发明名称 Exhaust nozzle for a liquid fuel rocket engine and associated method of manufacture
摘要 The nozzle(10) is formed as a body of revolution about a longitudinal axis(11) and has a cross section diameter that varies along this axis. The nozzle wall structure has multiple mutually adjacent cooling channels(11) helically extending in parallel from the nozzle inlet(13) to the nozzle outlet(14). The nozzle has at least two longitudinally adjacent sections(10a,10b,10c) with a shift between positive and negative channel angles from one section to the next.
申请公布号 SE518258(C2) 申请公布日期 2002.09.17
申请号 SE20010000076 申请日期 2001.01.11
申请人 VOLVO AERO CORP 发明人 JAN *HAEGGANDER
分类号 F02K;F02K9/64;F02K9/97;(IPC1-7):F02K9/64 主分类号 F02K
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