An injector system for propelling an aircraft. The system includes a diffusion structure and a conduit coupled to the diffusion structure. The duct includes a wall having an opening formed therethrough and configured to introduce a primary fluid generated by the aircraft into the diffusion structure. The airfoil is located in a flow of the primary fluid through the opening to the diffusion structure.
用于推进飞行器的喷射器系统。该系统包括扩散结构和联接至该扩散结构的管道。该管道包括壁,该壁具有穿过其形成的开口,并构造成将由飞行器产生的主要流体引入扩散结构。翼型位于通过开口到达扩散结构的主要流体的流中。
Winglet injector configuration
小翼喷射器构造
2024-06-18
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |