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1. 发明授权

US10018122B2 Pressure sensor noise filter prior to surge detection for a gas turbine engine 有权
公开(公告)号：US10018122B2
公开(公告)日：2018-07-10
申请号：US14773838
申请日：2014-01-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Michael Hrach , Andrew Brehm
IPC分类号： G05B13/00 , G05D7/00 , G06F19/00 , F02C9/18 , F02C9/00 , F02C9/28 , F02C9/26 , G05B15/02 , H03H7/01 , G05B9/03
CPC分类号： F02C9/18 , F02C9/00 , F02C9/263 , F02C9/28 , F05D2200/14 , F05D2200/33 , F05D2220/32 , F05D2240/20 , F05D2240/35 , F05D2260/84 , F05D2260/96 , F05D2270/101 , F05D2270/301 , F05D2270/309 , F05D2270/54 , F05D2270/70 , G05B9/03 , G05B15/02 , H03H7/01
摘要： A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of the FADEC channel A and the FADEC channel B to obtain a resultant value; a first comparator function to bound a proper high resultant value from the division function; a second comparator function to bound a proper low resultant value from the division function; and an OR gate in communication with the first comparator and the second comparator such that if an output from either the first comparator function and the second comparator function is true, that one of the FADEC channel A and the FADEC channel B is filtered out for a time period.

2. 发明申请

US20160040604A1 Pressure Sensor Noise Filter Prior to Surge Detection for a Gas Turbine Engine 有权
标题翻译：燃气轮机发动机浪涌检测前的压力传感器噪声滤波器
公开(公告)号：US20160040604A1
公开(公告)日：2016-02-11
申请号：US14773838
申请日：2014-01-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Michael HRACH , Andrew BREHM
IPC分类号： F02C9/18 , G05B15/02 , H03H7/01 , F02C9/26
CPC分类号： F02C9/18 , F02C9/00 , F02C9/263 , F02C9/28 , F05D2200/14 , F05D2200/33 , F05D2220/32 , F05D2240/20 , F05D2240/35 , F05D2260/84 , F05D2260/96 , F05D2270/101 , F05D2270/301 , F05D2270/309 , F05D2270/54 , F05D2270/70 , G05B9/03 , G05B15/02 , H03H7/01
摘要： A filter algorithm for a dual channel electronic engine control system according to one disclosed non-limiting embodiment of the present disclosure includes a division function that divides a measured pressure rate of change of one of a FADEC channel A and FADEC channel B by an average pressure of the FADEC channel A and the FADEC channel B to obtain a resultant value; a first comparator function to bound a proper high resultant value from the division function; a second comparator function to bound a proper low resultant value from the division function; and an OR gate in communication with the first comparator and the second comparator such that if an output from either the first comparator function and the second comparator function is true, that one of the FADEC channel A and the FADEC channel B is filtered out for a time period.
摘要翻译：根据本公开的一个公开的非限制性实施例的用于双通道电子发动机控制系统的滤波器算法包括除法功能，其将测量的FADEC通道A和FADEC通道B之一的压力变化率除以平均压力的FADEC通道A和FADEC通道B以获得结果值; 第一比较器功能，从分割函数中绑定适当的高结果值; 第二比较器功能，用于从分割函数中结合适当的低结果值; 以及与第一比较器和第二比较器通信的或门，使得如果来自第一比较器功能和第二比较器功能的输出为真，则FADEC通道A和FADEC通道B中的一个被滤出以用于时间段。

3. 发明授权

US09938837B2 Gas turbine engine airfoil trailing edge passage and core for making same 有权
公开(公告)号：US09938837B2
公开(公告)日：2018-04-10
申请号：US14390496
申请日：2013-03-12
申请人： United Technologies Corporation
发明人： Jeffrey R. Levine , Jeffrey S. Beattie , Malcolm C. Staddon
IPC分类号： F01D5/18 , B22C9/10
CPC分类号： F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
摘要： An airfoil has a body that includes leading and trailing edges that adjoin pressure and suction sides to provide an exterior airfoil surface. A cooling passage extends in a radial direction from a root to a tip. A trailing edge cooling passage interconnects the cooling passage to the trailing edge. The trailing edge cooling passage includes first and second pedestals of different sizes that are arranged in a repeating pattern with respect to pedestals of the same size and with respect to pedestals of different sizes.

