首页> 外国专利> Radial flow gas turbine engine with annular combustor liner

Radial flow gas turbine engine with annular combustor liner

机译:带有环形燃烧器衬套的径向流燃气涡轮发动机

摘要

A small gas turbine engine having a small, high speed shaft assembly including a central shaft member, a radial outflow compressor rotor secured to one end of the central shaft member with its inlet end disposed outboard of the shaft assembly, and a radial inflow turbine rotor secured to the other end of the central shaft member with its discharge end disposed outboard of the shaft assembly. The shaft assembly is supported at its ends, outboard of the rotors, by a pair of bearings which are axially secured but allow limited radial movement of the shaft assembly. An annular combustor is disposed between the turbine and compressor rotors in encircling relation to the central shaft member. Fuel is supplied to the combustor chamber from the exhaust end of the turbine through an axial passage in the shaft assembly opening at one end outboard of the exhaust end bearing and communicating at its other end with radial ports in the central shaft member arranged to sling fuel into the combustor chamber. The shaft assembly housing comprises two cast sections which are coupled together to enclose the combustor with the end portion of each housing section shaped to define a shroud for the radial blades of the turbine and compressor rotors, respectively. A cast nozzle plate and a diffuser plate are secured to the respective housing sections. The nozzle and diffuser plates each include an annular outer portion defining the vanes for the turbine and compressor rotors, respectively, and a central hollow hub portion embracing the central shaft member of the shaft assembly; the inboard ends of the two hub portions are axially spaced to expose the radial ports in the central shaft member and allow slinging delivery of fuel into the combustor. An annular air inlet to the compressor rotor spaces the shaft assembly housing from a transmission housing, and the compressor end of the shaft assembly is coupled, outboard of the compressor end bearing, to speed reduction gearing journalled within the transmission housing.
机译:一种小型燃气涡轮发动机,具有小型高速轴组件,该组件包括中心轴构件,固定在中心轴构件一端的径向流出压缩机转子,其入口端位于轴组件的外侧,以及径向流入涡轮机转子固定到中心轴构件的另一端,其排放端位于轴组件的外侧。轴组件在其端部在转子的外侧,由一对轴承轴向地固定,但允许轴组件的径向运动受限。环形燃烧器相对于中心轴构件环绕地设置在涡轮和压缩机转子之间。燃料从涡轮机的排气端通过位于排气端轴承外侧的一端的轴组件开口中的轴向通道供应到燃烧室,并在其另一端与中心轴构件中的径向端口连通,以径向排放燃料。进入燃烧室。轴组件壳体包括两个铸件,铸件被连接在一起以包围燃烧器,每个壳体的端部成形为分别限定用于涡轮机和压缩机转子的径向叶片的护罩。铸造的喷嘴板和扩散板固定到相应的壳体部分。喷嘴板和扩散板分别包括:环形的外部,其分别限定用于涡轮和压缩机转子的叶片;以及中心的中空毂部分,其包围轴组件的中心轴构件;两个毂部分的内侧端轴向间隔开以暴露中心轴构件中的径向端口,并允许将燃料吊装到燃烧器中。压缩机转子的环形进气口将轴组件外壳与变速箱外壳隔开,轴组件的压缩机端在压缩机端轴承的外侧连接至变速箱壳内的减速齿轮。

著录项

  • 公开/公告号US4000609A

    专利类型

  • 公开/公告日1977-01-04

    原文格式PDF

  • 申请/专利权人 EATON CORPORATION;

    申请/专利号US19740482808

  • 发明设计人 RICHARD CHUTE;

    申请日1974-06-24

  • 分类号F02C3/08;F02C7/06;F02C7/22;

  • 国家 US

  • 入库时间 2022-08-22 23:36:50

相似文献

  • 专利
  • 外文文献
  • 中文文献
获取专利

客服邮箱:kefu@zhangqiaokeyan.com

京公网安备:11010802029741号 ICP备案号:京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有
  • 客服微信

  • 服务号