发明名称 |
COMBINED CYCLE INTEGRATED COMBUSTOR AND NOZZLE SYSTEM |
摘要 |
<p>An engine that operates and produces the entire required vehicle thrust below Mach 4 is useful for a Hypersonic combined cycle vehicle by saving vehicle and engine development costs. One such engine is a combined cycle engine having both a booster and a dual mode ramjet (DMRJ). The booster and the DMRJ are integrated to provide effective thrust from Mach 0 to in excess of Mach 4. As the booster accelerates the vehicle from Mach 0 to in excess of Mach 4, from Mach 0 to about Mach 2 incoming air delivered to the DMRJ is accelerated by primary ejector thrusters that may receive oxidizer from either on-board oxidizer tanks or from turbine compressor discharge air. As the TBCC further accelerates the vehicle from about Mach 0 to in excess of Mach 4 exhaust from the turbine and exhaust from the DMRJ are combined in a common nozzle disposed downstream of a combustor portion of the DMRJ functioning as an aerodynamic choke.</p> |
申请公布号 |
EP2094963(B1) |
申请公布日期 |
2013.09.11 |
申请号 |
EP20070867744 |
申请日期 |
2007.12.12 |
申请人 |
AEROJET-GENERAL CORPORATION |
发明人 |
BULMAN, MELVIN J. |
分类号 |
F02K7/16;F02K7/14;F02K7/18 |
主分类号 |
F02K7/16 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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