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1. 发明授权

US07832193B2 Gas turbine engine assembly and methods 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：US07832193B2
公开(公告)日：2010-11-16
申请号：US11553571
申请日：2006-10-27
申请人： Robert Joseph Orlando , Thomas Ory Moniz , Jan Christopher Schilling
发明人： Robert Joseph Orlando , Thomas Ory Moniz , Jan Christopher Schilling
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。

2. 发明授权

US07603844B2 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：US07603844B2
公开(公告)日：2009-10-20
申请号：US11253415
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： 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。

3. 发明授权

US07493753B2 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：US07493753B2
公开(公告)日：2009-02-24
申请号：US11253932
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： F01D25/18 , F01D25/16 , F02C7/06 , F02K3/072 , Y02T50/671
摘要： A method facilitates assembling a gas turbine engine. The method comprises coupling a low-pressure turbine rotatable about a drive shaft to a counter-rotating fan assembly including a first fan assembly and a second fan assembly wherein the first fan assembly rotates in a first direction and the second fan assembly rotates in an opposite second direction. The method also comprises coupling a planetary gearbox substantially circumferentially about the drive shaft such that an input of the gearbox is coupled to the low-pressure turbine and an output of the gearbox is coupled to the counter-rotating fan assembly, and such that the gearbox is positioned within a lubrication fluid sump that substantially circumscribes the gearbox.
摘要翻译：一种便于组装燃气涡轮发动机的方法。该方法包括将围绕驱动轴旋转的低压涡轮机联接到包括第一风扇组件和第二风扇组件的反向旋转风扇组件，其中第一风扇组件沿第一方向旋转，而第二风扇组件以相反的方向旋转第二个方向该方法还包括将行星齿轮箱基本上周向地联接在驱动轴上，使得齿轮箱的输入端连接到低压涡轮机，并且齿轮箱的输出端连接到反向旋转的风扇组件，并且使得齿轮箱位于基本上限制齿轮箱的润滑液槽内。

4. 发明申请

US20080110153A1 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：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。

5. 发明申请

US20080072567A1 GAS TURBINE ENGINE ASSEMBLY AND METHOD OF ASSEMBLING SAME 有权
标题翻译：气体涡轮发动机组件及其组装方法
公开(公告)号：US20080072567A1
公开(公告)日：2008-03-27
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耦合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。

6. 发明授权

US07334392B2 Counter-rotating gas turbine engine and method of assembling same 有权
标题翻译：反转式燃气轮机及其组装方法
公开(公告)号：US07334392B2
公开(公告)日：2008-02-26
申请号：US10977075
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： F02C3/067 , F02K3/04
CPC分类号： F02K3/072 , F01D1/24 , F02C3/067 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft of the first fan assembly, wherein the second fan assembly includes a plurality of rotor blades that are configured to rotate in a second rotational direction, and coupling a gearbox to the second fan assembly that is configured to rotate the second fan assembly at a second rotational speed that is different than the first rotational speed.
摘要翻译：一种用于组装燃气涡轮发动机的方法包括：提供第一风扇组件，其包括多个转子叶片，所述多个转子叶片构造成以第一转速沿第一旋转方向旋转，可旋转地联接第一风扇组件，其中所述第二风扇组件包括多个转子叶片，所述多个转子叶片被构造成沿第二旋转方向旋转，并且将齿轮箱联接到所述第二风扇组件，所述第二风扇组件被构造成以不同于所述第二风扇组件的第二转速旋转所述第二风扇组件第一转速。

