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1. 发明申请

US20090178416A1 BIFURCATION AND AFT VENT USED TO VARY FAN NOZZLE EXIT AREA 有权
标题翻译：用于风扇喷嘴出口区域的分岔和通风口
公开(公告)号：US20090178416A1
公开(公告)日：2009-07-16
申请号：US12374336
申请日：2006-10-12
申请人： Edward F. Migliaro , Michael Winter , Ashok K. Jain
发明人： Edward F. Migliaro , Michael Winter , Ashok K. Jain
IPC分类号： F02K1/30 , F02K3/06
CPC分类号： F02K1/15 , F02K1/30 , F02K3/06 , F05D2220/326 , F05D2220/327
摘要： A turbofan engine includes a core nacelle housing a spool having a turbine. A turbofan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the turbofan and core nacelle. A bifurcation supports the core nacelle relative to the fan nacelle and extends radially between the nacelles. The core and fan nacelles provide a bypass flow path receiving bypass flow from the turbofan. In the example, the nacelles provide a fixed nozzle exit area. The bifurcation includes an inlet that is in communication with a passage. The passage is selectively opened and closed by a valve to provide air from the inlet to a vent opening near the nozzle exit area. By opening the valve, the nozzle exit area is effectively increased to provide increased bypass flow through the turbine engine.
摘要翻译：涡轮风扇发动机包括容纳具有涡轮的阀芯的核心机舱。涡轮风扇布置在核心机舱的上游并联接到线轴。风扇机舱围绕涡轮风扇和核心机舱。分叉支撑相对于风扇机舱的核心机舱，并且在发动机舱之间径向延伸。核心和风扇舱提供旁路流路，从涡轮风扇接收旁路流。在该示例中，发动机舱提供固定的喷嘴出口区域。分叉包括与通道连通的入口。该通道由阀选择性地打开和关闭，以将空气从入口提供到喷嘴出口区域附近的通风口。通过打开阀门，喷嘴出口区域被有效地增加，以提供通过涡轮发动机的增加的旁路流量。

2. 发明授权

US08650854B2 Bifurcation and aft vent used to vary fan nozzle exit area 有权
标题翻译：分岔和尾部通风口用于改变风扇喷嘴出口区域
公开(公告)号：US08650854B2
公开(公告)日：2014-02-18
申请号：US12374336
申请日：2006-10-12
申请人： Edward F. Migliaro, Jr. , Michael Winter , Ashok K. Jain
发明人： Edward F. Migliaro, Jr. , Michael Winter , Ashok K. Jain
IPC分类号： F02K1/00
CPC分类号： F02K1/15 , F02K1/30 , F02K3/06 , F05D2220/326 , F05D2220/327
摘要： A turbofan engine includes a core nacelle housing a spool having a turbine. A turbofan is arranged upstream from the core nacelle and is coupled to the spool. A fan nacelle surrounds the turbofan and core nacelle. A bifurcation supports the core nacelle relative to the fan nacelle and extends radially between the nacelles. The core and fan nacelles provide a bypass flow path receiving bypass flow from the turbofan. In the example, the nacelles provide a fixed nozzle exit area. The bifurcation includes an inlet that is in communication with a passage. The passage is selectively opened and closed by a valve to provide air from the inlet to a vent opening near the nozzle exit area. By opening the valve, the nozzle exit area is effectively increased to provide increased bypass flow through the turbine engine.
摘要翻译：涡轮风扇发动机包括容纳具有涡轮的阀芯的核心机舱。涡轮风扇布置在核心机舱的上游并联接到线轴。风扇机舱围绕涡轮风扇和核心机舱。分叉支撑相对于风扇机舱的核心机舱，并且在发动机舱之间径向延伸。核心和风扇舱提供旁路流路，从涡轮风扇接收旁路流。在该示例中，发动机舱提供固定的喷嘴出口区域。分叉包括与通道连通的入口。该通道由阀选择性地打开和关闭，以将空气从入口提供到喷嘴出口区域附近的通风口。通过打开阀门，喷嘴出口区域被有效地增加，以提供通过涡轮发动机的增加的旁路流量。

