公开(公告)号：US08256203B1

公开(公告)日：2012-09-04

申请号：US12021142

申请日：2008-01-28

申请人： James B. Blackmon ,  David B. Landrum ,  Sean Entrekin

发明人： James B. Blackmon ,  David B. Landrum ,  Sean Entrekin

IPC分类号： F02K3/00

CPC分类号： F02K9/52 ,  F02K1/004 ,  F02K3/025 ,  F02K7/16 ,  F02K7/18 ,  F02K9/78

摘要： The present disclosure generally pertains to rocket based combined cycle (RBCC) propulsion units. In one exemplary embodiment, at least one rocket thruster is integrated with a jet engine but is external to the flow path of the jet engine, forming an altitude compensating plug nozzle. Since the rocket thruster is external to such flow path, the rocket flow from the rocket thruster interacts with the jet flow from the jet engine aft of the nozzle of the jet engine. Such interaction occurs without a significant performance penalty in the operation of the jet engine. In fact, it is possible that the interaction of the rocket flow with the jet flow may actually improve the efficiency of the jet engine under some conditions. Moreover, having the rocket thrusters positioned external to the flow path of the jet engine helps to avoid many of the problems plaguing conventional RBCC propulsion units.

摘要翻译： 本公开通常涉及基于火箭的联合循环（RBCC）推进单元。 在一个示例性实施例中，至少一个火箭推进器与喷气发动机集成在一起，但是在喷气发动机的流动路径的外部，形成高度补偿塞子喷嘴。 由于火箭推进器在这种流动路径的外部，所以来自火箭推进器的火箭流与来自喷气发动机的喷嘴后部的喷气发动机的喷射流相互作用。 这种相互作用在喷气发动机的操作中没有显着的性能损失。 事实上，火箭流与射流的相互作用有可能在某些条件下实际上提高喷气发动机的效率。 此外，将火箭推进器定位在喷气发动机的流动路径的外部有助于避免困扰常规RBCC推进装置的许多问题。