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1. 发明公开

EP2241721A3 Airfoil with feature against flow separation, corresponding gas turbine engine and operating method 有权转让
标题翻译：与针对流分离元件，相关联的燃气涡轮发动机和操作程序叶片轮廓
公开(公告)号：EP2241721A3
公开(公告)日：2014-06-18
申请号：EP10250340.6
申请日：2010-02-25
申请人： United Technologies Corporation
发明人： Grover, Eric A. , Modesto-Madera, Noel , Praisner, Thomas J. , Jurek, Renee J.
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F05D2240/121 , F05D2240/303 , F05D2250/711
摘要： An example airfoil assembly includes a base (60) having an airfoil (54) projecting radially therefrom. The base (60) extends laterally away from the airfoil (54). The airfoil (54) extends axially from an airfoil leading edge portion (62) to an airfoil trailing edge portion (66). The base (60) has a humped area (74) forward the airfoil leading edge portion (62).

2. 发明公开

EP2484871A3 Turbomachine with a flow path having a circumferentially varying outer periphery 有权转让
标题翻译：在圆周周围的变化Turbomaschinenströmungsweg
公开(公告)号：EP2484871A3
公开(公告)日：2016-03-16
申请号：EP12153837.5
申请日：2012-02-03
申请人： United Technologies Corporation
发明人： Praisner, Thomas J. , Grover, Eric A. , Jurek, Renee J.
IPC分类号： F01D9/02 , F01D25/04
CPC分类号： F01D5/143 , F01D9/041 , F01D25/06 , F05D2220/3215 , F05D2250/184 , F05D2250/70
摘要： A turbomachine includes an annular flow path section (57) between a plurality of radially extending stator blades (64) and a plurality of radially extending rotor blades (66). At least a portion (70) of the flow path section (57) has a circumferentially varying outer periphery.

3. 发明公开

EP2441919A1 Aft loaded airfoil 审中-公开
标题翻译： Hinten belastete Schaufel
公开(公告)号：EP2441919A1
公开(公告)日：2012-04-18
申请号：EP11181843.1
申请日：2011-09-19
申请人： United Technologies Corporation
发明人： Estes, Matthew B. , Jurek, Renee J. , Magge, Shankar S.
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/141
摘要： An example airfoil array includes an airfoil array configured to rotate within a turbomachine at a different rotational speed than a fan within the turbomachine. The airfoil array includes a first airfoil (58) that is circumferentially spaced a distance (98) from an adjacent second airfoil (58a). A ratio of the distance (98) to an axial chord length (82) of the first airfoil (58) is less than 1.3. An uncovered turning angle of the first airfoil (58) is greater than 15 degrees.
摘要翻译：示例性翼型阵列包括翼型阵列，其构造成以与涡轮机内的风扇不同的转速在涡轮机内旋转。翼型阵列包括与邻近的第二翼型件（58a）周向隔开距离（98）的第一翼型件（58）。第一翼型件（58）的距离（98）与轴向弦长（82）的比值小于1.3。第一翼型件（58）的未覆盖的转动角度大于15度。

4. 发明公开

EP2241721A2 Airfoil with feature against flow separation, corresponding gas turbine engine and operating method 有权转让
标题翻译：与针对流分离元件，相关联的燃气涡轮发动机和操作程序叶片轮廓
公开(公告)号：EP2241721A2
公开(公告)日：2010-10-20
申请号：EP10250340.6
申请日：2010-02-25
申请人： United Technologies Corporation
发明人： Grover, Eric A. , Modesto-Madera, Noel , Praisner, Thomas J. , Jurek, Renee J.
IPC分类号： F01D5/14 , F01D5/30
CPC分类号： F01D5/143 , F05D2240/121 , F05D2240/303 , F05D2250/711
摘要： An example airfoil assembly includes a base (60) having an airfoil (54) projecting radially therefrom. The base (60) extends laterally away from the airfoil (54). The airfoil (54) extends axially from an airfoil leading edge portion (62) to an airfoil trailing edge portion (66). The base (60) has a humped area (74) forward the airfoil leading edge portion (62).
摘要翻译：一个例子翼型组件包括基部（60），其具有翼型件（54）从径向那里投射。所述基部（60）延伸尾盘反弹从翼型（54）的距离。该翼型件（54）从轴向延伸到翼型在翼型件后缘部分（66）的前缘部分（62）中去。所述基部（60）具有隆起区域（74）转发所述翼型前缘部分（62）。

