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1. 发明申请

WO2015088833A1 SYSTEMS AND METHODS CONTROLLING FAN PRESSURE RATIOS 审中-公开
标题翻译：控制风扇压力比的系统和方法
公开(公告)号：WO2015088833A1
公开(公告)日：2015-06-18
申请号：PCT/US2014/068193
申请日：2014-12-02
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KUPRATIS, Daniel B.
IPC分类号： F02K3/075
CPC分类号： F02K3/075 , F01D9/04 , F01D17/105 , F01D17/162 , F02K3/077 , F05D2220/36 , F05D2240/128 , F05D2240/55
摘要： A system for varying the fan pressure ratio of a gas turbine engine is provided. The system may comprise a stator having a variable area component. The variable area component may be configured to adjust the inlet area on the main fan bypass. In this regard, the variable area component may be configured to restrict flow to the main fan bypass and/or divert flow to the core flow from a fan section of a gas turbine engine.
摘要翻译：提供了一种用于改变燃气涡轮发动机的风扇压力比的系统。该系统可以包括具有可变面积分量的定子。可变区域组件可以被配置为调节主风扇旁路上的入口区域。在这方面，可变区域部件可以被配置为限制到主风扇旁路的流动和/或从燃气涡轮发动机的风扇部分转移到核心流的流动。

2. 发明申请

WO2015030858A3 GEARED ANNULAR AIRFLOW ACTUATION SYSTEM FOR VARIABLE CYCLE GAS TURBINE ENGINES 审中-公开
标题翻译：用于可变循环气体涡轮发动机的齿轮式气流启动系统
公开(公告)号：WO2015030858A3
公开(公告)日：2015-05-07
申请号：PCT/US2014014847
申请日：2014-02-05
申请人： UNITED TECHNOLOGIES CORP
发明人： IZQUIERDO FELIX
IPC分类号： F02C7/057 , F02C7/042
CPC分类号： F01D17/162 , F02C9/20 , F02K3/075 , F02K3/077 , F05D2240/12 , F05D2250/44 , F05D2260/4031 , F05D2260/53 , F05D2260/79
摘要： An annular airflow control system for a gas turbine engine includes a sync ring rotatable to move the multiple of contra-rotatable variable vanes through a respective multiple of geared interfaces to throttle an airflow through the multiple of contra-rotatable variable vanes.
摘要翻译：用于燃气涡轮发动机的环形气流控制系统包括可旋转的同步环，以通过相应的多个齿轮传动接口移动多个可反转的可变叶片，以节流通过多个可逆转可变叶片的气流。

3. 发明申请

WO2014163887A1 TURBINE ENGINE INCLUDING BALANCED LOW PRESSURE STAGE COUNT 审中-公开
标题翻译：涡轮发动机包括平衡低压级数
公开(公告)号：WO2014163887A1
公开(公告)日：2014-10-09
申请号：PCT/US2014/018606
申请日：2014-02-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KUPRATIS, Daniel Bernard , HASEL, Karl L.
IPC分类号： F02C3/107 , F02C3/04
CPC分类号： F02K3/075 , F05D2220/3213 , F05D2220/3218
摘要： A turbine engine includes at least a compressor section and a turbine section, each having at least a first and second portion. A ratio of turbine section second portion stages to compressor section second portion stages is less than or equal to 1.
摘要翻译：涡轮发动机至少包括压缩机部分和涡轮机部分，每个部分至少具有第一和第二部分。涡轮部分第二部分级与压缩机部分第二部分级的比例小于或等于1。

4. 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。

5. 发明申请

WO2014105237A2 GEARED TURBOFAN PRIMARY AND SECONDARY NOZZLE INTEGRATION GEOMETRY 审中-公开
标题翻译：齿轮涡轮机主要和二次喷嘴积分几何
公开(公告)号：WO2014105237A2
公开(公告)日：2014-07-03
申请号：PCT/US2013/061927
申请日：2013-09-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： KUPRATIS, Daniel Bernard , KOHLENBERG, Gregory A.
CPC分类号： F02K3/075 , F01D21/045 , F02C7/32 , F02K1/04 , F05D2260/30 , F05D2260/311 , Y10T29/49245
摘要： A disclosed example geared turbofan engine includes a fan section including a plurality of fan blades rotatable about an axis and a core engine section defined about an engine axis. The core engine section includes a primary nozzle including a primary outer diameter at a primary nozzle trailing edge and a primary maximum inner diameter forward of the primary trailing edge. A bypass passage a secondary nozzle that includes an outer diameter at a secondary nozzle trailing edge and a secondary maximum inner diameter forward of the secondary trailing edge. A ratio between the maximum inner diameter of the primary nozzle and an outer diameter at the trailing edge of the primary nozzle and a ratio between the maximum inner diameter of the secondary trailing edge and the outer diameter at the trailing edge of the secondary nozzle are both less than about 0.700.
摘要翻译：所公开的示例性齿轮涡扇发动机包括：风扇部分，其包括可围绕轴线旋转的多个风扇叶片和围绕发动机轴线限定的核心发动机部分。核心引擎部分包括主喷嘴，主喷嘴包括主喷嘴后缘处的主外径和主后缘的主要最大内径。旁通通道，二次喷嘴，其包括次级喷嘴后缘处的外径和次级后缘的次级最大内径。主喷嘴的最大内径和主喷嘴后缘的外径之间的比率以及次级后缘的最大内径与次喷嘴后缘的外径之间的比率都是小于约0.700。

