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1. 发明申请

US20200207466A1 AUTOMOBILE ENGINE 审中-公开
公开(公告)号：US20200207466A1
公开(公告)日：2020-07-02
申请号：US16811864
申请日：2020-03-06
申请人： Xiaoyi ZHU
发明人： Xiaoyi ZHU
IPC分类号： B64C27/16 , F02C3/107 , F02B39/02 , F01K25/02 , B64C27/473 , B64C11/24 , B64C11/16 , F01D1/32 , F01D5/12
摘要： The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, and thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.

2. 发明授权

US10697299B2 Method for designing and building a wheel 有权
公开(公告)号：US10697299B2
公开(公告)日：2020-06-30
申请号：US15542275
申请日：2015-12-02
申请人： CARPYZ SAS
发明人： Pierre Carrouset , Nicole Carrouset , Gabrielle Carrouset
IPC分类号： B23P15/00 , F01D5/02 , F01D1/32 , F01D5/04 , F04D29/30 , B64C11/24 , F01D5/18
摘要： A method for designing and building a wheel that is simultaneously a turbine and an impeller with a plurality of impeller blades, wherein each impeller blade of the plurality of impeller blades is hollow along an entire length of the impeller blade and which leads into a peripheral circular chamber that operates as a fueled engine (THRA). The method includes building an evolving section of an inner channel of the impeller blades with a plurality of strips each having a neutral axis, wherein each impeller blade rests on a profile of a plurality of profiles of a corresponding neutral axis, the profile built for an inlet to the turbine and for inlets to each impeller blade.

3. 发明授权

US10518869B2 Turboprop 有权
公开(公告)号：US10518869B2
公开(公告)日：2019-12-31
申请号：US15547118
申请日：2016-01-27
申请人： Safran Aircraft Engines
发明人： Paul Antoine Foresto , Anthony Binder , Alexandre Gerard Francois Couilleaux , Norman Bruno Andre Jodet
IPC分类号： B64C11/24 , F01D5/18 , F02C7/04 , B64D33/02
摘要： A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and an outlet leading to the trailing edge of the blade transversely directed in relation to the main elongation direction, such that an inner stream of air flowing in the inner air stream channel by entering via the inlet adjacent to the root of the blade is discharged via the outlet adjacent to the trailing edge of the blade by forming a stream of blown air that moves away from the trailing edge in a direction which is transverse to the main elongation direction and which has a component in the direction of a skeleton line of the blade at the trailing edge.

4. 发明授权

US10407158B2 Blade plug for communicating fluid therethrough 有权
公开(公告)号：US10407158B2
公开(公告)日：2019-09-10
申请号：US15131765
申请日：2016-04-18
申请人： Hamilton Sundstrand Corporation , Ratier-Figeac SAS
发明人： Paul A. Carvalho , Stephane Grimal , Pierre Alexandre Picard
IPC分类号： B64C11/24 , F04D27/02 , F04D29/32
摘要： A blade plug for an aircraft blade is provided. The blade plug includes a first body having a boss extending therefrom and an aperture passing through the boss, the first body configured to sealingly engage with an opening of a blade, a plug cap configured to releasably engage with the boss and move between a first position and a second position, and a passage passing through the first body configured to allow fluid communication through the first body. When the plug cap is in the first position, fluid may not pass through the passage and, when the plug cap is in the second position, fluid may pass through the passage, and the first body has an outer diameter of 4.15 inches (105.37 mm).

5. 发明申请

US20180362145A1 METHOD AND APPARATUS TO IMPROVE LIFT TO DRAG RATIO OF A ROTOR BLADE 审中-公开
公开(公告)号：US20180362145A1
公开(公告)日：2018-12-20
申请号：US15843039
申请日：2017-12-15
申请人： Bell Helicopter Textron Inc.
发明人： Christopher E. Foskey , Brendan P. Lanigan
IPC分类号： B64C11/18 , B64C11/24
摘要： In a first aspect, there is a method for improving a lift to drag ratio of a rotor blade, including providing a blade member having a leading edge and a trailing edge; providing a leading edge extension member; and coupling the leading edge extension member to a portion of the leading edge of the blade member to form the rotor blade. In a second aspect, there is a rotor blade including a blade member having a leading edge, and a trailing edge; and a leading edge extension member disposed on the leading edge of the blade member, wherein the leading edge extension member is configured to extend the chord length of at least a portion of the rotor blade. In a third aspect, there is a leading edge extension member for a rotor blade including a convex exterior surface configured to extend at least a portion of the chord length of the rotor blade.

