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1. 发明申请

US20150176490A1 Aircraft Engine Anti-Icing (EAI) Barrier Assembly, System and Method 有权
标题翻译：飞机发动机防冰（EAI）阻隔装置，系统和方法
公开(公告)号：US20150176490A1
公开(公告)日：2015-06-25
申请号：US13972902
申请日：2013-08-21
申请人： The Boeing Company
发明人： Haisan K. Trinh , Stuart W. Vogel , Robert T. Breister , Jack W. Mauldin
IPC分类号： F02C7/047 , B64D15/02
CPC分类号： F02C7/047 , B64D15/02 , B64D2033/0233 , F05D2230/60 , Y02T50/671 , Y10T29/49229
摘要： There is provided an aircraft engine anti-icing (EAI) barrier assembly. The aircraft EAI barrier assembly has a slip joint subassembly having a forward end and an aft end. The forward end is configured for fixed attachment at a forward bulkhead of an engine of an aircraft, and an aft end with a sliding joint. The aircraft EAI barrier assembly has a barrier subassembly attached through an aft bulkhead and has two mount pads configured for joined sealed attachment around the aft end of the slip joint subassembly to form a barrier to an engine inlet of the engine.
摘要翻译：提供飞机发动机防冰（EAI）屏障组件。飞机EAI屏障组件具有具有前端和后端的滑动接头子组件。前端构造成用于在飞行器的发动机的前舱壁处的固定附接，以及具有滑动接头的后端。飞机EAI屏障组件具有通过后舱壁连接的屏障子组件，并且具有两个安装垫，其构造成用于围绕滑动接头子组件的后端连接密封安装，以形成对发动机的发动机入口的屏障。

2. 发明授权

US09505499B2 Methods and apparatus for supporting engines and nacelles relative to aircraft wings 有权
标题翻译：相对于飞机机翼来支持发动机和发动机舱的方法和装置
公开(公告)号：US09505499B2
公开(公告)日：2016-11-29
申请号：US14928953
申请日：2015-10-30
申请人： The Boeing Company
发明人： Jack W. Mauldin , David W. Kwok , John A. Weidler , Antonio B. Gonzales , Edward L. Lawson , Andrew C. Kulak
IPC分类号： B64D27/00 , B64D27/26 , B64D29/00 , B64C7/02 , B64D29/02 , B64F5/00
CPC分类号： B64D27/26 , B64C7/02 , B64D29/00 , B64D29/02 , B64D2027/262 , B64F5/10 , Y02T50/44
摘要： Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.
摘要翻译：公开了相对于飞机机翼来支撑发动机和机舱的方法和装置。示例性装置包括机舱; 第一支撑结构，沿着发动机的推力轴联接在所述机舱和所述机舱的第一侧之间; 第二支撑结构，其沿所述推力轴线联接在所述机翼和所述机舱的第二侧之间，所述第一支撑结构与所述机翼上的所述第二支撑结构间隔开，纵向平面延伸穿过所述第一支撑结构，所述第二支撑结构和所述推力轴线，所述第一支撑结构相对于所述机翼刚性地固定，以基本上防止所述第一支撑结构发动机的运动，所述第二支撑结构相对于所述机翼刚性地固定，以基本上防止所述发动机的运动通过第二支撑结构，第一和第二支撑结构将联接到发动机的相对侧，以使得推力载荷能够通过第一和第二支撑结构反作用于机翼。

3. 发明申请

US20140262358A1 Fire Seal End Cap and Associated Multi-member Assembly and Method 有权
标题翻译：防火密封端盖和相关的多部件组装和方法
公开(公告)号：US20140262358A1
公开(公告)日：2014-09-18
申请号：US13975797
申请日：2013-08-26
申请人： The Boeing Company
发明人： Scott M. Livingston , Jack W. Mauldin , Robert P. Lotter , Paul B. Philipp , Khalid S. Alshobber , John N. Harris
IPC分类号： A62C3/08
CPC分类号： A62C3/08 , A62C2/06 , A62C99/009 , B64C1/10 , B64C1/16 , B64D27/00 , B64D45/00 , B64D2045/009 , F02K1/78 , F16J15/027 , F16J15/065 , F16L55/10 , F16L55/1026
摘要： A multi-member assembly including a first structural member, a second structural member opposed from the first structural member, a crossover seal positioned between the first and second structural members, wherein the crossover seal defines a bore, and an end cap including a cap portion and a plug portion protruding from the cap portion, wherein the plug portion is at least partially received in the bore such that the cap portion bridges the first and second structural members.
摘要翻译：一种多构件组件，包括第一结构构件，与第一结构构件相对的第二结构构件，位于第一和第二结构构件之间的交叉密封件，其中，交叉密封件限定孔，以及端盖，其包括盖部以及从所述帽部突出的插头部分，其中所述插头部分至少部分地容纳在所述孔中，使得所述帽部分桥接所述第一和第二结构构件。

