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1. 发明申请

US20120079804A1 COWL ASSEMBLY 审中-公开
标题翻译： COWL装配
公开(公告)号：US20120079804A1
公开(公告)日：2012-04-05
申请号：US13247466
申请日：2011-09-28
申请人： Alan Roy Stuart , Kenneth Stephan Scheffel
发明人： Alan Roy Stuart , Kenneth Stephan Scheffel
IPC分类号： F02K3/02
CPC分类号： F02K1/72 , F02K1/76 , F02K3/06
摘要： An assembly for a turbofan engine includes a first cowl member comprising an aft portion and a translatable cowl member comprising a forward portion configured to be received within the aft portion. The translatable cowl member is configured to be moveable with respect to the first cowl member between a first operational position wherein the forward portion is received within the aft portion of the first cowl member, and a second operational position wherein a smaller portion of the forward portion is received within the aft portion than in the first operational position. The translatable cowl member is configured to cooperate with a core cowl of the turbofan engine to define a portion of a fan duct having an exit nozzle, and the translatable cowl member is configured to define a flow control location near the exit nozzle that is associated with a controlling fan duct area.
摘要翻译：用于涡轮风扇发动机的组件包括第一整流罩构件，其包括后部部分和可平移的整流罩构件，其包括构造成容纳在后部中的前部。可平移整流罩构件被构造成可在第一操作位置和第二操作位置之间相对于第一整流罩构件在第一操作位置和第二操作位置之间移动，其中前部部分被容纳在第一整流罩构件的后部中，在后部中被接收在第一操作位置。所述可平移整流罩构件被构造成与所述涡轮风扇发动机的核心罩一起配合以限定具有出口喷嘴的风扇管道的一部分，并且所述可平移整流罩构件构造成限定出口喷嘴附近的流动控制位置，所述流动控制位置与控制风扇管道面积。

2. 发明申请

US20100192595A1 GAS TURBINE ENGINE ASSEMBLY AND METHODS OF ASSEMBLING SAME 审中-公开
标题翻译：气体涡轮发动机组件及其组装方法
公开(公告)号：US20100192595A1
公开(公告)日：2010-08-05
申请号：US12363427
申请日：2009-01-30
申请人： Robert Joseph Orlando , Thomas Ory Moniz , Alan Roy Stuart
发明人： Robert Joseph Orlando , Thomas Ory Moniz , Alan Roy Stuart
IPC分类号： F02C3/10
CPC分类号： F02K3/072 , F02C7/36 , F05D2220/323 , F05D2220/327 , Y10T29/49229
摘要： A turbine engine assembly includes, a core gas turbine engine, a first low-pressure turbine section in serial flow communication with the core gas turbine engine, the first low-pressure turbine section configured to rotate in a first rotational direction, a first gear assembly coupled to the first low-pressure turbine section, a second low-pressure turbine section coupled to the gear assembly, the second low-pressure turbine section configured to rotate in a second rotational direction, and a fan assembly coupled to the second low-pressure turbine section.
摘要翻译：涡轮发动机组件包括核心燃气涡轮发动机，与核心燃气涡轮发动机串联流动连通的第一低压涡轮机部分，第一低压涡轮机部分构造成沿第一旋转方向旋转，第一齿轮组件耦合到第一低压涡轮部分，联接到齿轮组件的第二低压涡轮机部分，第二低压涡轮机部分构造成沿第二旋转方向旋转;以及风扇组件，其联接到第二低压涡轮机部分涡轮段。

3. 发明申请

US20100155525A1 MONOLITHIC STRUCTURE FOR MOUNTING AIRCRAFT ENGINE 有权
标题翻译：用于安装飞机发动机的单片结构
公开(公告)号：US20100155525A1
公开(公告)日：2010-06-24
申请号：US12343833
申请日：2008-12-24
申请人： Alan Roy Stuart , Mark Linz
发明人： Alan Roy Stuart , Mark Linz
IPC分类号： B64D27/00 , F02K3/02 , F01D25/28
CPC分类号： B64D27/18 , B64D27/26 , B64D29/00 , Y02T50/44
摘要： Assembly includes an integral monolithic structure for mounting an engine to an aircraft. The monolithic structure includes a nacelle portion and a support structure. The nacelle portion includes an inlet region and a fan case region defining an annular wall about an axial channel. A ring member disposed in the axial channel is connected through a plurality of radial elements to the annular wall. The support structure portion includes a forward section integral with the nacelle portion and an aft section including at least one aircraft mount region for mounting the monolithic structure to an aircraft. The forward section includes an inlet stiffening region radially outward of the annular wall. When mounted on the aircraft, the nacelle portion and the support structure portion cooperate to form a first load path operable to transmit an applied nacelle maneuvering force directly to the aircraft instead of through the engine core.
摘要翻译：组件包括用于将发动机安装到飞机上的整体单体结构。整体结构包括机舱部分和支撑结构。机舱部分包括入口区域和限定围绕轴向通道的环形壁的风扇壳体区域。设置在轴向通道中的环构件通过多个径向元件连接到环形壁。所述支撑结构部分包括与所述机舱部分成一体的前部部分和包括用于将所述整体结构安装到飞行器的至少一个飞行器安装区域的后部部分。前部包括在环形壁的径向外侧的入口加强区域。当安装在飞机上时，机舱部分和支撑结构部分协作以形成第一负载路径，其可操作以将施加的机舱机动动力直接传递到飞行器而不是通过发动机机芯。