3. 发明授权

US09228534B2 Variable contour nacelle assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的可变轮廓机舱组件
公开(公告)号：US09228534B2
公开(公告)日：2016-01-05
申请号：US11772287
申请日：2007-07-02
申请人： Ashok K. Jain , Michael Winter
发明人： Ashok K. Jain , Michael Winter
IPC分类号： F02C7/042 , F02K3/06 , B64D33/02 , F02C7/045
CPC分类号： F02K3/06 , B64D33/02 , F02C7/042 , F02C7/045 , F05D2270/62 , F05D2270/64 , F05D2300/505 , Y02T50/671 , Y10T137/0645
摘要： A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.
摘要翻译：燃气涡轮发动机包括至少部分地围绕压缩机部分，燃烧器部分和涡轮部分的压缩机部分，燃烧器部分，涡轮部分和机舱组件。机舱组件的至少一部分包括可调轮廓。包括可调节轮廓的机舱组件的部分可选择性地在第一部分和第二位置之间移动以影响机舱组件的可调轮廓。控制器识别异常飞行器操作状况，并响应于检测到异常的飞行器操作状况而选择性地将包括可调节轮廓的机舱组件的部分移动在第一位置和第二位置之间。

4. 发明申请

US20090252600A1 ACTUATION OF A TURBOFAN ENGINE BIFURCATION TO CHANGE AN EFFECTIVE NOZZLE EXIT AREA 有权
标题翻译：涡轮发动机启动改造有效的喷嘴出口区域
公开(公告)号：US20090252600A1
公开(公告)日：2009-10-08
申请号：US12441576
申请日：2006-10-12
申请人： Michael Winter , Ashok K. Jain
发明人： Michael Winter , Ashok K. Jain
IPC分类号： F01D17/00
CPC分类号： F02K3/075 , F01D17/141 , F02K1/12
摘要： The invention relates to a turbine engine that includes a spool supporting at least one of a compressor and a turbine. A turbofan is coupled to the spool The spool is arranged in a core nacelle, and the turbofan is arranged upstream from the core nacelle. A fan nacelle surrounds the turbofan and the core nacelle and provides a bypass flow path. A structure extends radially between the core and fan nacelles to support the core nacelle relative to the fan nacelle. Surfaces are supported relative to the fixed structure and are moveable between closed and open positions to selectively obstruct bypass flow through the bypass flow path, thereby changing the effective area of the exit nozzle. A change in the effective area of the nozzle exit can be used to improve the efficiency and operation of the turbine engine.
摘要翻译：本发明涉及一种涡轮发动机，其包括支撑压缩机和涡轮机中的至少一个的阀芯。涡轮风扇联接到阀芯上。阀芯布置在核心机舱中，涡轮风扇布置在核心机舱的上游。风扇机舱围绕涡轮风扇和核心机舱，并提供旁路流动路径。结构在核心和风扇机舱之间径向延伸，以相对于风扇机舱支撑核心机舱。表面相对于固定结构被支撑，并且可在闭合位置和打开位置之间移动，以选择性地阻碍旁路流动通过旁路流动路径，从而改变出口喷嘴的有效面积。可以使用喷嘴出口的有效面积的变化来提高涡轮发动机的效率和操作。

5. 发明申请

US20090235638A1 VARIABLE AREA NOZZLE ASSISTED GAS TURBINE ENGINE RESTARTING 有权
标题翻译：可变区域喷嘴辅助气体涡轮发动机重新启动
公开(公告)号：US20090235638A1
公开(公告)日：2009-09-24
申请号：US12441756
申请日：2006-10-12
申请人： Ashok K. Jain , Michael Winter
发明人： Ashok K. Jain , Michael Winter
IPC分类号： F02C7/262 , F02K1/06
CPC分类号： F02C7/262 , F01D25/24 , F02C9/16 , F02K1/06 , F02K1/1207 , F02K1/15 , F02K3/075 , F05D2220/32 , F05D2260/85 , F05D2270/092
摘要： A turbofan engine starting system includes a core nacelle housing (12), a compressor (16) and a turbine (18). The core nacelle is disposed within a fan nacelle (34). The fan nacelle includes a turbofan (20). A bypass flow path (B) downstream from the turbofan is arranged between the two nacelles. A controller (50) is programmed to manipulate the nozzle exit area (A) of the bypass flow path to facilitate startup of the engine. In one example, the controller manipulates the nozzle exit area using hinged flaps (42) in response to an engine shutdown condition. The flaps open and close to adjust the nozzle exit area and the associated bypass flow rate, the mass flow rate of the air through the cave nacelle and the rotational speed of the compressor rotar (14).
摘要翻译：涡轮风扇发动机启动系统包括核心机舱壳体（12），压缩机（16）和涡轮机（18）。核心机舱设置在风扇机舱（34）内。风扇机舱包括涡轮风扇（20）。涡轮风扇下游的旁路流路（B）布置在两个机舱之间。控制器（50）被编程为操纵旁路流动路径的喷嘴出口区域（A）以便于启动发动机。在一个示例中，响应于发动机关闭状态，控制器使用铰接的翼片（42）来操纵喷嘴出口区域。翼片打开和关闭以调节喷嘴出口面积和相关的旁路流量，通过洞穴舱的空气的质量流量和压缩机转子的旋转速度（14）。

