发明名称 INJECTION DEVICE FOR COMBUSTION CHAMBERS OF LIQUID-FUELED ROCKET ENGINES
摘要 An injection device including at least one injection plate adjacent a combustion space of a combustion chamber, and at least one first injection nozzle including a first entry bore having a first discharge into the combustion chamber, and a first orifice bore, having a cross-sectional dimension less than or equal to the first entry bore, coaxially arranged with the first entry bore and remote from the first discharge. At least one second injection nozzle includes a second entry bore having a second discharge into the combustion chamber, and a second orifice bore, having a cross-sectional dimension less than or equal to the second entry bore, coaxially arranged with the second entry bore and remote from the second discharge. The instant abstract is neither intended to define the invention disclosed in this specification nor intended to limit the scope of the invention in any way.
申请公布号 US2010264240(A1) 申请公布日期 2010.10.21
申请号 US20100823326 申请日期 2010.06.25
申请人 EADS SPACE TRANSPORTATION GMBH 发明人 GOTZIG ULRICH;MAY DIETER
分类号 F23D11/36 主分类号 F23D11/36
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