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41. 发明授权

US07926259B2 Turbofan engine assembly and method of assembling same 有权
标题翻译： Turbofan发动机总成及组装方法
公开(公告)号：US07926259B2
公开(公告)日：2011-04-19
申请号：US11554993
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 , F02K3/072
CPC分类号： F02K3/072 , F02C7/36 , F16H57/0479 , F16H57/0486
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 first fan assembly coupled to a low-pressure turbine, a second fan assembly disposed downstream from the first fan assembly, and a gearbox coupled between the second fan assembly and the low-pressure turbine. 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，设置在核心燃气涡轮发动机下游的中压涡轮机，耦合到低压涡轮机的第一风扇组件，设置在第一风扇组件下游的第二风扇组件，以及联接在第二风扇组件和低压涡轮机之间的齿轮箱压力涡轮机。本文还描述了组装上述涡轮风扇发动机组件的方法。

42. 发明授权

US07921634B2 Turbofan engine assembly and method of assembling same 有权
标题翻译： Turbofan发动机总成及组装方法
公开(公告)号：US07921634B2
公开(公告)日：2011-04-12
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 , F02K3/072
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。

43. 发明授权

US07905083B2 Turbofan engine assembly and method of assembling same 有权
标题翻译： Turbofan发动机总成及组装方法
公开(公告)号：US07905083B2
公开(公告)日：2011-03-15
申请号：US11554997
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 , F02K3/072
CPC分类号： F02C7/36 , F02K3/072
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 an intermediate-pressure turbine disposed downstream from the core gas turbine engine, wherein the intermediate-pressure turbine drives the booster compressor and the second 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，以及设置在所述核心燃气涡轮发动机下游的中压涡轮机，其中所述中压涡轮机驱动所述增压压缩机和所述第二风扇组件。本文还描述了组装上述涡轮风扇发动机组件的方法。

44. 发明授权

US07870743B2 Compound nozzle cooled engine 有权
标题翻译：复合喷嘴冷却发动机
公开(公告)号：US07870743B2
公开(公告)日：2011-01-18
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： F02C6/08
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。

45. 发明授权

US07743613B2 Compound turbine cooled engine 有权
标题翻译：复合涡轮冷却发动机
公开(公告)号：US07743613B2
公开(公告)日：2010-06-29
申请号：US11595668
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： F02C6/08
CPC分类号： F01D9/065 , F01D25/12 , F02C7/12 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.
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。涡轮机包括一排喷嘴叶片，随后是一排转子叶片。叶片和叶片具有相应的前后冷却通道。第一，第二，第三和第四泄放回路与压缩机的不同级联流动连通，以在不同压力下从其中排出加压空气，以向涡轮机叶片和叶片的前后通道提供冷却剂。

46. 发明授权

US07594388B2 Counterrotating turbofan engine 有权
标题翻译：反转涡轮风扇发动机
公开(公告)号：US07594388B2
公开(公告)日：2009-09-29
申请号：US11145848
申请日：2005-06-06
申请人： David Glenn Cherry , Robert John Beacock , William Larson Clifford , Robert Joseph Orlando , Thomas Ory Moniz , Ching-Pang Lee
发明人： David Glenn Cherry , Robert John Beacock , William Larson Clifford , Robert Joseph Orlando , Thomas Ory Moniz , Ching-Pang Lee
IPC分类号： F02C3/067 , F02K3/072
CPC分类号： F02C3/067 , F01D5/142 , F01D9/02 , F01D9/041 , F01D9/065 , F02K3/072 , F05D2240/127 , Y02T50/671 , Y02T50/673
摘要： A turbofan engine includes a fan, compressor, combustor, high pressure turbine, and low pressure turbine joined in serial flow communication. The high pressure turbine includes two stages of rotor blades to effect corresponding exit swirl in the combustion gases discharged therefrom. A transition duct includes fairings extending between platforms for channeling the combustion gases to the low pressure turbine with corresponding swirl. First stage rotor blades in the low pressure turbine are oriented oppositely to the rotor blades in the high pressure turbine for counterrotation.
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，高压汽轮机和低压汽轮机。高压涡轮机包括两级转子叶片，以在从其排出的燃烧气体中实现相应的出口涡流。过渡管道包括在平台之间延伸的整流罩，用于将燃烧气体引导到具有相应涡流的低压涡轮机。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。

47. 发明申请

US20080148881A1 POWER TAKE-OFF SYSTEM AND GAS TURBINE ENGINE ASSEMBLY INCLUDING SAME 审中-公开
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：US20080148881A1
公开(公告)日：2008-06-26
申请号：US11614623
申请日：2006-12-21
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： F16H37/00
CPC分类号： F02C7/32 , F05D2220/50 , F05D2220/76 , F05D2260/4031 , Y02T50/671 , Y10T29/4932
摘要： A power take-off system for a gas turbine engine includes a starter coupled to a first spool using a first shaft, and a generator coupled to the second spool using a second shaft, the first shaft is circumferentially offset by the second shaft by an angle α. 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使用第一轴联接到第一阀芯的起动器和使用第二轴联接到第二阀芯的发电机，第一轴由第二轴沿周向偏移一定角度 α。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。

48. 发明申请

US20080112802A1 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：US20080112802A1
公开(公告)日：2008-05-15
申请号：US11559773
申请日：2006-11-14
申请人： Robert Joseph Orlando , Thomas Ory Moniz , Jorge Francisco Seda
发明人： Robert Joseph Orlando , Thomas Ory Moniz , Jorge Francisco Seda
IPC分类号： F01D1/02
CPC分类号： F02K1/08 , F02K1/386 , F02K3/06 , F02K3/075
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。

49. 发明申请

US20080112793A1 Interstage cooled turbine engine 有权
标题翻译：级间冷却涡轮发动机
公开(公告)号：US20080112793A1
公开(公告)日：2008-05-15
申请号：US11595606
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： F01D5/18
CPC分类号： F01D5/088 , F01D5/082 , F05D2260/20 , Y02T50/672 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.
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（HP）涡轮机。级间冷却回路从压缩机的中间阶段流动连接到支撑一排涡轮机叶片的HP盘的前面，用于将级间排放冷却空气引导到其中。

50. 发明申请

US20080112791A1 Compound turbine cooled engine 有权
标题翻译：复合涡轮冷却发动机
公开(公告)号：US20080112791A1
公开(公告)日：2008-05-15
申请号：US11595668
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： F02C9/18
CPC分类号： F01D9/065 , F01D25/12 , F02C7/12 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a row of nozzle vanes followed by a row of rotor blades. The vanes and blades have corresponding forward and aft internal cooling channels. First, second, third, and fourth bleed circuits are joined in flow communication with different stages of the compressor for bleeding pressurized air therefrom at different pressures to provide coolant to the forward and aft channels of the turbine vanes and blades.
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。涡轮机包括一排喷嘴叶片，随后是一排转子叶片。叶片和叶片具有相应的前后冷却通道。第一，第二，第三和第四泄放回路与压缩机的不同级联流动连通，以在不同压力下从其中排出加压空气，以向涡轮机叶片和叶片的前后通道提供冷却剂。

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