专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明申请

WO2014130361A1 TURBOFAN ENGINE INCLUDING THIRD FLOWPATH EXHAUST NOZZLE 审中-公开
标题翻译：涡轮发动机，包括第三个流量排气喷嘴
公开(公告)号：WO2014130361A1
公开(公告)日：2014-08-28
申请号：PCT/US2014/016509
申请日：2014-02-14
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： ROBERGE, Gary D.
IPC分类号： F02K1/12 , F02K1/38 , F02K3/02 , F01D17/14
CPC分类号： F02K1/1207 , F02K1/008 , F02K1/1292 , F02K1/38 , F02K3/02 , F02K3/075 , F02K3/077 , F05D2240/128 , F05D2250/36
摘要： A turbofan engine that includes a first flowpath, a second flowpath, a third flowpath, and a third flowpath exhaust nozzle is provided. The first flowpath is radially inboard of the second flowpath at a location upstream of a core section of the turbofan engine. The third flowpath is radially outboard of the second flowpath at the location upstream of the core section. The third flowpath exhaust nozzle defines a plurality of third flowpath exhaust exit ports through which gas traveling along the third flowpath may be discharged. An area or a geometry of each of the plurality of third flowpath exhaust exit ports is independently and selectively adjustable. A method for operating the turbofan engine includes independently and selectively adjusting an area or a geometry of at least one of the plurality of third flowpath exhaust exit ports to achieve a desired engine operation.
摘要翻译：提供了包括第一流路，第二流路，第三流路和第三流路排气喷嘴的涡轮风扇发动机。第一流路在涡轮风扇发动机的核心部分的上游的位置处径向地位于第二流动路径的内侧。第三流路径位于第二流路径的外侧，位于核心部分的上游位置处。第三流路排气喷嘴限定了多个第三流路排气出口，通过该排出口可以排出沿第三流路行进的气体。多个第三流路排出口中的每一个的区域或几何形状是可独立且有选择地调节的。用于操作涡扇风扇发动机的方法包括独立地和选择性地调节多个第三流路排气出口中的至少一个的面积或几何形状，以实现期望的发动机操作。

2. 发明申请

WO2004061286A1 APPARATUS AND METHOD FOR CONTROLLING PRIMARY FLUID FLOW USING SECONDARY FLUID FLOW INJECTION 审中-公开
标题翻译：使用二次流体流注射控制主流体流动的装置和方法
公开(公告)号：WO2004061286A1
公开(公告)日：2004-07-22
申请号：PCT/US2003/025664
申请日：2003-08-14
申请人： LOCKHEED MARTIN CORPORATION
发明人： LEE, Douglas , ANDERSON, J., Thomas , HERSHBERGER, Brian, K.
IPC分类号： F02K1/30
CPC分类号： F02K1/008 , F02K1/002 , F02K1/28 , F02K9/82
摘要： A device for controlling the direction of flow of a primary fluid includes one or more injectors oriented to inject a secondary fluid against the direction of flow of the primary fluid. The injector is formed by drilling or otherwise forming a hole at an angle to the surface of one or more sidewalls of an engine nozzle or other device. A feedback controller regulates the amount and duration of the secondary fluid injection to achieve the commanded attitude or attitude rate. The controller is coupled to one or more plenums attached to the sidewall(s). The plenums can be arranged to deliver secondary fluid to one or more of the injectors. Secondary fluid delivery to each plenum can be controlled independently to control the flow of the primary fluid in one or more directions. The device can be used to provide thrust vectoring in an aircraft or other type of vehicle, as well as other applications where it is desired to control the direction of a primary fluid.
摘要翻译：用于控制主要流体的流动方向的装置包括一个或多个喷射器，其被定向成相对于主要流体的流动方向喷射次要流体。喷射器通过钻孔或以其它方式形成与发动机喷嘴或其他装置的一个或多个侧壁的表面成一定角度的孔。反馈控制器调节次流体注入的量和持续时间，以达到所指示的姿态或姿态。控制器耦合到附接到侧壁的一个或多个增压室。增压室可以布置成将二次流体输送到一个或多个喷射器。可以独立地控制到每个气室的二次流体输送以控制主要流体在一个或多个方向上的流动。该装置可用于在飞行器或其他类型的车辆以及期望控制主要流体的方向的其它应用中提供推力矢量。