4. 发明申请

US20170241577A1 Integrated Gas Purge Path for Welded Sandwich Structure 审中-公开
公开(公告)号：US20170241577A1
公开(公告)日：2017-08-24
申请号：US15047073
申请日：2016-02-18
申请人： The Boeing Company
发明人： William R. Schell , Edward O. Jorgenson , Jack W. Mauldin , Mark D. Gilcreest , Benjamin S. Northup
IPC分类号： F16L13/02 , B23K31/02
CPC分类号： B23K20/26 , B23K20/02 , B23K2101/045
摘要： A method of forming a weld on a work piece is disclosed. The method may include creating an internal cavity along the work piece and extending a conduit having an exit orifice into the internal cavity such that the exit orifice may be positioned adjacent to the weld to be formed. The method may further include supplying a purge gas to the conduit, the purge gas being carried through the conduit and pushed out of the exit orifice so as to displace undesirable gasses away from the weld to be formed and then subsequently forming the weld.

5. 发明授权

US09663238B2 Nacelle inlet lip skin with pad-up defining a developable surface having parallel ruling lines 有权
公开(公告)号：US09663238B2
公开(公告)日：2017-05-30
申请号：US14076450
申请日：2013-11-11
申请人： The Boeing Company
发明人： Daniel J. Kane , Stuart W. Vogel , Hoa V. Truong , Michael W. Kass , Andrew T. Gilmore , Paul D. Whitmore , Jack W. Mauldin , Alejandro Silva , John Ybarra
IPC分类号： F02C7/04 , B64D33/02
CPC分类号： B64D33/02 , B64D2033/0286 , F02C7/04 , Y10T137/0536
摘要： A nacelle inlet is provided for a turbo-fan engine for an aircraft. The nacelle inlet includes a lip skin having first and second pad-ups, an inner barrel including a forward flange and a bulkhead. The bulkhead, the lip skin and the inner barrel are attached together at mating surfaces. The bulkhead and the lip skin are attached together at mating surfaces. Each mating surface defines a surface geometry which approximates a developable surface having parallel ruling lines. The developable surfaces are formed by machining.

6. 发明授权

US09528442B2 Aircraft engine anti-icing (EAI) barrier assembly, system and method 有权
标题翻译：飞机发动机防冰（EAI）屏障组装，系统和方法
公开(公告)号：US09528442B2
公开(公告)日：2016-12-27
申请号：US13972902
申请日：2013-08-21
申请人： The Boeing Company
发明人： Haisan K. Trinh , Stuart W. Vogel , Robert T. Breister , Jack W. Mauldin
IPC分类号： F02C7/047 , B64D15/02 , B64D33/02
CPC分类号： F02C7/047 , B64D15/02 , B64D2033/0233 , F05D2230/60 , Y02T50/671 , Y10T29/49229
摘要： An aircraft engine anti-icing barrier assembly having a slip joint subassembly, a barrier subassembly, and a vapor barrier subassembly. The slip joint subassembly has a forward end for fixed attachment at a forward bulkhead of an aircraft engine, and has an aft end having a sliding joint. The barrier subassembly is attached to an aft side of an aft bulkhead and inserted through the aft bulkhead. The barrier subassembly has two mount pads with an upper mount pad and a lower mount pad configured for joined sealed attachment around the slip joint subassembly to form a barrier between an engine fan case compartment and an aft compartment in an engine inlet. The vapor barrier subassembly is attached to the aft side of the aft bulkhead and adjacent the barrier subassembly, has a boot element and a boot element retainer, and forms a vapor barrier to the slip joint subassembly.
摘要翻译：具有滑动接头子组件，阻挡子组件和蒸气阻挡子组件的飞机发动机防冰隔离组件。滑动接头子组件具有用于在飞行器发动机的前隔板处固定附接的前端，并且具有具有滑动接头的后端。隔壁子组件附接到后舱壁的后侧并插入通过后舱壁。阻挡子组件具有两个安装垫，其具有上安装焊盘和下安装焊盘，其被配置用于围绕滑动接头子组件的连接密封附接，以在发动机入口中的发动机风扇壳体隔间与后舱之间形成隔离物。蒸气阻挡子组件附接到后舱壁的后侧并且邻近阻挡子组件，具有靴形元件和靴形件保持器，并且对滑动接头子组件形成蒸气阻挡层。