6. 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。

7. 发明申请

WO2013154638A1 GAS TURBINE ENGINE WITH COMPRESSOR INLET GUIDE VANE POSITIONED FOR STARTING 审中-公开
标题翻译：气体涡轮发动机，带有压缩机入口导向件，用于起动
公开(公告)号：WO2013154638A1
公开(公告)日：2013-10-17
申请号：PCT/US2013/021799
申请日：2013-01-17
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： WEHMEIER, Eric, J.
IPC分类号： F02C7/22
CPC分类号： F02C3/13 , F01D19/00 , F02C7/262 , F02C9/20 , F02K1/1207 , F02K3/06 , F02K3/075 , F05D2260/85 , F05D2270/092
摘要： A gas turbine engine includes a variable inlet guide vane positioned forwardly of a low pressure compressor. The angle of the inlet guide vane is controlled at startup to increase airflow into the compressor. This is particularly useful when the gas turbine engine is being restarted while an associated aircraft is in the air, and is relied upon to increase windmill speed of the compressor and turbine rotors. A method and variable inlet vane are also disclosed.
摘要翻译：燃气涡轮发动机包括位于低压压缩机前方的可变入口引导叶片。入口导叶的角度在启动时被控制，以增加进入压缩机的气流。当燃气涡轮发动机在相关联的飞行器处于空气中时重新启动，并且依赖于增加压缩机和涡轮转子的风车速度时，这是特别有用的。还公开了一种方法和可变入口叶片。

8. 发明申请

WO2013095765A1 GAS TURBINE DUCT BLOCKER WITH ROTATABLE VANE SEGMENTS 审中-公开
标题翻译：具有可旋转风扇段的气体涡轮阻塞器
公开(公告)号：WO2013095765A1
公开(公告)日：2013-06-27
申请号：PCT/US2012/061332
申请日：2012-10-22
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： JONES, James , BURSEY, JR., Roger W. , MAUER, John H. , HAWKE, Larry B. , CLAWSON, Ronald T. , OLECH, Andrew P.
IPC分类号： F01D17/14 , F02C9/18 , F02K1/82 , F02K3/075
CPC分类号： F01D17/141 , F02C9/18 , F02K1/822 , F02K3/075 , F05D2240/50 , F05D2250/411 , Y02T50/675
摘要： A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first vane segments that extend radially between an inner rotor platform and an outer rotor platform, and a plurality of first flow apertures that extend axially through the duct blocker rotor. Each first flow aperture also extends circumferentially between respective adjacent first vane segments. The duct blocker stator includes a plurality of second vane segments that extend radially between an inner stator platform and an outer stator platform, and a plurality of second flow apertures that extend axially through the duct blocker stator. Each second flow aperture also extends circumferentially between respective adjacent second vane segments. The first vane segments move circumferentially relative to the second vane segments to regulate fluid flowing between the first flow apertures and the second flow apertures.
摘要翻译：用于燃气涡轮发动机的旋转管道阻塞器包括管道阻塞转子和管道阻塞器定子。导管阻塞器转子包括多个第一叶片段，其在内转子平台和外转子平台之间径向延伸，以及多个第一流动孔，其轴向延伸穿过管道阻塞转子。每个第一流动孔径在相邻的相邻的第一叶片段之间周向地延伸。管道阻塞器定子包括在内部定子平台和外部定子平台之间径向延伸的多个第二叶片段，以及沿轴向延伸穿过管道阻塞定子的多个第二流动孔。每个第二流动孔也在相邻的相邻的第二叶片段之间周向延伸。第一叶片段相对于第二叶片段周向运动，以调节在第一流动孔和第二流动孔之间流动的流体。

