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. 发明公开

EP2809929A1 HIGH TURNING FAN EXIT STATOR 有权转让
标题翻译：高转动风扇退出定子
公开(公告)号：EP2809929A1
公开(公告)日：2014-12-10
申请号：EP13778582.0
申请日：2013-01-28
申请人： United Technologies Corporation
发明人： BRILLIANT, Lisa I. , ROSE, Becky E. , DONG, Yuan , BALAMUCKI, Stanley J.
IPC分类号： F02G1/00
CPC分类号： F01D5/141 , F02C7/36 , F02K3/072 , F05D2220/36 , Y02T50/673
摘要： A turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section that rotates about a longitudinal axis and a compressor section. The turbine engine also includes a fan exit stator located between the fan section and the compressor section, the fan exit stator including an airfoil. The airfoil defines an entrance angle with respect to a leading edge of the airfoil and a line parallel to the longitudinal axis, and the airfoil defines an exit angle with respect to a trailing edge of the airfoil and a line parallel to the longitudinal axis. A difference between the entrance angle and the exit angle is between about 45° and about 65°. The turbine engine also includes a turbine section, and a portion of the compressor section is driven by a portion of the turbine section.
摘要翻译：除了别的之外，根据本公开的示例性方面的涡轮发动机包括围绕纵向轴线旋转的风扇部分和压缩机部分。涡轮发动机还包括位于风扇部分和压缩机部分之间的风扇出口定子，风扇出口定子包括翼型。翼型限定相对于翼型的前缘和平行于纵向轴线的线的入口角，并且翼型件限定相对于翼型件的后缘和平行于纵向轴线的线的出口角。入口角度和出口角度之间的差异在大约45°和大约65°之间。涡轮发动机还包括涡轮部分，并且压缩机部分的一部分由涡轮部分的一部分驱动。

2. 发明授权

EP3239459B1 EFFICIENT LOW PRESSURE RATIO PROPULSOR STAGE FOR GAS TURBINE ENGINES 有权转让
公开(公告)号：EP3239459B1
公开(公告)日：2019-01-02
申请号：EP17168737.9
申请日：2017-04-28
申请人： United Technologies Corporation
发明人： ROSE, Becky E.
IPC分类号： F01D5/14 , F01D9/04

3. 发明公开

EP3052789A1 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
标题翻译：低压比风扇发动机在进风口和风扇尺寸之间具有一定的尺寸关系
公开(公告)号：EP3052789A1
公开(公告)日：2016-08-10
申请号：EP14850031.7
申请日：2014-09-18
申请人： United Technologies Corporation
发明人： LORD, Wesley K. , MALECKI, Robert E. , QIU, Yuan , ROSE, Becky E. , GILSON, Jonathan
IPC分类号： F02C7/36
CPC分类号： F02K3/068 , F01D25/24 , F02C7/04 , F05D2220/36 , F05D2240/303 , F05D2260/40311 , F05D2260/96 , Y02T50/671
摘要： According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan section including a fan, the fan including a plurality of fan blades, a diameter of the fan having a dimension D that is based on a dimension of the fan blades, each fan blade having a leading edge, and a forward most portion on the leading edges of the fan blades in a first reference plane, a turbine section including a high pressure turbine and a low pressure turbine, the low pressure turbine driving the fan, a nacelle including an inlet portion forward of the fan, a forward edge on the inlet portion in a second reference plane, and a length of the inlet portion having a dimension L measured along an engine axis between the first reference plane and the second reference plane. A dimensional relationship of L/D is no more than 0.45.
摘要翻译：根据一个示例性实施例，燃气涡轮发动机组件尤其包括具有多个风扇叶片的风扇。风扇的直径具有基于风扇叶片的尺寸的尺寸D. 每个风扇叶片都有一个前缘。入口部分位于风扇的前方。入口部分的长度在至少一些风扇叶片的前缘的位置与入口部分上的前缘之间具有尺寸L. L / D的尺寸关系在约0.2和约0.45之间。

4. 发明公开

EP2935788A1 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 有权转让
标题翻译：与小的压力比的风扇马达和之间的入口和风扇尺寸的尺寸关系
公开(公告)号：EP2935788A1
公开(公告)日：2015-10-28
申请号：EP13864565.0
申请日：2013-12-18
申请人： United Technologies Corporation
发明人： LORD, Wesley K. , MALECKI, Robert E. , QIU, Yuan J. , ROSE, Becky E. , GILSON, Jonathan
IPC分类号： F01D5/14 , F01D5/12 , F02C7/00
CPC分类号： F01D25/24 , F01D5/02 , F01D5/141 , F01D15/12 , F01D17/105 , F02C7/04 , F02K3/06 , F05D2220/32 , F05D2250/00 , F05D2260/40311 , F05D2260/96 , Y02T50/671 , Y02T50/673
摘要： According to an example embodiment, a gas turbine engine assembly includes, among other things, a fan that has a plurality of fan blades. A diameter of the fan has a dimension D that is based on a dimension of the fan blades. Each fan blade has a leading edge. An inlet portion is situated forward of the fan. A length of the inlet portion has a dimension L between a location of the leading edge of at least some of the fan blades and a forward edge on the inlet portion. A dimensional relationship of L/D is between about 0.2 and 0.45.