6. 发明申请

US20080267762A1 NACELLE ASSEMBLY HAVING INLET AIRFOIL FOR A GAS TURBINE ENGINE 有权
标题翻译：具有用于气体涡轮发动机的入口空气的空调组件
公开(公告)号：US20080267762A1
公开(公告)日：2008-10-30
申请号：US11739216
申请日：2007-04-24
申请人： Ashok K. Jain , Michael Winter
发明人： Ashok K. Jain , Michael Winter
IPC分类号： B64C21/00
CPC分类号： F02C7/042 , B64C23/00 , B64D33/02 , B64D2033/0226 , B64D2033/0286 , F02K3/00 , F05D2270/17
摘要： A nacelle assembly includes an inlet lip section and an airfoil adjacent to the inlet lip section. The airfoil is selectively moveable between a first position and a second position to adjust the flow of oncoming airflow and to influence an effective boundary layer thickness of the nacelle assembly.
摘要翻译：机舱组件包括入口唇部和与入口唇部相邻的翼面。翼型件可选择性地在第一位置和第二位置之间移动以调节迎面而来的气流的流动并且影响机舱组件的有效边界层厚度。

7. 发明授权

US08209953B2 Gas turbine engine system providing simulated boundary layer thickness increase 有权
标题翻译：提供模拟边界层厚度的燃气轮机系统增加
公开(公告)号：US08209953B2
公开(公告)日：2012-07-03
申请号：US12963667
申请日：2010-12-09
申请人： Michael Winter , Ashok K. Jain
发明人： Michael Winter , Ashok K. Jain
IPC分类号： F02K3/02
CPC分类号： F02C6/08 , B64D33/02 , B64D2033/0226 , F02C7/045 , F02C7/047 , F02K1/28 , F02K3/06 , F04D27/0238 , F04D27/0253 , F04D29/545 , F04D29/684 , Y10T137/0536
摘要： A gas turbine engine system for an aircraft includes a nacelle having a fan cowl with an inlet lip section and a core cowl, at least one compressor and at least one turbine, at least one combustor between the compressor and the turbine, a bleed passage, and a controller. The bleed passage includes an inlet for receiving a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The controller identifies an operability condition and selectively introduces the bleed airflow near a boundary layer of the inlet lip section in response to the operability condition.
摘要翻译：用于飞行器的燃气涡轮发动机系统包括具有风扇罩的机舱，其具有入口唇部和芯罩，至少一个压缩机和至少一个涡轮，压缩机和涡轮之间的至少一个燃烧器，排放通道，和控制器。排放通道包括用于接收排出气流的入口和从出口沿上游方向排出排气的出口。控制器识别可操作性条件，并响应于可操作性条件选择性地引入入口唇缘部分的边界层附近的排出气流。