4. 发明授权

US09279331B2 Gas turbine engine airfoil with dirt purge feature and core for making same 有权
标题翻译：带有污垢清除功能的燃气涡轮发动机翼型和制造相同的核心
公开(公告)号：US09279331B2
公开(公告)日：2016-03-08
申请号：US13453137
申请日：2012-04-23
申请人： Jeffrey R. Levine , Jeffrey S. Beattie
发明人： Jeffrey R. Levine , Jeffrey S. Beattie
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
摘要： An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.
摘要翻译：机翼包括一个机身。主体包括邻近压力和吸力侧的前缘和后缘，以提供外部翼型表面。第一和第二冷却通道在径向方向上从根部延伸到尖端。第一冷却通道包括从顶端径向插入的尖端标记通道，并且沿着弦向延伸到穿过后缘的第一端。第二冷却通道包括邻近末端标记通道终止的第二端，并且污物清除通道将第二端与尖端标记通道相互连接。还公开了制造翼型的核心。

5. 发明申请

US20140030066A1 ACTIVE CLEARANCE CONTROL MANIFOLD SYSTEM 有权
标题翻译：主动间隙控制系统
公开(公告)号：US20140030066A1
公开(公告)日：2014-01-30
申请号：US13743818
申请日：2013-01-17
申请人： GENERAL ELECTRIC COMPANY
发明人： Scott Alan Schimmels , Daniel John Fusinato , John Carl Glessner , Dan Nicholas Mirkovich , Robert Proctor
IPC分类号： F01D11/24
CPC分类号： F01D11/24 , F01D25/12 , F01D25/14 , F05D2200/33 , F05D2260/201 , F05D2260/30 , Y02T50/676
摘要： Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.
摘要翻译：公开了用于燃气涡轮发动机的主动间隙控制系统。示例性主动间隙控制系统可以包括大致周向安装的喷射管，其包括多个冲击孔，其被布置成将热控制空气撞击到壳体的间隙控制部件上; 将喷射管基本上刚性地连接到壳体上的刚性安装组件; 和/或滑动安装组件，其将喷射管连接到壳体，同时允许喷射管和壳体在大致平行于发动机轴线的方向上的有限的相对运动。滑动安装件可以连接到刚性安装座的大致轴向前方的壳体。间隔距离与冲击孔直径的比值可以小于约8.弧距与冲击孔直径的比可以小于约15。

6. 发明授权

US07922445B1 Variable inlet guide vane with actuator 失效
标题翻译：可变入口导向叶片带执行机构
公开(公告)号：US07922445B1
公开(公告)日：2011-04-12
申请号：US12558901
申请日：2009-09-14
申请人： William W Pankey , Jack W. Wilson, Jr.
发明人： William W Pankey , Jack W. Wilson, Jr.
IPC分类号： F01B25/02
CPC分类号： F01D17/162 , F01D17/20 , F05D2200/33
摘要： A variable inlet guide vane assembly for a gas turbine engine, where the guide vanes are pivotably connected to a sync ring that is contained within an annular groove within the casing so that leakage through holes in the casing is minimized. The guide vanes include a slider mechanism on one of the ends that will allow for both an axial and a rotational movement of the guide vane pin when the guide vanes pivot about a fixed pin on an opposite end of the guide vanes. a round rotary vane actuator with a height much less than a diameter is mounted outside of the casing and connects to the sync ring through a driving linkage.
摘要翻译：一种用于燃气涡轮发动机的可变入口引导叶片组件，其中导向叶片可枢转地连接到容纳在壳体内的环形槽内的同步环，使得通过壳体中的孔的泄漏最小化。导向叶片包括在其中一个端部上的滑动机构，当导叶绕导向叶片的相对端上的固定销枢转时，该滑块机构将允许导叶销的轴向和旋转运动。具有远小于直径的高度的圆形旋转叶片致动器安装在壳体的外部并通过驱动连杆连接到同步环。

7. 发明申请

US20090274554A1 Fluid flow machine including rotors with small rotor exit angles 有权
标题翻译：流体流动机包括具有小转子出口角的转子
公开(公告)号：US20090274554A1
公开(公告)日：2009-11-05
申请号：US12379789
申请日：2009-02-27
申请人： Volker Guemmer
发明人： Volker Guemmer
IPC分类号： F01D9/04 , F01D5/14
CPC分类号： F01D5/143 , F02C3/067 , F04D29/324 , F05D2200/33 , F05D2240/301 , F05D2240/304 , F05D2250/70 , Y02T50/673
摘要： A fluid flow machine includes at least one rotor blade row designed for high work coefficients, which—in its center section and/or averaged over the blade height—provides for an essentially swirl-free relative outflow. The respective rotor, in its trailing edge area, is essentially orientated in meridional direction, which essentially corresponds to the meridional flow direction.
摘要翻译：流体流动机器包括设计用于高工作系数的至少一个转子叶片排，其中心部分和/或在叶片高度上平均 - 提供基本上无漩涡的相对流出。相应的转子在其后缘区域中基本上在子午线方向上定向，其基本上对应于子午线流动方向。