5. 发明公开

EP2809935A1 COMPRESSOR FLOWPATH 审中-公开
标题翻译：压缩器流动路径
公开(公告)号：EP2809935A1
公开(公告)日：2014-12-10
申请号：EP13775563.3
申请日：2013-01-18
申请人： United Technologies Corporation
发明人： BRILLIANT, Lisa I. , ROSE, Becky E. , DONG, Yuan , BALAMUCKI, Stanley J.
IPC分类号： F02K3/02 , F02K3/00 , F02C9/00
CPC分类号： F04D29/547 , F02K3/04 , F02K3/06 , F04D19/028 , F04D25/045 , F04D29/321 , F04D29/563 , F04D29/682 , F05D2220/3217 , F05D2220/36 , F05D2260/606
摘要： A core flowpath through a low pressure compressor section of a gas turbine engine includes an outer diameter, which has a slope angle relative to an axis defined by the core flowpath. The slope angle is a slope angle that is operable to prevent flow separation of a fluid passing through the core flowpath.

6. 发明授权

EP3052789B1 GEARED TURBOFAN HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 有权
公开(公告)号：EP3052789B1
公开(公告)日：2019-06-19
申请号：EP14850031.7
申请日：2014-09-18
申请人： United Technologies Corporation
发明人： LORD, Wesley K. , MALECKI, Robert E. , QIU, Yuan , ROSE, Becky E. , GILSON, Jonathan
IPC分类号： F02C7/36 , F02C7/04 , F02K3/068

7. 发明公开

EP3156627A1 LOW PRESSURE RATIO FAN ENGINE HAVING A DIMENSIONAL RELATIONSHIP BETWEEN INLET AND FAN SIZE 审中-公开
标题翻译：与小压比之间的入口和风扇尺寸的尺寸关系FAN电厂
公开(公告)号：EP3156627A1
公开(公告)日：2017-04-19
申请号：EP16193884.0
申请日：2016-10-14
申请人： United Technologies Corporation
发明人： LORD, Wesley K. , MALECKI, Robert E. , QIU, Yuan J. , ROSE, Becky E. , GILSON, Jonathan
IPC分类号： F02C3/107 , F02K3/068 , F02C7/045
CPC分类号： F02C3/107 , F02C7/045 , F02K3/068 , F05D2250/00 , F05D2260/96 , Y02T50/671
摘要： A gas turbine engine assembly includes a fan (42) including a plurality of fan blades (92), a diameter of the fan (42) having a dimension D that is based on a dimension of the fan blades (92), each fan blade (92) having a leading edge, a geared architecture (48) configured to drive the fan (42), a turbine section (28) configured to drive the geared architecture (48), a compressor section (24) including a first compressor (44) and a second compressor (52), and an inlet portion (82) forward of the fan (42). A length of the inlet portion (82) has a dimension L between a location of the leading edge of at least some of the fan blades (92) and a forward edge (84) on the inlet portion (82). A dimensional relationship of L/D is between about 0.2 and about 0.45.
摘要翻译：一种燃气涡轮发动机组件包括风扇（42）包括风扇叶片的多个（92），其直径具有尺寸D的风扇（42）的并基于（92）的风扇叶片的尺寸，每个风扇叶片具有前缘，配置为驱动所述风扇（42），被配置为驱动齿轮传动架构（48），一个压缩机部分（24），包括第一压缩机的涡轮段（28）的齿轮传动结构（48）（（92） 44）和第二压缩机（52），和（在入口部82）的风扇（42的正向）。入口部分（82）的长度具有至少一些风扇叶片（92）和前边缘（84）上的入口部分（82）的前缘的位置之间的尺寸L。 L的尺寸关系/ D是约0.2至约12:45之间。

8. 发明公开

EP2809926A2 VARIABLE VANE SCHEDULING BASED ON FLIGHT CONDITIONS FOR INCLEMENT WEATHER 有权转让
标题翻译：翼可调协调根据对恶劣的天气条件飞行
公开(公告)号：EP2809926A2
公开(公告)日：2014-12-10
申请号：EP13743341.3
申请日：2013-01-28
申请人： United Technologies Corporation
发明人： ROSE, Becky E. , BRILLIANT, Lisa I
IPC分类号： F02C9/20
CPC分类号： B64D45/00 , B64D2033/022 , F01D17/162 , F02C7/05 , F02C9/20 , F04D27/0292 , F04D29/563 , F05D2270/114
摘要： A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.