8. 发明授权

US08209950B2 Detecting ice buildup on an aircraft engine and actuating the turbofan exit nozzle to break the ice 有权
标题翻译：检测飞机发动机上的积冰并启动涡轮风扇出口喷嘴以打破冰块
公开(公告)号：US08209950B2
公开(公告)日：2012-07-03
申请号：US12441587
申请日：2006-10-12
申请人： Ashok K. Jain , Michael Winter
发明人： Ashok K. Jain , Michael Winter
IPC分类号： F02G3/00
CPC分类号： F02K1/16 , B64D15/16 , B64D29/00 , F02C7/047 , F02K1/06 , F05D2260/16 , F05D2260/80 , F05D2270/44
摘要： A turbofan engine deicing system includes a core nacelle (12) housing a turbine. A turbofan (20) is arranged upstream from the core nacelle. A controller (50) manipulates the turbofan in response to detecting an icing condition for avoiding undesired ice buildup on the turbofan engine (10) and nacelle parts. In one example, a variable area nozzle (40) is actuated to generate pressure pulses or a surge condition to break up any ice buildup. The icing condition can be determined by at least one sensor (52) and/or predicted based upon icing conditions schedules.
摘要翻译：涡轮风扇发动机除冰系统包括容纳涡轮的核心机舱（12）。涡轮风扇（20）布置在核心机舱的上游。控制器（50）响应于检测到结冰条件来操纵涡扇风扇，以避免涡轮风扇发动机（10）和机舱部件上的不期望的积冰。在一个示例中，致动可变区域喷嘴（40）以产生压力脉冲或喘振状况以分解任何积冰。结冰条件可以由至少一个传感器（52）确定和/或基于结冰条件计划预测。

9. 发明授权

US07870721B2 Gas turbine engine providing simulated boundary layer thickness increase 有权
标题翻译：提供模拟边界层厚度的燃气轮机增加
公开(公告)号：US07870721B2
公开(公告)日：2011-01-18
申请号：US11595040
申请日：2006-11-10
申请人： Michael Winter , Ashok K. Jain
发明人： Michael Winter , Ashok K. Jain
IPC分类号： F02K3/02
CPC分类号： F02C6/08 , B64D33/02 , B64D2033/0226 , F02C7/045 , F02C7/047 , F02K1/28 , F02K3/06 , F04D27/0238 , F04D27/0253 , F04D29/545 , F04D29/684 , Y10T137/0536
摘要： A nacelle assembly for a gas turbine engine includes a fan cowl disposed about an axis, a core cowl within the fan cowl and a bleed passage having an inlet that receives a bleed airflow and an outlet that discharges the bleed airflow in an upstream direction from the outlet. The bleed airflow is selectively introduced near a boundary layer of an inlet lip section of the fan cowl.
摘要翻译：用于燃气涡轮发动机的机舱组件包括围绕轴线设置的风扇罩，风扇整流罩内的核心罩，以及具有接收排出气流的入口的排放通道和从上游方向排放出气流的出口出口。排出气流被选择性地引入到风扇罩的入口唇部的边界层附近。

10. 发明授权

US09328666B2 Variable area nozzle assisted gas turbine engine restarting 有权
标题翻译：可变面积喷嘴辅助燃气轮机重启
公开(公告)号：US09328666B2
公开(公告)日：2016-05-03
申请号：US12441756
申请日：2006-10-12
申请人： Ashok K. Jain , Michael Winter
发明人： Ashok K. Jain , Michael Winter
IPC分类号： F02C7/262 , F02K1/12 , F02K1/15 , F02K3/075
CPC分类号： F02C7/262 , F01D25/24 , F02C9/16 , F02K1/06 , F02K1/1207 , F02K1/15 , F02K3/075 , F05D2220/32 , F05D2260/85 , F05D2270/092
摘要： An example turbofan engine restarting system includes a core nacelle housing, a compressor, and a turbine. The core nacelle is disposed within a fan nacelle. A bypass flowpath downstream from the turbofan is arranged between the two nacelles. A controller is programmed to manipulate the nozzle exit area of the bypass flowpath to facilitate startup of the engine. In one example, the controller manipulates the nozzle exit area using hinged flaps in response to an engine shutdown condition. The flaps open and close to adjust the nozzle exit area and the associated bypass flow rate, the mass flow rate of the air through the core nacelle and the rotational speed of the compressor rotor.
摘要翻译：涡轮风扇发动机重起系统的一个例子包括一个核心机舱壳体，一个压缩机和一个涡轮机。核心机舱设置在风扇机舱内。在这两个机舱之间布置有涡轮风扇下游的旁路流路。控制器被编程为操纵旁路流路的喷嘴出口区域以便于启动发动机。在一个示例中，控制器响应于发动机关闭状态而使用铰接的襟翼来操纵喷嘴出口区域。翼片打开和关闭以调节喷嘴出口面积和相关的旁路流量，通过核心机舱的空气的质量流量和压缩机转子的转速。

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