发明名称 |
METHOD FOR IMPROVING THE PERFORMANCE OF A BYPASS TURBOJET ENGINE |
摘要 |
The engine has a cooling air nozzle (T) with a throat arranged before a cooling air outlet orifice (6). An annular section of the throat has a nominal area fixed by thermodynamic cycle of the engine and lower than an area of the orifice such that a convergent-divergent nozzle (15) is formed at a rear part of an annular cooling air channel (12). The area of the orifice is adapted to a reference value of an expansion ratio of cooling air (9) comprised between extreme values of expansion ratios respectively corresponding to starting and ending of a cruising phase. An independent claim is also included for a method for improving performances of a ducted fan turbine engine that is mounted on an aircraft before accomplishing a determined flight mission. |
申请公布号 |
EP2212538(A2) |
申请公布日期 |
2010.08.04 |
申请号 |
EP20080871241 |
申请日期 |
2008.10.30 |
申请人 |
AIRBUS OPERATIONS SAS |
发明人 |
PRAT, DAMIEN;CROSTA, FRANK |
分类号 |
F02K3/06 |
主分类号 |
F02K3/06 |
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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