6. 发明授权

US09869297B2 Attachment method and system to install components, such as vortex generators, to a wind turbine blade 有权
公开(公告)号：US09869297B2
公开(公告)日：2018-01-16
申请号：US14706026
申请日：2015-05-07
申请人： General Electric Company
发明人： James Robert Tobin , William Max Gobeli , Scott Gabell Riddell , Michael Christopher Booth
IPC分类号： A46D1/00 , B44C1/17 , B63H1/26 , F03D11/02 , B64C11/16 , B64C11/24 , D05C15/00 , B32B15/04 , B64C27/46 , F04D29/38 , B32B3/06 , F03B3/12 , B32B33/00 , B32B37/00 , B32B38/10 , B32B5/00 , F01D5/14 , F01D5/18 , B29C51/16 , B29C63/00 , B29C65/00 , F03B7/00 , B63H7/02 , B32B7/04 , B32B7/12 , B32B7/14 , B32B9/00 , F03D1/06 , F03D13/10 , B29C65/48 , B29C65/72 , B29C65/50 , B29C65/56
CPC分类号： F03D1/0675 , B29C65/4825 , B29C65/483 , B29C65/5057 , B29C65/562 , B29C65/72 , F03D13/10 , F05B2240/122 , Y02E10/721
摘要： A method for installing an add-on component to a surface of a wind turbine blade includes attaching an adhesive side of strips of a double-sided adhesive tape onto either the surface of the wind turbine blade or a surface of the add-on component, the tape strips having a release liner on an opposite exposed side thereof. The tape strips having an extension tail of the release liner that extends beyond an edge of the add-on component when the add-on component is placed and held at a desired position against the surface of the wind turbine blade. With the add-on component held at the desired position, the extension tail is pulled away at an angle such that that release liner is removed along the length of the tape strip while maintaining the add-on component against the blade surface to attach the exposed adhesive under the release liner to either the surface of the wind turbine blade or the surface of the add-on component.

7. 发明申请

US20180009522A1 TURBOPROP 审中-公开
公开(公告)号：US20180009522A1
公开(公告)日：2018-01-11
申请号：US15547118
申请日：2016-01-27
申请人： Safran Aircraft Engines
发明人： Paul Antoine FORESTO , Anthony BINDER , Alexandre Gerard Francois COUILLEAUX , Norman Bruno Andre JODET
IPC分类号： B64C11/24 , F01D5/18 , F02C7/04
摘要： A turboprop including a propeller including a blade extending in a direction, which also includes a root, a leading edge, a trailing edge, and a wing tip, and an inner air stream channel, wherein the inner air stream channel includes an inlet located at the root of the blade and an outlet leading to the trailing edge of the blade transversely directed in relation to the main elongation direction, such that an inner stream of air flowing in the inner air stream channel by entering via the inlet adjacent to the root of the blade is discharged via the outlet adjacent to the trailing edge of the blade by forming a stream of blown air that moves away from the trailing edge in a direction which is transverse to the main elongation direction and which has a component in the direction of a skeleton line of the blade at the trailing edge.

8. 发明申请

US20160318599A1 BLADE PLUG FOR COMMUNICATING FLUID THERETHROUGH 审中-公开
标题翻译：用于传播流体的叶片
公开(公告)号：US20160318599A1
公开(公告)日：2016-11-03
申请号：US15131765
申请日：2016-04-18
申请人： Hamilton Sundstrand Corporation , Ratier-Figeac SAS
发明人： Paul A. Carvalho , Stephane Grimal , Pierre Alexandre Picard
IPC分类号： B64C11/24
CPC分类号： B64C11/24 , F04D27/0292 , F04D29/324
摘要： A blade plug for an aircraft blade is provided. The blade plug includes a first body having a boss extending therefrom and an aperture passing through the boss, the first body configured to sealingly engage with an opening of a blade, a plug cap configured to releasably engage with the boss and move between a first position and a second position, and a passage passing through the first body configured to allow fluid communication through the first body. When the plug cap is in the first position, fluid may not pass through the passage and, when the plug cap is in the second position, fluid may pass through the passage, and the first body has an outer diameter of 4.15 inches (105.37 mm).
摘要翻译：提供了一种用于飞机刀片的刀片插头。叶片插头包括第一本体，其具有从其延伸的凸台和穿过凸台的孔，第一主体被构造成与叶片的开口密封地接合，构造成可与凸台可释放地接合并在第一位置和第二位置，以及通过所述第一主体的通道，所述通道构造成允许通过所述第一主体的流体连通。当塞帽处于第一位置时，流体不能通过通道，并且当塞帽位于第二位置时，流体可以通过通道，并且第一主体具有4.15英寸（105.37mm）的外径）。