7. 发明申请

US20160052637A1 METHODS AND APPARATUS FOR SUPPORTING ENGINES AND NACELLES RELATIVE TO AIRCRAFT WINGS 有权
标题翻译：支持与飞机机翼相关的发动机和机器的方法和装置
公开(公告)号：US20160052637A1
公开(公告)日：2016-02-25
申请号：US14928953
申请日：2015-10-30
申请人： The Boeing Company
发明人： Jack W. Mauldin , David W. Kwok , John A. Weidler , Antonio B. Gonzales , Edward L. Lawson , Andrew C. Kulak
IPC分类号： B64D27/26 , B64F5/00 , B64D29/00
CPC分类号： B64D27/26 , B64C7/02 , B64D29/00 , B64D29/02 , B64D2027/262 , B64F5/10 , Y02T50/44
摘要： Methods and apparatus for supporting engines and nacelles relative to aircraft wings are disclosed. An example apparatus includes a nacelle; a first support structure coupled between a wing and a first side of the nacelle along a thrust axis of an engine; a second support structure coupled between the wing and a second side of the nacelle along the thrust axis, the first support structure spaced apart from the second support structure on the wing, a longitudinal plane to extend through the first support structure, the second support structure, and the thrust axis, the first support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the first support structure, the second support structure to be rigidly fixed relative to the wing to substantially prevent movement of the engine by the second support structure, the first and second support structures to be coupled to opposite sides of the engine to enable thrust loads to be reacted through the first and second support structures to the wing.
摘要翻译：公开了相对于飞机机翼来支撑发动机和机舱的方法和装置。示例性装置包括机舱; 第一支撑结构，沿着发动机的推力轴联接在所述机舱和所述机舱的第一侧之间; 第二支撑结构，其沿所述推力轴线联接在所述机翼和所述机舱的第二侧之间，所述第一支撑结构与所述机翼上的所述第二支撑结构间隔开，纵向平面延伸穿过所述第一支撑结构，所述第二支撑结构和所述推力轴线，所述第一支撑结构相对于所述机翼刚性地固定，以基本上防止所述第一支撑结构发动机的运动，所述第二支撑结构相对于所述机翼刚性地固定，以基本上防止所述发动机的运动通过第二支撑结构，第一和第二支撑结构将联接到发动机的相对侧，以使得推力载荷能够通过第一和第二支撑结构反作用于机翼。

8. 发明授权

US10654125B2 Integrated gas purge path for welded sandwich structure 有权
公开(公告)号：US10654125B2
公开(公告)日：2020-05-19
申请号：US15047073
申请日：2016-02-18
申请人： The Boeing Company
发明人： William R. Schell , Edward O. Jorgenson , Jack W. Mauldin , Mark D. Gilcreest , Benjamin S. Northup
IPC分类号： B23K20/26 , B23K20/02 , B23K101/04
摘要： A method of forming a weld on a work piece is disclosed. The method may include creating an internal cavity along the work piece and extending a conduit having an exit orifice into the internal cavity such that the exit orifice may be positioned adjacent to the weld to be formed. The method may further include supplying a purge gas to the conduit, the purge gas being carried through the conduit and pushed out of the exit orifice so as to displace undesirable gasses away from the weld to be formed and then subsequently forming the weld.

9. 发明申请

US20180140878A1 Fire Seal End Cap and Associated Multi-Member Assembly and Method 审中-公开
公开(公告)号：US20180140878A1
公开(公告)日：2018-05-24
申请号：US15860791
申请日：2018-01-03
申请人： The Boeing Company
发明人： Scott M. Livingston , Jack W. Mauldin , Robert P. Lotter , Paul B. Philipp , Khalid S. Alshobber , John N. Harris
IPC分类号： A62C3/08 , B64C1/10
CPC分类号： A62C3/08 , A62C2/06 , A62C99/009 , B64C1/10 , B64C1/16 , B64D27/00 , B64D45/00 , B64D2045/009 , F02K1/78 , F16J15/027 , F16J15/065 , F16L55/10 , F16L55/1026
摘要： A fire seal end cap including a cap portion and a plug portion, wherein the plug portion protrudes from the cap portion, and wherein the cap portion and the plug portion are formed from a fire-resistant material.

10. 发明授权

US09889323B2 Fire seal end cap and associated multi-member assembly and method 有权
公开(公告)号：US09889323B2
公开(公告)日：2018-02-13
申请号：US13975797
申请日：2013-08-26
申请人： The Boeing Company
发明人： Scott M. Livingston , Jack W. Mauldin , Robert P. Lotter , Paul B. Philipp , Khalid S. Alshobber , John N. Harris
IPC分类号： F16L55/10 , A62C3/08 , F16J15/16 , F02F11/00 , B64C1/10 , B64C1/16 , B64D27/00 , B64D45/00 , F16J15/02 , F16J15/06
CPC分类号： A62C3/08 , A62C2/06 , A62C99/009 , B64C1/10 , B64C1/16 , B64D27/00 , B64D45/00 , B64D2045/009 , F02K1/78 , F16J15/027 , F16J15/065 , F16L55/10 , F16L55/1026
摘要： A multi-member assembly including a first structural member, a second structural member opposed from the first structural member, a crossover seal positioned between the first and second structural members, wherein the crossover seal defines a bore, and an end cap including a cap portion and a plug portion protruding from the cap portion, wherein the plug portion is at least partially received in the bore such that the cap portion bridges the first and second structural members.

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