5. 发明授权

EP2241721B1 Airfoil assembly, corresponding gas turbine engine assembly and method of influencing flow in a gas turbine engine 有权转让
公开(公告)号：EP2241721B1
公开(公告)日：2019-07-03
申请号：EP10250340.6
申请日：2010-02-25
申请人： United Technologies Corporation
发明人： Grover, Eric A. , Modesto-Madera, Noel , Praisner, Thomas J. , Jurek, Renee J.
IPC分类号： F01D5/14

6. 发明公开

EP2484871A2 Turbomachine with a flow path having a circumferentially varying outer periphery 有权转让
标题翻译： Turbomaschinenströmungswegmit einer sich im UmfangänderndenPeripherie
公开(公告)号：EP2484871A2
公开(公告)日：2012-08-08
申请号：EP12153837.5
申请日：2012-02-03
申请人： United Technologies Corporation
发明人： Praisner, Thomas J. , Grover, Eric A. , Jurek, Renee J.
IPC分类号： F01D9/02 , F01D25/04
CPC分类号： F01D5/143 , F01D9/041 , F01D25/06 , F05D2220/3215 , F05D2250/184 , F05D2250/70
摘要： A turbomachine includes an annular flow path section (57) between a plurality of radially extending stator blades (64) and a plurality of radially extending rotor blades (66). At least a portion (70) of the flow path section (57) has a circumferentially varying outer periphery.
摘要翻译：涡轮机械包括在多个径向延伸的定子叶片（64）和多个径向延伸的转子叶片（66）之间的环形流路部分（57）。流路部（57）的至少一部分（70）具有周向变化的外周。

7. 发明授权

EP2484871B1 TURBOMACHINE WITH A FLOW PATH HAVING A CIRCUMFERENTIALLY VARYING OUTER PERIPHERY AND METHOD 有权转让
公开(公告)号：EP2484871B1
公开(公告)日：2019-05-08
申请号：EP12153837.5
申请日：2012-02-03
申请人： United Technologies Corporation
发明人： Praisner, Thomas J. , Grover, Eric A. , Jurek, Renee J.
IPC分类号： F01D9/02 , F01D25/04

8. 发明公开

EP2383434A3 High pitch-to-chord turbine airfoils 审中-实审转让
标题翻译：涡轮机叶片与涡轮机桨距，以弦长的高比率
公开(公告)号：EP2383434A3
公开(公告)日：2013-06-19
申请号：EP11250416.2
申请日：2011-04-01
申请人： United Technologies Corporation
发明人： Praisner, Thomas J. , Estes, Matthew B. , Jurek, Renee J.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3215 , Y02T50/673
摘要： A low pressure turbine engine component (18) for use in an engine (10), for propelling a vehicle such as an aircraft is formed by a disk portion (20) and a plurality of low pressure turbine blades (21) extending outwardly from the disk portion (20). Each of the low pressure turbine blades (21) has an airfoil portion (25) with an axial chord (31) length and a trailing edge (29). The low pressure turbine blades (21) are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance (35) between the trailing edges (29) of adjacent ones of the low pressure turbine blades (21) and the chord is the axial chord (31) length of the blades (21).

9. 发明公开

EP2383434A2 High pitch-to-chord turbine airfoils 审中-实审转让
标题翻译： Turbinenschaufel mit hohemVerhältnisvon Turbinensteigung zurSehnenlänge
公开(公告)号：EP2383434A2
公开(公告)日：2011-11-02
申请号：EP11250416.2
申请日：2011-04-01
申请人： United Technologies Corporation
发明人： Praisner, Thomas J. , Estes, Matthew B. , Jurek, Renee J.
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F05D2220/3215 , Y02T50/673
摘要： A low pressure turbine engine component (18) for use in an engine (10), for propelling a vehicle such as an aircraft is formed by a disk portion (20) and a plurality of low pressure turbine blades (21) extending outwardly from the disk portion (20). Each of the low pressure turbine blades (21) has an airfoil portion (25) with an axial chord (31) length and a trailing edge (29). The low pressure turbine blades (21) are spaced apart so that there is a pitch-to-chord ratio greater than 1.4, wherein the pitch is a distance (35) between the trailing edges (29) of adjacent ones of the low pressure turbine blades (21) and the chord is the axial chord (31) length of the blades (21).
摘要翻译：用于推进诸如飞行器的车辆的用于发动机（10）的低压涡轮发动机部件（18）由盘部分（20）和多个从所述飞行器向外延伸的多个低压涡轮机叶片（21）形成，盘部分（20）。每个低压涡轮叶片（21）具有具有轴向弦（31）长度和后缘（29）的翼型部分（25）。所述低压涡轮机叶片（21）间隔开，使得所述桨距对弦比大于1.4，其中间距是相邻的低压涡轮机的后缘（29）之间的距离（35）叶片（21）并且弦是叶片（21）的轴向弦（31）长度。

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