall together defining a cavity, and •⋅ at least one de-icing device having an inner wall mounted in the cavity opposite the upstream outer wall in order to together define a calibrated de-icing space, as well as a member for supplying and a member for discharging a de-icing air flow in the de-icing space.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.