9. 发明公开

EP3239459A1 EFFICIENT LOW PRESSURE RATIO PROPULSOR STAGE FOR GAS TURBINE ENGINES 有权转让
标题翻译：燃气涡轮发动机的高效低压比推进器
公开(公告)号：EP3239459A1
公开(公告)日：2017-11-01
申请号：EP17168737.9
申请日：2017-04-28
申请人： United Technologies Corporation
发明人： ROSE, Becky E.
IPC分类号： F01D5/14 , F01D9/04
CPC分类号： F04D25/024 , F01D5/141 , F01D5/147 , F01D9/041 , F02K3/06 , F04D29/321 , F05B2220/303 , F05B2230/00 , F05D2240/12 , F05D2240/301 , F05D2260/4031 , Y02T50/672 , Y02T50/673
摘要： A propulsor (22) for a gas turbine engine (20) includes a case (15) including a duct (18) disposed along an axis (A) to define a flow path (B). A rotor (60) includes a row (62) of propulsor blades (64) extending in a generally radial direction (R) outwardly from a hub (66), the hub (66) rotatable about the axis (A) such that the propulsor blades (64) deliver airflow into the flow path (B). A row (80) of guide vanes (82) are situated in the flow path (B). At least two of the guide vanes (82) extend in the generally radial direction (R) between inner and outer surfaces (19 A , 19 B ) of the duct (18), extend in a chordwise direction (H) between a first leading edge (84) and a first trailing edge (86) to define a vane chord dimension (VCD) at a first span position of the corresponding guide vane (82), and define a vane circumferential pitch (VCP) at the first span position of the corresponding guide vane (82) and an adjacent one of the guide vanes (82). The row (80) of guide vanes (82) has a vane solidity (VR) defined as VCD/VCP, the vane solidity (VR) being equal to or less than 1.43.
摘要翻译：用于燃气涡轮发动机（20）的推进器（22）包括壳体（15），该壳体包括沿着轴线（A）布置以限定流动路径（B）的管道（18）。转子（60）包括从毂（66）向外大致径向（R）延伸的推进器叶片（64）的排（62），毂（66）可围绕轴线（A）旋转，使得推进器叶片（64）将气流输送到流动路径（B）中。导流叶片（82）的一排（80）位于流动路径（B）中。至少两个导向叶片（82）在导管（18）的内表面和外表面（19A，19B）之间沿大致径向方向（R）延伸，在第一前缘（H）和相应的导向叶片（82）的第一跨度位置处限定叶片弦尺寸（VCD）的第一后缘（86），并且在相应的导叶（82）的第一跨度位置处限定叶片圆周节距（VCP）导向叶片（82）和相邻的一个导向叶片（82）。导向叶片（82）的排（80）具有定义为VCD / VCP的叶片密实度（VR），叶片密实度（VR）等于或小于1.43。

10. 发明公开

EP3054112A1 NOSE CONE ASSEMBLY AND METHOD OF CIRCULATING AIR IN A GAS TURBINE ENGINE 有权转让
标题翻译：在加拿大EINEM GASTURBINENMOTOR的NASENKEGELBAUGRUPPE UND VERFAHREN ZURLUFTFÜHRUNG
公开(公告)号：EP3054112A1
公开(公告)日：2016-08-10
申请号：EP16154872.2
申请日：2016-02-09
申请人： United Technologies Corporation
发明人： SUCIU, Gabriel L. , SNAPE, Nathan , BIFULCO, Anthony R. , ACKERMANN, William K. , ROSE, Becky E. , CHANDLER, Jesse M.
IPC分类号： F01D25/12 , F02C7/04 , F02C7/047 , F02C7/18 , F02C7/32 , F02C7/14
CPC分类号： F02K1/04 , F01D15/08 , F01D25/12 , F01D25/125 , F01D25/14 , F02C7/04 , F02C7/047 , F02C7/057 , F02C7/14 , F02C7/18 , F02C7/185 , F02C7/32 , F05D2220/32 , F05D2260/20 , F05D2260/213
摘要： A nose cone assembly (64) for a gas turbine engine (20) and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone (66) having an aperture (68) and communicating air to an interior space (70) of the nose cone and a discharge member (74) communicating the air out of the nose cone.
摘要翻译：公开了一种用于燃气涡轮发动机（20）的鼻锥组件（64）和在燃气涡轮发动机中循环空气的方法。鼻锥组件包括具有孔（68）并将空气连通到鼻锥的内部空间（70）的鼻锥（66）和将空气从鼻锥传出的排出构件（74）。

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