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

WO2014007880A2 REVERSE CORE GEAR TURBOFAN 审中-公开
标题翻译：反转核心齿轮TURBOFAN
公开(公告)号：WO2014007880A2
公开(公告)日：2014-01-09
申请号：PCT/US2013/033776
申请日：2013-03-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KUPRATIS, Daniel Bernard , MOON, Francis R.
CPC分类号： F02C6/02 , F01D17/141 , F02C3/05 , F02C3/10 , F02C3/107 , F02C3/13 , F02C3/145 , F02C7/36 , F02C9/18 , F02K3/06 , F02K3/065 , F02K3/075 , F05D2220/32 , F05D2220/323 , F05D2250/36 , F05D2260/4023 , F05D2260/4031 , F05D2270/053
摘要： A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.
摘要翻译：燃气涡轮发动机在轴向外部位置处具有风扇。风扇围绕旋转轴线旋转。风扇将空气输送到外部旁路管道中，并穿过定位在外部旁路管道径向内部的增压器风扇。增压风扇将空气输送到径向中间管道中，并且穿过冷涡轮机进入径向内部核心管道，其被引导到压缩机中。来自压缩机的空气沿着朝向风扇的方向轴向地流动通过燃烧器部分，并且在涡轮机部分的排气口被引导进入中间管道。减速器通过风扇驱动涡轮部分驱动风扇。还公开了一种方法。

2. 发明申请

WO2014046832A1 TRANSITION DUCT FOR USE IN A TURBINE ENGINE AND METHOD OF ASSEMBLY 审中-公开
标题翻译：涡轮发动机中使用的过渡管和组装方法
公开(公告)号：WO2014046832A1
公开(公告)日：2014-03-27
申请号：PCT/US2013/055804
申请日：2013-08-20
申请人： GENERAL ELECTRIC COMPANY
发明人： MACHNAIM, Joseph , KEITH, Brian, David , CARSON, Scott, Michael
IPC分类号： F01D25/30 , F01D9/02
CPC分类号： F02K3/065 , B23P11/00 , F01D9/02 , F04D29/547 , Y10T29/49323
摘要： A transition duct (300) for use in a turbine engine (10) is provided. The transition duct (300) includes a radially inner wall (304) and a radially outer wall (208) positioned about the radially inner wall (304) defining a flow passage (306) therebetween. The radially outer wall (208) extends and is contoured from an upstream end (310) to a downstream end (320) of the transition duct (300). As such, the slope of the radially outer wall (208) increases from the upstream end (310) to a predetermined axial location (308) and decreases from the predetermined axial location (308) to the downstream end (320). A turbine assembly comprising such a transition duct (300) between its high pressure turbine (18) and its low pressure turbine (20). A corresponding method of assembling a transition duct (300) for use in a turbine assembly.
摘要翻译：提供一种用于涡轮发动机（10）的过渡管道（300）。过渡管道（300）包括径向内壁（304）和围绕径向内壁（304）定位在其间的流动通道（306）的径向外壁（208）。径向外壁（208）从过渡管道（300）的上游端（310）延伸到下游端（320）。这样，径向外壁（208）的斜面从上游端（310）增加到预定的轴向位置（308），并从预定的轴向位置（308）减小到下游端（320）。一种涡轮组件，包括在其高压涡轮机（18）和其低压涡轮机（20）之间的这种过渡管道（300）。组装用于涡轮组件的过渡管道（300）的相应方法。

3. 发明申请

WO2014007880A3 REVERSE CORE GEAR TURBOFAN 审中-公开
标题翻译：反转核心齿轮涡轮机
公开(公告)号：WO2014007880A3
公开(公告)日：2014-03-20
申请号：PCT/US2013033776
申请日：2013-03-26
申请人： UNITED TECHNOLOGIES CORP
发明人： KUPRATIS DANIEL BERNARD , MOON FRANCIS R
IPC分类号： F02C7/36 , F02C3/067 , F02K3/072
CPC分类号： F02C6/02 , F01D17/141 , F02C3/05 , F02C3/10 , F02C3/107 , F02C3/13 , F02C3/145 , F02C7/36 , F02C9/18 , F02K3/06 , F02K3/065 , F02K3/075 , F05D2220/32 , F05D2220/323 , F05D2250/36 , F05D2260/4023 , F05D2260/4031 , F05D2270/053
摘要： A gas turbine engine has a fan at an axially outer location. The fan rotates about an axis of rotation. The fan delivers air into an outer bypass duct, and across a booster fan positioned radially inwardly of the outer bypass duct. The booster fan delivers air into a radially middle duct, and across a cold turbine into a radially inner core duct being directed into a compressor. From the compressor, air flows axially in a direction back toward the fan through a combustor section, and across an exhaust of the turbine section as directed into the middle duct. A gear reduction drives the fan from a fan drive turbine section. A method is also disclosed.
摘要翻译：燃气涡轮发动机在轴向外部位置具有风扇。风扇绕旋转轴旋转。风扇将空气输送到外部旁路管道中，并且跨过位于外部旁路管道的径向内侧的增压风扇。增压风扇将空气输送到径向中间的管道中，并且将冷却涡轮机转入径向内部的芯管道，将其导入压缩机。从压缩机，空气沿着朝向风扇的方向通过燃烧器部分轴向流动，并且沿着涡轮机部分的排气指向中间管道。齿轮减速器从风扇驱动涡轮机部分驱动风扇。还公开了一种方法。