9. 发明申请

WO2013095764A1 GAS TURBINE DUCT BLOCKER THAT INCLUDES A DUCT BLOCKER ROTOR WITH A PLURALITY OF ROLLER ELEMENTS 审中-公开
标题翻译：气体涡轮阻塞器包括具有多个滚子元件的导管阻塞器
公开(公告)号：WO2013095764A1
公开(公告)日：2013-06-27
申请号：PCT/US2012/061326
申请日：2012-10-22
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： JONES, James , MAURER, John H. , WARD, Eric J. , BURSEY, JR., Roger W.
IPC分类号： F01D17/14 , F02C9/18 , F02K1/82 , F02K3/075
CPC分类号： F01D17/141 , F02C9/18 , F02K1/822 , F02K3/075 , F05D2240/50 , F05D2250/411 , Y02T50/675
摘要： A rotational duct blocker for a gas turbine engine includes a duct blocker rotor and a duct blocker stator. The duct blocker rotor includes a plurality of first vane segments that extend radially between an inner rotor platform and an outer rotor platform, and a plurality of first flow apertures that extend axially through the duct blocker rotor. Each first flow aperture also extends circumferentially between respective adjacent first vane segments. The duct blocker stator includes a plurality of second vane segments that extend radially between an inner stator platform and an outer stator platform, and a plurality of second flow apertures that extend axially through the duct blocker stator. Each second flow aperture also extends circumferentially between respective adjacent second vane segments. The first vane segments move circumferentially relative to the second vane segments to regulate fluid flowing between the first flow apertures and the second flow apertures.
摘要翻译：用于燃气涡轮发动机的旋转管道阻塞器包括管道阻塞转子和管道阻塞器定子。导管阻塞器转子包括多个第一叶片段，其在内转子平台和外转子平台之间径向延伸，以及多个第一流动孔，其轴向延伸穿过管道阻塞转子。每个第一流动孔口也在各个相邻的第一叶片段之间周向延伸。所述管道阻塞器定子包括在内部定子平台和外部定子平台之间径向延伸的多个第二叶片段，以及沿轴向延伸穿过管道阻塞定子的多个第二流动孔。每个第二流动孔口也在相应的相邻的第二叶片段之间周向延伸。第一叶片段相对于第二叶片段周向运动，以调节在第一流动孔和第二流动孔之间流动的流体。

10. 发明申请

WO2012123681A1 TURBOMACHINE A HELICE(S) POUR AERONEF, A TUYERE MOBILE 审中-公开
标题翻译：具有风扇的涡轮机，用于具有移动喷嘴喷嘴的飞机
公开(公告)号：WO2012123681A1
公开(公告)日：2012-09-20
申请号：PCT/FR2012/050537
申请日：2012-03-14
申请人： SNECMA , DRON, Sébastien , TANTOT, Nicolas, Jérôme, Jean
发明人： DRON, Sébastien , TANTOT, Nicolas, Jérôme, Jean
IPC分类号： F02K1/09 , F02K3/02 , F02K3/072 , B64C11/48 , F02K3/075
CPC分类号： F01D9/02 , B64D2027/005 , F02K1/09 , F02K1/763 , F02K3/025 , F02K3/072 , F02K3/075 , F05D2300/505 , Y02T50/66
摘要： Turbomachine à hélice(s) pour aéronef, à tuyère mobile. -La turbomachine comporte au moins une turbine (5) entraînant en rotation l'hélice (3, 4), et une tuyère (8) prolongeant coaxialement ladite turbine en ménageant, avec un cône de sortie (10) terminant la turbine, un passage (11) à section transversale annulaire pour les gaz de combustion qui traversent la turbine. Avantageusement, la tuyère (8) est montée mobile entre deux positions extrêmes pour lesquelles, sous l'action de moyens de commande (12), la section transversale annulaire du passage (11) des gazest respectivement minimale ou maximale, permettant de faire varier ladite section selon les phases fonctionnelles de l'aéronef et de répartir la poussée entre l'hélice et la tuyère.
摘要翻译：涡轮机与飞机的风扇，移动喷嘴。所述涡轮机包括驱动所述风扇（3,4）旋转的至少一个涡轮机（5）和与所述涡轮机同轴延伸的喷射喷嘴（8），并且利用终止涡轮机的出口锥体（10）产生通道（11），其通过涡轮机的燃烧气体的环形横截面。有利地，喷射喷嘴（8）被安装成使得其可以在控制装置（12）的作用下在两个极限位置之间移动，用于气体的通道（11）的环形截面分别在其最小值或最大限度地，使得可以根据飞行器的操作阶段来改变所述横截面并且分配风扇和喷嘴之间的推力。

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