4. 发明申请

US20120305700A1 SYSTEM AND METHOD FOR MOUNTING AN AIRCRAFT ENGINE 有权
标题翻译：用于安装飞机发动机的系统和方法
公开(公告)号：US20120305700A1
公开(公告)日：2012-12-06
申请号：US13487666
申请日：2012-06-04
申请人： Alan Roy Stuart , John Robert Fehrmann
发明人： Alan Roy Stuart , John Robert Fehrmann
IPC分类号： B64D27/12
CPC分类号： B64D27/18 , B64D27/12 , B64D27/26 , B64D2027/268 , F01D25/285 , F02C7/20 , F02K3/06 , Y02T50/671
摘要： A mounting system and method capable of reducing backbone deflection in a high-bypass turbofan engine. The system includes a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to an engine support structure of the aircraft. The first and second links are configured to define a focal point thereof at a location that is a distance from a centerline of the engine of not more than 15% of an inlet diameter at an inlet of the engine, and is located aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver. The location of the focal point is such that a moment of a thrust load of the engine and a moment of the inlet load oppose each other, thereby reducing backbone bending of the engine during the climb maneuver.
摘要翻译：一种能够减少高旁路涡扇风扇发动机主臂偏转的安装系统和方法。该系统包括刚性结构和连杆机构，其具有至少第一和第二连杆，每个连杆都枢转地连接到刚性结构并且适于枢转地连接到飞行器的发动机支撑结构。第一和第二连杆构造成在距离发动机中心线一定距离的位置处限定其焦点，该位置不大于发动机入口处入口直径的15％，并位于向量当飞机处于爬升机动时，发动机受到的入口负载。焦点的位置使得发动机的推力负载和入口负载的力矩相对的时刻，从而减少在爬升机动期间发动机的主干弯曲。

5. 发明申请

US20120304621A1 CLAMPING SYSTEM AND METHOD FOR THRUST REVERSER ATTACHMENT 有权
标题翻译：夹紧系统和方法用于逆向连接
公开(公告)号：US20120304621A1
公开(公告)日：2012-12-06
申请号：US13325203
申请日：2011-12-14
申请人： Alan Roy Stuart , John Robert Fehrmann
发明人： Alan Roy Stuart , John Robert Fehrmann
IPC分类号： F02K1/54 , B23P17/00 , F02K3/02
CPC分类号： F01D25/243 , F02K1/64 , F02K1/72 , F05D2230/60 , F05D2260/30 , Y10T29/49229
摘要： A method and system suitable facilitating the connection and disconnection of a thrust reverser assembly to a fan case of a nacelle of a gas turbine engine. The method and system entail operating a clamping system to simultaneously engage and disengage flanges associated with the fan case and flanges associated with the fixed structure of the thrust reverser assembly. The clamping system includes a plurality of over-center clamping mechanisms, each of which is movable to simultaneously clamp together complementary flanges of the thrust reverser assembly and the fan case.
摘要翻译：一种适合促进推力反向器组件与燃气涡轮发动机的机舱的风扇壳体的连接和断开的方法和系统。该方法和系统需要操作夹紧系统以同时接合和分离与风扇壳体相关联的凸缘和与推力反向器组件的固定结构相关联的凸缘。夹紧系统包括多个过中心夹紧机构，每个夹紧机构可移动以同时夹紧推力反向器组件和风扇壳体的互补凸缘。

6. 发明申请

US20120079805A1 THRUST REVERSER ASSEMBLY 审中-公开
标题翻译：扭矩反向装置
公开(公告)号：US20120079805A1
公开(公告)日：2012-04-05
申请号：US13247596
申请日：2011-09-28
申请人： Alan Roy Stuart , John Robert Fehrmann
发明人： Alan Roy Stuart , John Robert Fehrmann
IPC分类号： F02K3/02
CPC分类号： F02K1/72 , F02K3/06
摘要： A thrust reverser assembly includes a first cowl member and a second cowl member repositionable relative to the first cowl member and operable to open a gap between the first cowl member and the second cowl member. A movable member is in supported connection with the second cowl member. The movable member is passively actuatable to move between a generally axially extending disposition and a generally radially extending disposition to direct bypass airflow of a turbofan engine.
摘要翻译：推力反向器组件包括第一整流罩构件和第二整流罩构件，其可相对于第一整流罩构件重新定位并且可操作以打开第一整流罩构件和第二整流罩构件之间的间隙。可移动构件与第二整流罩构件支撑连接。可移动构件被动地致动以在大致轴向延伸的配置和大体上径向延伸的配置之间移动，以引导涡轮风扇发动机的旁路气流。

