- 专利标题: SYSTEM AND METHOD FOR COOLING A LEADING EDGE OF A HIGH SPEED VEHICLE
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申请号: US17114908申请日: 2020-12-08
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公开(公告)号: US20220177111A1公开(公告)日: 2022-06-09
- 发明人: Nicholas William Rathay , Gregory Alexander Natsui , Brian Magann Rush
- 申请人: General Electric Company
- 申请人地址: US NY Schenectady
- 专利权人: General Electric Company
- 当前专利权人: General Electric Company
- 当前专利权人地址: US NY Schenectady
- 主分类号: B64C1/38
- IPC分类号: B64C1/38 ; B64C30/00 ; F28D15/04 ; F28D15/02 ; B64C3/36 ; B64C1/06
摘要:
A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.