发明名称 High-output turbo-pump for liquid-fuelled rocket motor - has large-diameter rotary shaft with high pressure turbine and supporting and fluid bearings
摘要 The turbo-pump consists of a large-diameter rotary shaft (22) carrying a high-pressure turbine (5) which forms a single pump stage to receive the liquid fuel through a suction duct (3) and deliver it under pressure through a feed duct (4). It has one bearing (23) to support the shaft (22) in a zone of reduced section situated in front of the turbine (5).There is a fluid bearing (24), able to withstand a high speed of rotation, situated in a zone of large section to the rear of the turbine, and at least one turbine stage (32, 33) to the rear of the fluid bearing. A high-pressure inductance fan (31) is situated in front of the bearing (23), and the turbo-pump is equipped with cast metal housing sections (1, 2, 38) of simple shape. ADVANTAGE - Simple and compact design, with reduced manufacturing costs.
申请公布号 FR2698661(A1) 申请公布日期 1994.06.03
申请号 FR19920014390 申请日期 1992.11.30
申请人 PROPULSION STE EUROPEENNE 发明人 LEHE JEAN-ROBERT;BEAURAIN ANDRE
分类号 F01D11/22;F02K9/48;F04D13/04;(IPC1-7):F02C6/10;F04D1/00;F04D29/00 主分类号 F01D11/22
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