System and method for cooling a leading edge of a high speed vehicle
US11260953B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Nov 15, 2019 |
| Grant date | Mar 1, 2022 |
| Priority date | — |
| Expiry date | Jul 30, 2040 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64C30/00
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.