3. 发明申请

WO2003081013A2 SYSTEM AND METHOD OF PULSED DETONATION INJECTION FOR FLUID FLOW CONTROL OF INLETS, NOZZLES, AND LIFT FANS 审中-公开
标题翻译：喷嘴，喷嘴和提升风机的流体流量控制的脉冲喷射注入系统和方法
公开(公告)号：WO2003081013A2
公开(公告)日：2003-10-02
申请号：PCT/US2003/002286
申请日：2003-01-23
申请人： LOCKHEED MARTIN CORPORATION
发明人： HUNTER, Louis, G. , MILLER, Daniel, N. , HAGSETH, Paul, E.
IPC分类号： F02K
CPC分类号： F02K1/28 , F02K1/008 , F02K7/02
摘要： According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the diverging portion, at least one port located in a wall of the nozzle and angled with respect to the fluid flow, and at least one pulse detonation device operable to inject a plurality of detonation waves in a pulsed manner through the port and into the fluid flow. The pulsed detonation waves operate to alter the fluid flow.
摘要翻译：根据本发明的一个实施例，用于改变流体流动的系统包括具有流体流动的喷嘴，包括会聚部分，会聚部分下游的发散部分和将会聚部分连接到发散部分的喉部，位于所述喷嘴的壁中并且相对于所述流体流成角度的至少一个端口以及至少一个脉冲爆震装置，其可操作以以脉冲的方式通过所述端口喷射到所述流体流中的多个爆震波。脉冲爆震波用于改变流体流动。

4. 发明申请

WO01046580A1 AN OUTLET DEVICE FOR A JET ENGINE 审中-公开
标题翻译：喷气发动机的出口装置
公开(公告)号：WO01046580A1
公开(公告)日：2001-06-28
申请号：PCT/SE2000/002661
申请日：2000-12-22
IPC分类号： F02K1/00 , F02K1/12 , F02K1/40 , F02K9/97
CPC分类号： F02K1/002 , F02K1/008 , F02K1/1207
摘要： An outlet device for a jet engine (2) includes an outlet channel (3), which has an upstream end (3') for being connected to the jet engine and a downstream end (3'') and which defines a main flow direction (a) for a jet from the jet engine. The outlet channel has in the proximity of the downstream end an elongated shape, seen in a section across the flow direction, and includes at least two outlet portions (4, 5, 6), which are separated from each other, for a respective outlet flow of said jet. A first outlet portion (5, 6) includes means for controlling the outlet direction of the outlet flow in a first plane and a second outlet portion (4) includes means for controlling the outlet direction of the outlet flow in a second plane, which forms an angle to the first plane. An aircraft may include such an outlet device.
摘要翻译：用于喷气发动机（2）的出口装置包括出口通道（3），其具有用于连接到喷气发动机的上游端（3'）和下游端（3“），并且限定主流向（a）来自喷气发动机的喷气机。出口通道在下游端附近具有细长形状，在横跨流动方向的截面中看到，并且包括彼此分离的至少两个出口部分（4,5,6），用于相应的出口所述射流的流动。第一出口部分（5,6）包括用于控制出口流在第一平面中的出口方向的装置，第二出口部分（4）包括用于控制出口流在第二平面中的出口方向的装置，与第一个平面的角度。飞机可以包括这样的出口装置。

