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61. 发明授权

US07673442B2 Turbofan engine cowl assembly 有权
标题翻译：涡轮发动机罩总成
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。

62. 发明授权

US07661260B2 Gas turbine engine assembly and method of assembling same 有权
标题翻译：燃气轮机组装及组装方法
公开(公告)号：US07661260B2
公开(公告)日：2010-02-16
申请号：US11535592
申请日：2006-09-27
申请人： Thomas Ory Moniz , Robert Joseph Orlando
发明人： Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F02K3/02
CPC分类号： F02C7/36 , F01D5/026 , F02K3/06 , F05D2260/403
摘要： A method for assembling a gas turbine engine assembly includes coupling a fan assembly to a core gas turbine engine such that the fan assembly is upstream from the core gas turbine engine, coupling a low-pressure turbine downstream from the core gas turbine engine such, wherein the low-pressure turbine includes a disk and a plurality of splines formed in the disk, providing a shaft that includes a first end and a second end that includes a plurality of splines, coupling the shaft first end to the fan assembly, and coupling the shaft second end to the low-pressure turbine such that the shaft splines mesh with the disk splines such that torque is transmitted from the low-pressure turbine to the fan assembly via the shaft during engine operation.
摘要翻译：一种用于组装燃气涡轮发动机组件的方法包括将风扇组件连接到核心燃气涡轮发动机，使得风扇组件在核心燃气涡轮发动机的上游，将核心燃气涡轮发动机下游的低压涡轮机联接到其中，其中所述低压涡轮机包括盘和形成在所述盘中的多个花键，提供轴，所述轴包括第一端和包括多个花键的第二端，所述花键将所述轴的第一端连接到所述风扇组件，轴第二端连接到低压涡轮机，使得轴花键与盘形花键啮合，使得在发动机操作期间，扭矩通过轴从低压涡轮机传递到风扇组件。

63. 发明授权

US07513102B2 Integrated counterrotating turbofan 有权
标题翻译：集成逆转涡扇风扇
公开(公告)号：US07513102B2
公开(公告)日：2009-04-07
申请号：US11145875
申请日：2005-06-06
申请人： Thomas Ory Moniz , Scott Michael Carson , Robert Joseph Orlando , Ching-Pang Lee , David Glenn Cherry
发明人： Thomas Ory Moniz , Scott Michael Carson , Robert Joseph Orlando , Ching-Pang Lee , David Glenn Cherry
IPC分类号： F02K3/00 , F02K3/02 , F02C1/06
CPC分类号： F01D5/14 , F01D5/141 , F02C3/067 , F02K3/072 , Y02T50/671 , Y02T50/673
摘要： A turbofan engine includes a fan, compressor, combustor, single-stage high pressure turbine, and low pressure turbine joined in serial flow communication. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation. First stage stator vanes in the low pressure turbine have camber and twist for carrying swirl directly between the rotor blades of the high and low pressure turbines.
摘要翻译：涡轮风扇发动机包括串联流动连接的风扇，压缩机，燃烧器，单级高压涡轮机和低压涡轮机。低压涡轮机中的第一级转子叶片与用于逆旋转的高压涡轮机中的转子叶片相反地定向。低压涡轮机中的第一级定子叶片具有用于在高压和低压涡轮机的转子叶片之间直接携带涡流的弯曲和扭转。

