公开(公告)号：US20210147086A1

公开(公告)日：2021-05-20

申请号：US16685541

申请日：2019-11-15

Applicant: General Electric Company

Inventor： Nicholas William Rathay ,  Gregory Alexander Natsui ,  Brian Magann Rush

IPC: B64D13/00 ,  B64C30/00 ,  B64C1/10 ,  F28F21/00

Abstract: 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 energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.