7. 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。

8. 发明授权

US08713910B2 Integrated thrust reverser/pylon assembly 有权
标题翻译：集成推力反向器/塔架总成
公开(公告)号：US08713910B2
公开(公告)日：2014-05-06
申请号：US12533334
申请日：2009-07-31
申请人： Alan Roy Stuart , John Robert Fehrmann
发明人： Alan Roy Stuart , John Robert Fehrmann
IPC分类号： F02K3/02 , F02K1/00
CPC分类号： F02K1/72 , Y02T50/672
摘要： Assembly for supporting a gas turbine engine comprises a support member including mounting sites for attachment to an associated aircraft. The support member includes integral slider tracks disposed on opposed sidewalls for selective engagement with a translatable cowl. The translatable cowl is translatable along the slider tracks to selectively cover and expose a cascade thrust-reversing structure. The cascade structure includes arcuate segments mounted in hinged relationship to the support member. Rearward translation of the translatable cowl to a service position permits the cascade structure to be opened for access to the core engine.
摘要翻译：用于支撑燃气涡轮发动机的组件包括支撑构件，该支撑构件包括用于附接到相关飞行器的安装位置。支撑构件包括设置在相对侧壁上的整体滑块轨道，用于与可平移的整流罩选择性地接合。可平移的整流罩可以沿着滑块轨道平移，以选择性地覆盖和暴露级联推力反转结构。级联结构包括以铰链关系安装到支撑构件的弓形段。将可翻译整流罩向后平移到维修位置允许级联结构打开以接近核心发动机。

9. 发明申请

US20080010969A1 GAS TURBINE ENGINE AND METHOD OF OPERATING SAME 审中-公开
标题翻译：气体涡轮发动机及其运行方法
公开(公告)号：US20080010969A1
公开(公告)日：2008-01-17
申请号：US11456666
申请日：2006-07-11
申请人： Thomas Anthony Hauer , Alan Roy Stuart , John Robert Fehrmann
发明人： Thomas Anthony Hauer , Alan Roy Stuart , John Robert Fehrmann
IPC分类号： F02K1/54
CPC分类号： F02K1/72 , B64D29/02
摘要： A method for operating a gas turbine engine assembly for an aircraft that includes a wing, wherein the gas turbine engine includes a core gas turbine engine and a fan coupled to the core gas turbine engine, the gas turbine engine assembly extends upstream from the wing and includes a first cowl and a second cowl that is repositionable with respect to the first cowl. The method includes selectively positioning the second cowl in a first operational position such that airflow is channeled from the gas turbine engine across a surface of the wing to facilitate increasing lift, and selectively positioning the second cowl in a second operational position such that the airflow is channeled from the gas turbine engine to effect reverse thrust.
摘要翻译：一种用于操作包括机翼的飞行器的燃气涡轮发动机组件的方法，其中所述燃气涡轮发动机包括核心燃气涡轮发动机和联接到所述核心燃气涡轮发动机的风扇，所述燃气涡轮发动机组件从所述机翼的上游延伸，包括可相对于第一整流罩重新定位的第一整流罩和第二整流罩。该方法包括将第二整流罩选择性地定位在第一操作位置，使得气流从燃气涡轮发动机引导穿过翼的表面以便于增加升力，并且将第二整流罩选择性地定位在第二操作位置，使得气流是从燃气涡轮发动机引导以产生反向推力。

10. 发明授权

US08727269B2 System and method for mounting an aircraft engine 有权
标题翻译：用于安装飞机发动机的系统和方法
公开(公告)号：US08727269B2
公开(公告)日：2014-05-20
申请号：US13487666
申请日：2012-06-04
申请人： Alan Roy Stuart , John Robert Fehrmann
发明人： Alan Roy Stuart , John Robert Fehrmann
IPC分类号： B64D27/00
CPC分类号： B64D27/18 , B64D27/12 , B64D27/26 , B64D2027/268 , F01D25/285 , F02C7/20 , F02K3/06 , Y02T50/671
摘要： A mounting system and method capable of reducing backbone deflection in a high-bypass turbofan engine. The system includes a rigid structure and a linkage mechanism having at least first and second links that are each pivotally connected to the rigid structure and adapted to be pivotally connected to an engine support structure of the aircraft. The first and second links are configured to define a focal point thereof at a location that is a distance from a centerline of the engine of not more than 15% of an inlet diameter at an inlet of the engine, and is located aft of a vector of an inlet load to which the engine is subjected when the aircraft is in a climb maneuver. The location of the focal point is such that a moment of a thrust load of the engine and a moment of the inlet load oppose each other, thereby reducing backbone bending of the engine during the climb maneuver.
摘要翻译：一种能够减少高旁路涡扇风扇发动机主臂偏转的安装系统和方法。该系统包括刚性结构和连杆机构，其具有至少第一和第二连杆，每个连杆都枢转地连接到刚性结构并且适于枢转地连接到飞行器的发动机支撑结构。第一和第二连杆构造成在距离发动机中心线一定距离的位置处限定其焦点，该位置不大于发动机入口处入口直径的15％，并位于向量当飞机处于爬升机动时，发动机受到的入口负载。焦点的位置使得发动机的推力负载和入口负载的力矩相对的时刻，从而减少在爬升机动期间发动机的主干弯曲。

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