64. 发明申请

US20090064683A1 POWER TAKE-OFF SYSTEM AND GAS TURBINE ENGINE ASSEMBLY INCLUDING SAME 有权
标题翻译：动力系统和气体发动机组件包括相同的
公开(公告)号：US20090064683A1
公开(公告)日：2009-03-12
申请号：US11695741
申请日：2007-04-03
申请人： Thomas Ory Moniz , Jan Christopher Schilling , Robert Joseph Orlando , Raymond Felix Patt
发明人： Thomas Ory Moniz , Jan Christopher Schilling , Robert Joseph Orlando , Raymond Felix Patt
IPC分类号： F02C7/32 , B23P11/00 , F16H37/00 , F02C3/10
CPC分类号： F02C7/275 , F02C7/32 , F02C7/36 , Y02T50/671 , Y10T29/49245
摘要： A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described.
摘要翻译：用于燃气涡轮发动机的动力输出系统包括联接到第二阀芯的起动器和联接在起动器和第一阀芯之间的离合器组件，所述离合器组件构造成当启动燃气轮机时将第一阀芯耦合到起动器发动机总成。还描述了组装包括动力输出系统的燃气涡轮发动机组件的方法和包括动力输出系统的燃气涡轮发动机组件。

65. 发明授权

US07490460B2 Gas turbine engine assembly and methods of assembling same 失效
标题翻译：燃气轮机组装及组装方法
公开(公告)号：US07490460B2
公开(公告)日：2009-02-17
申请号：US11253935
申请日：2005-10-19
申请人： Thomas Ory Moniz , Robert Joseph Orlando
发明人： Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F02K3/00
CPC分类号： F02C7/06 , F02C3/067 , F02K3/072 , F05D2240/52 , F05D2260/40311 , F16H1/2827 , F16H57/082 , Y02T50/671
摘要： A gearbox includes a support structure, at least one sun gear coupled within the support structure, and a plurality of planetary gears coupled within the support structure. The support structure includes a first portion, an axially aft second portion, and a thrust spring coupled between the first and second portions.
摘要翻译：齿轮箱包括支撑结构，联接在支撑结构内的至少一个太阳轮，以及联接在支撑结构内的多个行星齿轮。支撑结构包括第一部分，轴向后部第二部分和联接在第一和第二部分之间的止推弹簧。

66. 发明申请

US20080112801A1 TURBOFAN ENGINE COWL ASSEMBLY AND METHOD OF OPERATING THE SAME 有权
标题翻译：涡轮发动机总成及其运行方法
公开(公告)号：US20080112801A1
公开(公告)日：2008-05-15
申请号：US11559747
申请日：2006-11-14
申请人： Thomas Ory Moniz , Jorge Francisco Seda , Robert Joseph Orlando
发明人： Thomas Ory Moniz , Jorge Francisco Seda , Robert Joseph Orlando
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。

67. 发明申请

US20080112794A1 Compound nozzle cooled engine 有权
标题翻译：复合喷嘴冷却发动机
公开(公告)号：US20080112794A1
公开(公告)日：2008-05-15
申请号：US11595669
申请日：2006-11-10
申请人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
发明人： Ching-Pang Lee , Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F01D1/00
CPC分类号： F02C7/12 , F01D5/189 , F05D2220/3212 , F05D2260/201 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.
摘要翻译：燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。涡轮机包括喷嘴，随后是一排转子叶片。第一泄放回路在压缩机的最后阶段和喷嘴的叶片中的前冷却通道之间流动连通地连接，用于在第一压力下用加压的一次空气向其中供给第一冷却孔。第二泄放回路在压缩机的中间级与喷嘴叶片中的后冷却通道之间流动连通地连接，以在小于第一压力的第二压力下用加压的二次空气供给第二冷却孔。