7. 发明授权

US07269938B2 Counter-rotating gas turbine engine and method of assembling same 有权
标题翻译：反转式燃气轮机及其组装方法
公开(公告)号：US07269938B2
公开(公告)日：2007-09-18
申请号：US10976494
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： F02C3/067
CPC分类号： F02K3/072 , F01D25/16 , F02C3/067 , F16C17/024 , F16C19/50 , F16C2360/23
摘要： A method for assembling a gas turbine engine includes providing a high pressure turbine, 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, and coupling a plurality of bearings between the outer rotor and a turbine mid-frame between the high pressure turbine and at least one of the inner and outer rotors such that the plurality of bearings support a forward end of the outer rotor.
摘要翻译：一种用于组装燃气涡轮发动机的方法包括提供高压涡轮机，提供包括构造成在第一方向上旋转的第一多个涡轮叶片排的低压涡轮机内转子，提供低压涡轮机外转子，其包括第二组多个涡轮机叶片排，其构造成沿与第一方向相反的第二方向旋转;以及将外转子和涡轮机中间框架之间的多个轴承联接在高压涡轮机与至少一个内部和外转子使得多个轴承支撑外转子的前端。

8. 发明授权

US07096674B2 High thrust gas turbine engine with improved core system 有权
标题翻译：具有改进的核心系统的高推力燃气轮机
公开(公告)号：US07096674B2
公开(公告)日：2006-08-29
申请号：US10941546
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
IPC分类号： F02C6/08
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
摘要翻译：一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。

9. 发明授权

US06763654B2 Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans 有权
标题翻译：飞机燃气涡轮发动机具有可变转矩分流反转旋转低压涡轮机和增压器逆向旋转风扇
公开(公告)号：US06763654B2
公开(公告)日：2004-07-20
申请号：US10260480
申请日：2002-09-30
申请人： Robert Joseph Orlando , Thomas Ory Moniz , John Lewis Baughman
发明人： Robert Joseph Orlando , Thomas Ory Moniz , John Lewis Baughman
IPC分类号： F02K3072
CPC分类号： F01D1/24 , F02C3/067 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaft turbines with a row of low pressure variable vanes disposed therebetween and drivingly connected to coaxial low pressure inner and outer shafts respectively which are located radially inwardly of the high pressure spool. The low pressure inner and outer shaft turbines are drivingly connected to a forward and aft fan blade rows by the low pressure inner and outer shafts. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.
摘要翻译：一种燃气涡轮发动机涡轮组件包括具有高压涡轮机的高压阀芯，所述高压涡轮机通过可围绕发动机中心线旋转的高压轴驱动地连接到高压压缩机。低压涡轮机具有反转的低压内外涡轮机，其一排低压可变叶片设置在它们之间并分别驱动地连接到位于高压线轴的径向内侧的同轴低压内外轴和外轴。低压内外涡轮机通过低压内外轴驱动连接到前风扇叶片和后风扇叶片排。单向旋转助力器驱动地连接到低压外轴并且轴向位于后风扇叶片排的后部和下游。

10. 发明授权

US06763653B2 Counter rotating fan aircraft gas turbine engine with aft booster 有权
标题翻译：逆向旋转风机飞机燃气涡轮发动机带后升压器
公开(公告)号：US06763653B2
公开(公告)日：2004-07-20
申请号：US10253156
申请日：2002-09-24
申请人： Robert Joseph Orlando , Thomas Ory Moniz
发明人： Robert Joseph Orlando , Thomas Ory Moniz
IPC分类号： F02K302
CPC分类号： F02C3/067 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaft turbines drivingly connected to coaxial low pressure inner and outer shafts respectively which are at least in part rotatably disposed co-axial with and radially inwardly of the high pressure spool. The low pressure inner shaft turbine is drivingly connected to a forward fan blade row by the low pressure inner shaft. The low pressure outer shaft turbine is drivingly connected to a aft fan blade row by the low pressure outer shaft. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.
摘要翻译：一种燃气涡轮发动机涡轮组件包括具有高压涡轮机的高压阀芯，所述高压涡轮机通过可围绕发动机中心线旋转的高压轴驱动地连接到高压压缩机。低压涡轮机具有反转可旋转的低压内外涡轮机，其分别驱动地连接到同轴的低压内外轴和外轴，其至少部分地可旋转地设置成与高压阀芯同轴并且径向向内。低压内轴涡轮机通过低压内轴与前风扇叶片排驱动连接。低压外轴涡轮机通过低压外轴与后风扇叶片排驱动连接。单向旋转助力器驱动地连接到低压外轴并且轴向位于后风扇叶片排的后部和下游。

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