5. 发明申请

WO00005496A1 VECTORING NOZZLE CONTROL SYSTEM 审中-公开
标题翻译：传感器喷嘴控制系统
公开(公告)号：WO00005496A1
公开(公告)日：2000-02-03
申请号：PCT/US1999/010560
申请日：1999-05-13
IPC分类号： F02K1/00 , F02K1/12 , F02K1/15
CPC分类号： F02K1/1292 , F02K1/008 , F02K1/15 , F05D2200/26
摘要： A method controls the stroke of three circumferentially spaced apart actuators attached at respective joints to an actuation ring positionable to vector thrust in a gas turbine engine exhaust nozzle. The circumferential angular location of each of the actuator joints is specified and, the stroke for each of the actuators is independently calculated using the joint locations in response to pitch and yaw commands. The actuators are then operated to effect the respective strokes therefor to position the nozzle. In a preferred embodiment, the angular locations are specified once, and trigonometric functions thereof are calculated and stored in memory. The stored values may then be used subsequently in calculating stroke as the pitch and yaw commands change.
摘要翻译：一种方法控制附接在各个接头处的三个周向间隔开的致动器的行程，以致可定位成在燃气涡轮发动机排气喷嘴中矢量推力的致动环。规定每个致动器接头的周向角位置，并且根据俯仰和偏航指令，使用接合位置独立地计算每个致动器的行程。然后操作致动器以实现相应的行程以定位喷嘴。在优选实施例中，角度位置被指定一次，并且其三角函数被计算并存储在存储器中。随后随着俯仰和偏航指令的改变，随后可以使用所存储的值来计算行程。

6. 发明申请

WO1994021910A1 EXTERNAL FLAP VECTORING MECHANISM 审中-公开
标题翻译：外部翼片载体机构
公开(公告)号：WO1994021910A1
公开(公告)日：1994-09-29
申请号：PCT/US1993002754
申请日：1993-03-18
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , BARCZA, William, K.
IPC分类号： F02K01/00
CPC分类号： F02K1/008
摘要： An external flap vectoring mechanism on an axisymmetric gas turbine exhaust nozzle, the external flap vectoring mechanism comprising a plurality of external flaps, each such flap having first (11) and second flaps (12), the first flap pivotably connected to a sync ring (14) and the second flap pivotably connected to the aft end of the first flap thereby providing for lateral movement of the second flap relative to the first.
摘要翻译：在轴对称燃气轮机排气喷嘴上的外部翼片向导机构，所述外部翼片矢量化机构包括多个外部翼片，每个所述翼片具有第一和第二翼片（12），所述第一翼片可枢转地连接到同步环（ 14），并且第二折片可枢转地连接到第一翼片的后端，从而提供第二翼片相对于第一翼片的横向移动。

7. 发明申请

WO2011055061A1 ENGIN VOLANT, SPATIAL OU AÉRIEN, POURVU D'UN SYSTÈME PROPULSIF À TUYÈRE ORIENTABLE 审中-公开
标题翻译：使用具有直接喷射喷嘴的推进系统提供的空中或空间
公开(公告)号：WO2011055061A1
公开(公告)日：2011-05-12
申请号：PCT/FR2010/052287
申请日：2010-10-26
申请人： ASTRIUM SAS , CAYE, Paul
发明人： CAYE, Paul
IPC分类号： B64G1/28 , B64G1/38 , B64G1/10 , F02K9/84
CPC分类号： B64G1/38 , B64G1/28 , B64G1/401 , F02K1/008 , F02K1/763 , F02K9/84
摘要： L'engin volant comporte des moyens (4) qui sont aptes à déplacer la tuyère (1), en l'absence de propulsion, pour engendrer des forces inertielles destinées à le stabiliser.
摘要翻译：飞行器包括能够在没有推进力的情况下移动喷嘴（1）的装置（4），以产生用于稳定车辆的惯性力。

