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公开(公告)号：US08091334B2
公开(公告)日：2012-01-10
申请号：US13014168
申请日：2011-01-26
IPC分类号： F02K1/08
CPC分类号： F02K1/08 , Y02T50/671
摘要： An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.
摘要翻译： 提供了一种用于涡扇发动机组件的内芯前罩挡板组件。 发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心罩的径向外侧定位的机舱，以及限定在核心罩和机舱之间的风扇喷嘴管道。 内芯整流罩挡板组件包括内芯前罩挡板和致动器组件，该致动器组件构造成通过相对于内芯罩来选择性地重新定位内芯整流罩挡板来改变风扇喷嘴管道的喉部区域。
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公开(公告)号：US20080110153A1
公开(公告)日：2008-05-15
申请号：US11559761
申请日：2006-11-14
申请人： Jorge Francisco Seda , Thomas Ory Moniz , Robert Joseph Orlando , Alan Roy Stuart , Kenneth S. Scheffel
发明人： Jorge Francisco Seda , Thomas Ory Moniz , Robert Joseph Orlando , Alan Roy Stuart , Kenneth S. Scheffel
IPC分类号： F02K3/02
CPC分类号： F02K1/72
摘要： A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed. The method further includes selectively positioning the second cowl between the second operational position and a third operational position to vary an amount of air flowing through the fan nozzle duct and the thrust reverser assembly, wherein the second operational position substantially prevents airflow from flowing through the thrust reverser assembly to improve the efficiency of the turbofan engine, and wherein the third operational position directs airflow through the thrust reverser assembly.
摘要翻译： 提供了一种用于操作涡扇发动机组件的方法。 涡轮风扇发动机组件包括一个外围核心燃气涡轮发动机的核心罩，一个位于核心整流罩径向外侧的机舱，一个风扇喷嘴管道，其具有限定在核心整流罩和一部分机舱之间的区域，第一整流罩和 第二整流罩限定所述机舱的一部分，其中所述第二整流罩相对于所述第一整流罩可重新定位;以及推力反向器组件，其中所述第二整流罩围绕所述推力反向器组件。 该方法包括将风扇组件的操作速度从第一操作速度改变到第二操作速度。 该方法还包括将第二整流罩选择性地定位在第一操作位置和第二操作位置之间以改变风扇喷嘴管道的面积，以便于在第二操作速度下提高发动机效率。 该方法还包括将第二整流罩选择性地定位在第二操作位置和第三操作位置之间以改变流过风扇喷嘴管道和推力反向器组件的空气量，其中第二操作位置基本上防止气流流过推力 反向器组件以提高涡轮风扇发动机的效率，并且其中第三操作位置引导气流通过推力反向器组件。
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公开(公告)号：US20080112802A1
公开(公告)日：2008-05-15
申请号：US11559773
申请日：2006-11-14
IPC分类号： F01D1/02
摘要： A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.
摘要翻译： 提供涡轮风扇发动机总成。 涡轮风扇发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心整流罩径向向外定位的机舱，限定在核心整流罩和机舱之间的风扇喷嘴管道，以及内部核心整流罩 挡板组件位于风扇喷嘴管道内。 内芯整流罩挡板组件包括耦合到风扇喷嘴管道内的核心整流罩的一部分的第一磁芯整流罩挡板，耦合到磁芯整流罩的一部分并且与第一磁芯整流罩径向向内定位的第二磁芯整流罩挡板 挡板和致动器组件，其被配置成通过相对于第一芯导流板挡板选择性地重新定位第二芯面罩挡板来改变风扇喷嘴管道的喉部区域。 还提供了一种用于操作涡扇发动机组件的方法。
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公开(公告)号：US20110120136A1
公开(公告)日：2011-05-26
申请号：US13014168
申请日：2011-01-26
IPC分类号： F02C9/00
CPC分类号： F02K1/08 , Y02T50/671
摘要： An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.
摘要翻译： 提供了一种用于涡扇发动机组件的内芯前罩挡板组件。 发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心罩的径向外侧定位的机舱，以及限定在核心罩和机舱之间的风扇喷嘴管道。 内芯整流罩挡板组件包括内芯前罩挡板和致动器组件，该致动器组件构造成通过相对于内芯罩来选择性地重新定位内芯整流罩挡板来改变风扇喷嘴管道的喉部区域。
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公开(公告)号：US07886518B2
公开(公告)日：2011-02-15
申请号：US11559747
申请日：2006-11-14
IPC分类号： F02K1/08
CPC分类号： F02K1/08 , Y02T50/671
摘要： An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.
摘要翻译： 提供了一种用于涡扇发动机组件的内芯前罩挡板组件。 发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心罩的径向外侧定位的机舱，以及限定在核心罩和机舱之间的风扇喷嘴管道。 内芯整流罩挡板组件包括内芯前罩挡板和致动器组件，该致动器组件构造成通过相对于内芯罩来选择性地重新定位内芯整流罩挡板来改变风扇喷嘴管道的喉部区域。
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公开(公告)号：US07681399B2
公开(公告)日：2010-03-23
申请号：US11559773
申请日：2006-11-14
IPC分类号： F02K1/00
摘要： A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.
