公开(公告)号：US20100034663A1

公开(公告)日：2010-02-11

申请号：US12187791

申请日：2008-08-07

申请人： Tom Elliott ,  Greg Heitland ,  Jeff Howe ,  Mark C. Morris

发明人： Tom Elliott ,  Greg Heitland ,  Jeff Howe ,  Mark C. Morris

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

摘要： A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

摘要翻译： 燃气涡轮发动机组件具有流过气体流路的燃烧气体。 燃气涡轮发动机组件包括定子组件，该定子组件包括延伸到气体流路中的定子叶片; 以及在定子组件下游的涡轮机转子组件，并且包括涡轮机平台和从涡轮机平台延伸到主流燃烧气体流动路径中的涡轮机转子叶片。 涡轮转子叶片包括压力侧和与从前缘延伸到后缘的压力侧相对的吸力侧。 燃烧气体在与涡轮机转子叶片的前缘相邻的形成区域形成马蹄形旋涡，并且涡轮机转子组件还包括涡轮机平台中的第一组孔，用于将第一射流引导到马蹄形旋涡的形成区域中。

公开(公告)号：US08167557B2

公开(公告)日：2012-05-01

申请号：US12187791

申请日：2008-08-07

申请人： Tom Elliott ,  Greg Heitland ,  Jeff Howe ,  Mark C. Morris

发明人： Tom Elliott ,  Greg Heitland ,  Jeff Howe ,  Mark C. Morris

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F05D2240/127 ,  F05D2240/81 ,  F05D2260/2212 ,  Y02T50/673 ,  Y02T50/676

摘要： A gas turbine engine assembly has combustion gases flowing through a gas flow path. The gas turbine engine assembly includes a stator assembly comprising a stator vane that extends into the gas flow path; and a turbine rotor assembly downstream of the stator assembly and comprising a turbine platform and a turbine rotor blade extending from the turbine platform into the mainstream combustion gases flow path. The turbine rotor blade includes a pressure side and a suction side opposing the pressure side that extend from a leading edge to a trailing edge. The combustion gases form horseshoe vortices at a formation area adjacent the leading edge of the turbine rotor blade, and the turbine rotor assembly further includes a first set of holes in the turbine platform for directing first jets into the formation area of the horseshoe vortices.

摘要翻译： 燃气涡轮发动机组件具有流过气体流路的燃烧气体。 燃气涡轮发动机组件包括定子组件，该定子组件包括延伸到气体流路中的定子叶片; 以及在定子组件下游的涡轮机转子组件，并且包括涡轮机平台和从涡轮机平台延伸到主流燃烧气体流动路径中的涡轮机转子叶片。 涡轮转子叶片包括压力侧和与从前缘延伸到后缘的压力侧相对的吸力侧。 燃烧气体在与涡轮机转子叶片的前缘相邻的形成区域形成马蹄形旋涡，并且涡轮机转子组件还包括涡轮机平台中的第一组孔，用于将第一射流引导到马蹄形旋涡的形成区域中。

公开(公告)号：US08262342B2

公开(公告)日：2012-09-11

申请号：US12171000

申请日：2008-07-10

申请人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

发明人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

IPC分类号： F01D5/14

CPC分类号： F01D11/001 ,  F01D5/143 ,  F01D5/145 ,  F01D11/02 ,  F01D11/04 ,  Y02T50/673

摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。 组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片 路径。 定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。

公开(公告)号：US20100008760A1

公开(公告)日：2010-01-14

申请号：US12171000

申请日：2008-07-10

申请人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

发明人： Mark C. Morris ,  Jeff Howe ,  Greg Heitland ,  Jason Smoke

IPC分类号： F01D1/02

CPC分类号： F01D11/001 ,  F01D5/143 ,  F01D5/145 ,  F01D11/02 ,  F01D11/04 ,  Y02T50/673

摘要： A gas turbine engine assembly includes a housing including an annular duct wall that at least partially defines a mainstream hot gas flow path configured to receive mainstream hot gas flow. The assembly further includes a stator assembly including a stator vane that extends into the mainstream hot gas flow path and a turbine rotor assembly downstream of the stator assembly that includes a turbine disk and a turbine blade extending from the turbine disk into the mainstream hot gas flow path. The stator assembly and turbine assembly define a turbine disk cavity, and the turbine disk cavity includes a recirculation cavity configured to recirculate gas ingested from the mainstream hot gas flow path back into the mainstream hot gas flow path.

摘要翻译： 燃气涡轮发动机组件包括壳体，该壳体包括至少部分地限定主流热气流动路径的环形管道壁，所述主流热气体流动路径被配置为接收主流热气流。 组件还包括定子组件，该定子组件包括延伸到主流热气流路径中的定子叶片和在定子组件下游的涡轮转子组件，该涡轮转子组件包括涡轮盘和从涡轮盘延伸到主流热气流中的涡轮叶片 路径。 定子组件和涡轮机组件限定涡轮机盘腔，并且涡轮机盘腔包括再循环空腔，其被配置成将从主流热气流路径吸入的气体再循环回主流热气流路径。