4. 发明申请

WO2005049423A2 COAXIAL PROPULSION SYSTEMS WITH FLOW MODIFICATION ELEMENT 审中-公开
标题翻译：同轴推进系统与流量修正元件
公开(公告)号：WO2005049423A2
公开(公告)日：2005-06-02
申请号：PCT/CA2004/001927
申请日：2004-11-18
申请人： DISTRIBUTED THERMAL SYSTEMS LTD. , HARRISON, Howard, R.
发明人： HARRISON, Howard, R.
IPC分类号： B64D
CPC分类号： B64C11/001 , B64C11/48 , F02K3/04 , F02K3/065
摘要： A coaxial propulsion system has a primary propeller, a flow control element to reduce swirl, and a secondary propeller, mounted in series configuration. A connecting shroud directs the combined thrust. Said primary propeller and said secondary propeller may be connected to the same engine, or independent engines for greater reliability and performance. A coaxial jet fan system has a primary fan, a flow control element to reduce swirl, and a secondary fan, mounted in a series configuration. A connecting shroud directs the combined bypass and jet thrust. Further, a secondary shroud provides a primary bypass and a secondary bypass thrust, thereby establishing a greater level of control over the bypass ratio and engine efficiency.
摘要翻译：同轴推进系统具有初级螺旋桨，减少涡流的流量控制元件和安装成串联配置的次级螺旋桨。连接罩导向组合的推力。所述主推进器和所述次级螺旋桨可以连接到相同的发动机或独立的发动机以获得更高的可靠性和性能。同轴喷射风扇系统具有主风扇，减少涡流的流量控制元件和以串联配置安装的次风扇。连接罩指导组合的旁路和喷射推力。此外，次级护罩提供初级旁路和次级旁路推力，从而建立对旁路比和发动机效率的更高水平的控制。

5. 发明申请

WO2013012316A1 TURBOFAN ENGINE WITH CONVERGENT - DIVERGENT EXHAUST NOZZLE 审中-公开
标题翻译： TURBOFAN发动机具有融合 - 多样的排气喷嘴
公开(公告)号：WO2013012316A1
公开(公告)日：2013-01-24
申请号：PCT/NL2012/000049
申请日：2012-07-13
申请人： LEEP, Cor
发明人： LEEP, Cor
IPC分类号： F02K1/36 , F02K3/065
CPC分类号： F02K1/28 , F02K1/36 , F02K3/065 , F05D2250/323 , F05D2250/324 , F05D2260/601
摘要： With the speedy and hot airplane turbojet exhaust gases a lot of energy is blown away and wasted nowadays. By this invention a venturi (35) and a diverging duct (14) transform this exhaust energy into a useful and strong low pressure gas stream that sucks outside air through a fan (3) and a bypass (9,10,11) outside the original turbojet engine. (here called core engine). Thus the fan (3) is propelled and drives the central shaft (2 ) of the core engine (4). Now the turbine (7) in the rear of the core engine (4) can deliver less energy to the central shaft (21) for maintaining the right rotation. Likewise turbine (7) can absorb less energy out of the hot and speedy gases inside the core engine. A bigger part of this energy is available for creating thrust now. That is the major profit of this new invention.
摘要翻译：随着快速和热的飞机涡轮喷气式废气，现在大量的能量被吹走和浪费。通过本发明，文丘里管（35）和发散管（14）将这种排气能量转化成有用且强劲的低压气流，其通过外部的风扇（3）和旁路（9,10,11）吸入外部空气。原始涡轮喷气发动机。（这里称为核心引擎）。因此，风扇（3）被推进并驱动核心发动机（4）的中心轴（2）。现在，核心发动机（4）后部的涡轮机（7）可以向中心轴（21）输送更少的能量以维持正确的旋转。同样，涡轮机（7）可以从核心发动机内的热和快速气体中吸收更少的能量。这种能量的较大部分现在可用于创建推力。这是这项新发明的主要利润。

6. 发明申请

WO2005049423A3 COAXIAL PROPULSION SYSTEMS WITH FLOW MODIFICATION ELEMENT 审中-公开
标题翻译：带流量改变元件的同轴推进系统
公开(公告)号：WO2005049423A3
公开(公告)日：2005-07-21
申请号：PCT/CA2004001927
申请日：2004-11-18
申请人： DISTRIBUTED THERMAL SYSTEMS LT , HARRISON HOWARD R
发明人： HARRISON HOWARD R
IPC分类号： B64C11/00 , B64C11/46 , B64C11/48 , B64D20060101 , F02K3/04 , F02K3/065
CPC分类号： B64C11/001 , B64C11/48 , F02K3/04 , F02K3/065
摘要： A coaxial propulsion system has a primary propeller, a flow control element to reduce swirl, and a secondary propeller, mounted in series configuration. A connecting shroud directs the combined thrust. Said primary propeller and said secondary propeller may be connected to the same engine, or independent engines for greater reliability and performance. A coaxial jet fan system has a primary fan, a flow control element to reduce swirl, and a secondary fan, mounted in a series configuration. A connecting shroud directs the combined bypass and jet thrust. Further, a secondary shroud provides a primary bypass and a secondary bypass thrust, thereby establishing a greater level of control over the bypass ratio and engine efficiency.
摘要翻译：同轴推进系统具有主螺旋桨，用于减少涡流的流量控制元件以及以串联配置安装的辅助螺旋桨。一个连接的导流罩引导组合推力。所述主螺旋桨和所述辅助螺旋桨可以连接到相同的发动机或独立的发动机以获得更高的可靠性和性能。同轴射流风机系统具有主风机，用于减少涡流的流量控制元件以及以串联配置安装的次级风机。一个连接护罩指导组合的旁路和喷射推力。此外，二级护罩提供了一级旁路和二级旁路推力，从而对旁路比和发动机效率建立了更高水平的控制。

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