68. 发明申请

US20080098718A1 TURBOFAN ENGINE ASSEMBLY AND METHOD OF ASSEMBLING SAME 有权
标题翻译：涡轮发动机组件及其组装方法
公开(公告)号：US20080098718A1
公开(公告)日：2008-05-01
申请号：US11555097
申请日：2006-10-31
申请人： John Leslie Henry , Robert Joseph Orlando , Thomas Ory Moniz
发明人： John Leslie Henry , Robert Joseph Orlando , Thomas Ory Moniz
IPC分类号： F02K3/02
CPC分类号： F02C3/067 , F02C7/36 , F05D2260/40311
摘要： A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, and a gearbox comprising an input and an output, said gearbox output coupled to at least one of said first and second rotor sections, said gearbox input coupled to said low-pressure turbine. A method of assembling the turbofan engine assembly described herein is also provided.
摘要翻译：涡轮风扇发动机组件包括：包括高压压缩机，燃烧器和高压涡轮机的核心燃气涡轮发动机，与所述核心燃气涡轮发动机相连的低压涡轮;反向旋转增压压缩机，包括第一转子其构造成沿第一方向旋转，第二转子部分构造成沿相反的第二方向旋转;以及齿轮箱，包括输入和输出，所述齿轮箱输出联接到所述第一和第二转子部分中的至少一个，所述变速箱输入端连接到所述低压涡轮。还提供了一种组装本文所述涡轮风扇发动机组件的方法。

69. 发明申请

US20080098717A1 TURBOFAN ENGINE ASSEMBLY AND METHOD OF ASSEMBLING SAME 有权
标题翻译：涡轮发动机组件及其组装方法
公开(公告)号：US20080098717A1
公开(公告)日：2008-05-01
申请号：US11555045
申请日：2006-10-31
申请人： Robert Joseph Orlando , Thomas Ory Moniz
发明人： Robert Joseph Orlando , Thomas Ory Moniz
IPC分类号： F02K3/02
CPC分类号： F01D1/24 , F01D1/26 , F02C3/067 , F02K3/072 , F05D2260/40311
摘要： A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and a low-pressure turbine disposed downstream from the intermediate-pressure turbine, the low-pressure turbine configured to drive the counter-rotating fan assembly. A method of assembling the above turbofan engine assembly is also described herein.
摘要翻译：涡轮风扇发动机组件包括：核心燃气涡轮发动机，其包括高压压缩机，燃烧器和高压涡轮，耦合在核心燃气涡轮发动机上游的增压压缩机，耦合到增压压缩机的中压涡轮机，所述中压涡轮机设置在所述核心燃气涡轮发动机的下游，配置在所述增压压缩机的上游的反向旋转风扇组件，所述反向旋转风扇组件包括构造成沿第一方向旋转的第一风扇和配置为在相对的第二方向上旋转，以及低压涡轮机，其设置在中压涡轮机的下游，该低压涡轮机构造成驱动反向旋转的风扇组件。本文还描述了组装上述涡轮风扇发动机组件的方法。

70. 发明授权

US07195447B2 Gas turbine engine and method of assembling same 有权
标题翻译：燃气轮机及其组装方法
公开(公告)号：US07195447B2
公开(公告)日：2007-03-27
申请号：US10976495
申请日：2004-10-29
申请人： Thomas Ory Moniz , Robert Joseph Orlando
发明人： Thomas Ory Moniz , Robert Joseph Orlando
IPC分类号： F01D1/24
CPC分类号： F02C3/067 , F01D25/162 , F05D2230/64
摘要： A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, providing a low-pressure turbine outer rotor that includes a second plurality of turbine blade rows configured to rotate in a second direction that is opposite the first direction, coupling a turbine mid-frame assembly including a plurality of spokes within the engine such that the spokes are spaced axially forward of the inner rotor, coupling a bearing between the turbine mid-frame assembly and the inner rotor such that the inner rotor is rotatably coupled to the turbine mid-frame, and adjusting the plurality of spokes to align the bearing in a radial direction.
摘要翻译：一种用于组装燃气涡轮发动机的方法，包括提供低压涡轮机内转子，所述低转速涡轮内转子包括构造成沿第一方向旋转的第一多个涡轮机叶片排，提供包括第二多个涡轮机的低压涡轮机外转子叶片排构造成沿与第一方向相反的第二方向旋转，将包括发动机内的多个辐条的涡轮机中框架组件联接成使得辐条在内转子的轴向前方间隔开，将轴承在涡轮中部框架组件和内部转子，使得内部转子可旋转地联接到涡轮机中间框架，并且调节多个辐条以使轴承沿径向对准。

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