摘要翻译： 提供涡轮风扇发动机总成。 涡轮风扇发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心整流罩径向向外定位的机舱，限定在核心整流罩和机舱之间的风扇喷嘴管道，以及内部核心整流罩 挡板组件位于风扇喷嘴管道内。 内芯整流罩挡板组件包括耦合到风扇喷嘴管道内的核心整流罩的一部分的第一磁芯整流罩挡板，耦合到磁芯整流罩的一部分并且与第一磁芯整流罩径向向内定位的第二磁芯整流罩挡板 挡板和致动器组件，其被配置成通过相对于第一芯导流板挡板选择性地重新定位第二芯面罩挡板来改变风扇喷嘴管道的喉部区域。 还提供了一种用于操作涡扇发动机组件的方法。
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公开(公告)号：US07673442B2
公开(公告)日：2010-03-09
申请号：US11559761
申请日：2006-11-14
申请人： Jorge Francisco Seda , Thomas Ory Moniz , Robert Joseph Orlando , Alan Roy Stuart , Kenneth S. Scheffel
发明人： Jorge Francisco Seda , Thomas Ory Moniz , Robert Joseph Orlando , Alan Roy Stuart , Kenneth S. Scheffel
IPC分类号： F02K1/54
CPC分类号： F02K1/72
摘要： A method for operating a turbofan engine assembly is provided. The turbofan engine assembly includes a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct having an area defined between the core cowl and a portion of the nacelle, a first cowl and a second cowl that define a portion of the nacelle wherein the second cowl is repositionable with respect to the first cowl, and a thrust reverser assembly wherein the second cowl surrounds the thrust reverser assembly. The method includes varying an operating speed of the fan assembly from a first operating speed to a second operating speed. The method further includes selectively positioning the second cowl between a first operational position and a second operational position to vary the area of the fan nozzle duct to facilitate improving engine efficiency at the second operating speed. The method further includes selectively positioning the second cowl between the second operational position and a third operational position to vary an amount of air flowing through the fan nozzle duct and the thrust reverser assembly, wherein the second operational position substantially prevents airflow from flowing through the thrust reverser assembly to improve the efficiency of the turbofan engine, and wherein the third operational position directs airflow through the thrust reverser assembly.
摘要翻译： 提供了一种用于操作涡扇发动机组件的方法。 涡轮风扇发动机组件包括一个外围核心燃气涡轮发动机的核心罩，一个位于核心整流罩径向外侧的机舱，一个风扇喷嘴管道，其具有限定在核心整流罩和一部分机舱之间的区域，第一整流罩和 第二整流罩限定所述机舱的一部分，其中所述第二整流罩相对于所述第一整流罩可重新定位;以及推力反向器组件，其中所述第二整流罩围绕所述推力反向器组件。 该方法包括将风扇组件的操作速度从第一操作速度改变到第二操作速度。 该方法还包括将第二整流罩选择性地定位在第一操作位置和第二操作位置之间以改变风扇喷嘴管道的面积，以便于在第二操作速度下提高发动机效率。 该方法还包括将第二整流罩选择性地定位在第二操作位置和第三操作位置之间以改变流过风扇喷嘴管道和推力反向器组件的空气量，其中第二操作位置基本上防止气流流过推力 反向器组件以提高涡轮风扇发动机的效率，并且其中第三操作位置引导气流通过推力反向器组件。
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公开(公告)号：US20080112801A1
公开(公告)日：2008-05-15
申请号：US11559747
申请日：2006-11-14
IPC分类号： F01D1/02
CPC分类号： F02K1/08 , Y02T50/671
摘要： An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.
摘要翻译： 提供了一种用于涡扇发动机组件的内芯前罩挡板组件。 发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心罩的径向外侧定位的机舱，以及限定在核心罩和机舱之间的风扇喷嘴管道。 内芯整流罩挡板组件包括内芯前罩挡板和致动器组件，该致动器组件构造成通过相对于内芯罩来选择性地重新定位内芯整流罩挡板来改变风扇喷嘴管道的喉部区域。
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公开(公告)号：US07832193B2
公开(公告)日：2010-11-16
申请号：US11553571
申请日：2006-10-27
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F01D15/12 , F02K3/072 , Y02T50/671
摘要： A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine to the core gas turbine engine, coupling a booster compressor to a gearbox, and coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine.
摘要翻译： 一种组装燃气轮机组件的方法包括提供包括高压压缩机，燃烧器和涡轮机的核心燃气涡轮发动机，将低压涡轮机耦合到核心燃气涡轮发动机，将升压压缩机连接到变速箱， 并且将所述齿轮箱联接到所述低压涡轮机，使得所述增压压缩机由所述低压涡轮机驱动。
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公开(公告)号：US07603844B2
公开(公告)日：2009-10-20
申请号：US11253415
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F01D21/045 , F01D21/04 , F02K3/072 , F05B2260/3011 , F05D2260/4031 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox to the low-pressure turbine, coupling a first fan assembly to the gearbox such that the first fan assembly rotates in a first direction, and coupling a mechanical fuse between the first fan assembly and the low-pressure turbine such that the mechanical fuse fails at a predetermined moment load.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将低压涡轮联接到核心涡轮发动机，将齿轮箱联接到低压涡轮机，将第一风扇组件联接到齿轮箱，使得第一风扇组件沿第一方向旋转 并且在第一风扇组件和低压涡轮机之间联接机械保险丝，使得机械保险丝在预定的力矩负载下失效。
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