8. 发明申请

WO00005497A1 VECTORING NOZZLE CALIBRATION 审中-公开
标题翻译： VECTORING NOZZLE校准
公开(公告)号：WO00005497A1
公开(公告)日：2000-02-03
申请号：PCT/US1999/011445
申请日：1999-05-24
IPC分类号： F02K1/15 , F02K1/00 , F02K1/12
CPC分类号： F02K1/008
摘要： A method and system are used to calibrate a plurality of actuators joined to an actuation ring in a control system for vectoring exhaust flaps in a vectoring nozzle. The actuators include output rods which are positioned to respective first positions at which output stroke is measured. The actuators are repositioned to different second positions, and the output stroke thereof is again measured. The stroke measurement for each of the actuators is calibrated to effect a common linear response between the first and second measurement positions. The calibrated actuators ensure coordinated linear actuation thereof as the output rods are positioned between their minimum and maximum extensions.
摘要翻译：一种方法和系统用于校准连接到用于在向量化喷嘴中引导排气翼的控制系统中的致动环的多个致动器。致动器包括输出杆，其定位在测量输出冲程的相应的第一位置。致动器重新定位到不同的第二位置，并且再次测量其输出冲程。对每个致动器的行程测量被校准以实现第一和第二测量位置之间的公共线性响应。当输出杆位于其最小和最大延伸之间时，经校准的致动器确保其协调的线性致动。

9. 发明申请

WO1998016732A1 AN AXISYMMETRIC VECTORING NOZZLE ACTUATING SYSTEM HAVING MULTIPLE POWER CONTROL CIRCUITS 审中-公开
标题翻译：具有多个功率控制电路的轴对称矢量喷嘴动作系统
公开(公告)号：WO1998016732A1
公开(公告)日：1998-04-23
申请号：PCT/US1996016406
申请日：1996-10-16
申请人： GENERAL ELECTRIC COMPANY
发明人： GENERAL ELECTRIC COMPANY , AUSDENMOORE, Robert, Michael
IPC分类号： F02K01/15
CPC分类号： F02K1/008 , F02K1/15 , Y02T50/671
摘要： A failsafe nozzle actuating system (2) for an aircraft gas turbine engine axisymmetric vectoring exhaust nozzle (14) has a vectoring ring (86) operably linked to a plurality of pivotal flaps (50) which are circumferentially disposed about a nozzle centerline (8) and bounding an exhaust gas flowpath (4) in the nozzle (14). The failsafe nozzle actuating system (2) has at least two independently operable first and second vertoring actuating systems (2A and 2B) including first and second groups of actuators (90A and 90B) operably connected to the vectoring ring (86) and first and second failsafe control means to control power to the first and second groups of actuators (90A and 90B), respectively. The first group of vectoring actuators is interdigitated with the second group of second vectoring actuators around the nozzle (14). Either of the two groups of actuators are operable to actuate the nozzle (14) when the other group is failsafed.
摘要翻译：用于飞机燃气涡轮发动机轴对称矢量排气喷嘴（14）的故障保护喷嘴致动系统（2）具有可操作地连接到围绕喷嘴中心线（8）周向设置的多个枢转翼片（50）的矢量环（86）并且在所述喷嘴（14）中限定排气流路（4）。故障保护喷嘴致动系统（2）具有至少两个独立可操作的第一和第二垂直致动系统（2A和2B），包括可操作地连接到向导环（86）的第一和第二组致动器组（90A和90B），第一和第二组致动系统故障保护控制装置分别控制第一和第二组致动器（90A和90B）的动力。第一组矢量执行器与围绕喷嘴（14）的第二组第二矢量执行器相互交错。当另一组发生故障时，两组致动器中的任一组可操作以致动喷嘴（14）。

10. 发明申请

WO1992003649A1 AXISYMMETRIC NOZZLE WITH GIMBLED UNISON RING 审中-公开
标题翻译：带有GIMBLED UNISON环的AXISYMMETRIC喷嘴
公开(公告)号：WO1992003649A1
公开(公告)日：1992-03-05
申请号：PCT/US1991005197
申请日：1991-07-23
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： UNITED TECHNOLOGIES CORPORATION , MCLAFFERTY, George, H. , THAYER, Edward, B. , STEWART, Jim, D.
IPC分类号： F02K01/12
CPC分类号： F02K1/1223 , F02K1/008
摘要： A thrust vectoring exhaust nozzle (10) includes a plurality of flaps (16-22) and seals (24-28) positioned by a unison ring (52) and flap links (54-60).
摘要翻译：推力矢量排气喷嘴（10）包括多个翼片（16-22）和由协调环（52）和翼片连杆（54-60）定位的密封件（24-28）。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式