9. 发明授权

US08491263B1 Turbine blade with cooling and sealing 有权
标题翻译：涡轮叶片具有冷却和密封
公开(公告)号：US08491263B1
公开(公告)日：2013-07-23
申请号：US12820164
申请日：2010-06-22
申请人： George Liang
发明人： George Liang
IPC分类号： B64C11/24
CPC分类号： F01D5/187 , F01D5/20 , F05D2240/81
摘要： A turbine rotor blade with a thin thermal skin bonded to a spar to form a near-wall cooled blade, the blade having a near-wall cooling circuit formed by plurality of multiple pass serpentine flow cooling circuits that have cooling channels formed within the airfoil walls and the platform, and with a row of cooling air exit slots that connect to the last leg of the serpentine flow cooling channels and open onto an upstream side of the tip edge so that cooling air is discharged to form a blockage for the blade tip. The airfoil walls include radial extending cooling channels that form the airfoil legs of the serpentine cooling circuits.
摘要翻译：一种涡轮转子叶片，其具有粘结到翼梁的薄的热表面以形成近壁冷却的叶片，所述叶片具有由多个多通道蛇形流冷却回路形成的近壁冷却回路，所述多通道蛇形流冷却回路具有形成在翼型壁内的冷却通道和平台，以及一排冷却空气出口槽，其连接到蛇形流冷却通道的最后一段，并且在顶端边缘的上游侧开口，使得冷却空气被排出以形成用于叶片尖端的阻塞。翼型壁包括形成蛇形冷却回路的翼型腿的径向延伸的冷却通道。

10. 发明授权

US08192169B2 Highly reliable, low cost wind turbine rotor blade 有权
标题翻译：高可靠性，低成本的风力发电机转子叶片
公开(公告)号：US08192169B2
公开(公告)日：2012-06-05
申请号：US12757832
申请日：2010-04-09
申请人： Frederick W Piasecki
发明人： Frederick W Piasecki
IPC分类号： B64C11/24
CPC分类号： B23P15/04 , F03D1/06 , F03D9/00 , F03D9/25 , F03D13/20 , Y02E10/721 , Y02E10/725 , Y02E10/728 , Y02P70/523 , Y10T29/49336 , Y10T29/49337 , Y10T29/49339
摘要： A wind turbine rotor blade and a wind turbine incorporating the rotor blade include a first and second composite skin. A first and a second spar pultrusion having a base and a plurality of integral ribs generally normal to the base are attached to the inside surface of the first and second composite skins and extend the span of the rotor blade. At least one shear web connects a rib of the first spar pultrusion to a corresponding rib of the second spar pultrusion. The width of the spar pultrusions decreases in a step-wise fashion along the span of the rotor blade from the root to the tip. The leading or trailing edge of the rotor blade may be selectably opened for inspection and repair.
摘要翻译：并入转子叶片的风力涡轮机转子叶片和风力涡轮机包括第一和第二复合表皮。具有大致垂直于基座的基部和多个整体肋的第一和第二翼梁拉挤成型件附接到第一和第二复合材料表面的内表面并延伸转子叶片的跨度。至少一个剪切腹板将第一翼梁拉挤成形件的肋连接到第二翼梁拉挤成形件的对应肋部。翼梁拉挤成型件的宽度沿着转子叶片的跨度从根部到尖端以逐步的方式减小。转子叶片的前缘或后缘可选择地打开以进行检查和修理。

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