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    Device for producing burnable gases for thrust engines
    1.
    发明授权
    Device for producing burnable gases for thrust engines 失效
    用于生产用于发动机的可燃气体的装置

    公开(公告)号：US3635030A

    公开(公告)日：1972-01-18

    申请号：US3635030D

    申请日：1969-11-05

    申请人： BOLKOW GMBH

    发明人： SCHUBERT JOHANNES ,  FUCHS ROLF

    IPC分类号： C06B45/12 ,  F02K7/18 ,  F02K9/14 ,  F02K9/72 ,  F02K7/10 ,  F02K9/06

    CPC分类号： F02K9/72 ,  C06B45/12 ,  F02K7/18 ,  F02K9/14 ,  Y10S60/917

    摘要： Burnable gases under pressure for operating engines such as thrust engines and particular rocket and ramjet engines are produced by arranging together two solid propellant charges, one of which comprises an auxiliary propellant charge having a high thermal efficiency and the other constituting a main propellant charge comprising a material of low heat of fusion and evaporation. The auxiliary charge is ignited by a fuse device and will burn off adjacent the main charge but shielded therefrom by a burn-off insulation. The burnable gases which are produced are directed by their own pressure through a gas duct into a combustion chamber where they are admixed with an oxidizer which may be supplied under the pressure force of the gases themselves.

    摘要翻译： 用于操作发动机例如推力发动机和特定火箭和冲压式发动机的可燃气体通过将两个固体推进剂装料布置在一起而产生，其中一个固体推进剂装料包括具有高热效率的辅助推进剂装料，另一个构成主推进剂装料， 熔融和蒸发热量低的材料。 辅助电荷由保险丝装置点燃，并且在主电荷附近被烧掉，但是被燃烧绝缘层隔离。 所生产的可燃气体通过其自身的压力通过气体管道引导到燃烧室中，在这些燃烧室中与可在气体本身的压力下供应的氧化剂混合。

    Method for producing burnable gases for thrust engines
    2.
    发明授权
    Method for producing burnable gases for thrust engines 失效
    用于制造用于发动机的可燃气体的方法

    公开(公告)号：US3595020A

    公开(公告)日：1971-07-27

    申请号：US3595020D

    申请日：1970-04-14

    申请人： BOLKOW GMBH

    发明人： SCHUBERT JOHANNES ,  FUCHS ROLF

    IPC分类号： F02K7/18 ,  F02K9/12 ,  F02K9/72 ,  F02K7/08 ,  F02K9/02

    CPC分类号： F02K7/18 ,  F02K9/12 ,  F02K9/72 ,  Y10S60/917

    摘要： Burnable gases under pressure for operating engines such as thrust engines and particular rocket and ramjet engines are produced by arranging together two solid propellant charges, one of which comprises an auxiliary propellant charge having a high thermal efficiency and the other constituting a main propellant charge comprising a material of low heat of fusion and evaporation. The auxiliary charge is ignited by a fuse device and will burn off adjacent the main charge but shielded therefrom by a burn-off insulation. The burnable gases which are produced are directed by their own pressure through a gas duct into a combustion chamber where they are admixed with an oxidizer which may be supplied under the pressure force of the gases themselves.