8. 发明申请

US20180179898A1 NOZZLE SECTOR FOR A TURBINE ENGINE WITH DIFFERENTIALLY COOLED BLADES 审中-公开
公开(公告)号：US20180179898A1
公开(公告)日：2018-06-28
申请号：US15759316
申请日：2016-09-15
申请人： SAFRAN AIRCRAFT ENGINES
发明人： Olivier Jean Daniel BAUMAS , Anne-Marie ARRAITZ , Anthony Pierre BEGUIN , Pragash DOUGLAS
IPC分类号： F01D5/18 , F01D9/04
CPC分类号： F01D5/186 , F01D9/041 , F05D2200/33 , F05D2240/128 , F05D2260/202 , Y02T50/676
摘要： A nozzle sector for a turbine engine. The nozzle sector includes a radially outer platform, a radially inner platform, a first end blade, a second end blade and at least one first central blade between the end blades in a circumferential direction of the platforms. The blades extend radially between the platforms in the direction of the span of said blades. The sector includes means for cooling the blades, configured to cool each of the blades by circulating cooling air over same. The cooling means are configured to cool the one or more central blades more than at least one of the end blades.

9. 发明授权

US09341074B2 Active clearance control manifold system 有权
标题翻译：主动间隙控制歧管系统
公开(公告)号：US09341074B2
公开(公告)日：2016-05-17
申请号：US13743818
申请日：2013-01-17
申请人： General Electric Company
发明人： Scott Alan Schimmels , Daniel John Fusinato , John Carl Glessner , Dan Nicholas Mirkovich , Robert Proctor
IPC分类号： F01D11/24 , F01D25/12 , F01D25/14
CPC分类号： F01D11/24 , F01D25/12 , F01D25/14 , F05D2200/33 , F05D2260/201 , F05D2260/30 , Y02T50/676
摘要： Active clearance control systems for gas turbine engines are disclosed. An example active clearance control system may include a generally circumferentially mounted spray tube comprising a plurality of impingement holes arranged to impinge thermal control air on a clearance control component of a case; a rigid mounting assembly substantially rigidly coupling the spray tube to the case; and/or a sliding mounting assembly coupling the spray tube to the case while permitting limited relative movement between the spray tube and the case in a direction generally parallel with an engine axis. The sliding mount may be coupled to the case generally axially forward of the rigid mount. A ratio of the stand-off distance to the impingement hole diameter may be less than about 8. A ratio of the arc spacing to the impingement hole diameter may be less than about 15.
摘要翻译：公开了用于燃气涡轮发动机的主动间隙控制系统。示例性主动间隙控制系统可以包括大致周向安装的喷射管，其包括多个冲击孔，其被布置成将热控制空气撞击到壳体的间隙控制部件上; 将喷射管基本上刚性地连接到壳体上的刚性安装组件; 和/或滑动安装组件，其将喷射管连接到壳体，同时允许喷射管和壳体在大致平行于发动机轴线的方向上的有限的相对运动。滑动安装件可以连接到刚性安装座的大致轴向前方的壳体。间隔距离与冲击孔直径的比值可以小于约8.弧距与冲击孔直径的比可以小于约15。

10. 发明申请

US20150361803A1 TURBOMACHINE ROTOR BLADE, TURBOMACHINE ROTOR DISC, TURBOMACHINE ROTOR, AND GAS TURBINE ENGINE WITH DIFFERENT ROOT AND SLOT CONTACT FACE ANGLES 有权
标题翻译：涡轮转子叶片，涡轮转子盘，涡轮转子和具有不同根和油槽接触面角度的气体涡轮发动机
公开(公告)号：US20150361803A1
公开(公告)日：2015-12-17
申请号：US14763756
申请日：2014-02-03
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： Richard Bluck , David Butler , David Overton
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D5/02 , F01D5/30 , F05D2200/33 , F05D2250/38
摘要： A turbomachine rotor blade has a firtree shaped root, to be secured in a rotor disc rotatable around a rotor axis. In a plane perpendicular to the rotor axis, the root has a first, second, and third root lobe with a first, second, and third root contact face. Each of the first, second, and third root contact face is angled relative to a radial root bottom axis with a first, second, and third root angle, respectively. The first root angle is smaller than the second and the second root angle is substantially equal to the third. A turbomachine rotor disc has a firtree shaped slot having a first, second, and third slot angle, the first slot angle being smaller than the second and the second slot angle being substantially equal to the third. A gas turbine engine has the turbomachine rotor herein.
摘要翻译：涡轮机转子叶片具有圆形根部，固定在可围绕转子轴线旋转的转子盘中。在垂直于转子轴线的平面中，根部具有带有第一，第二和第三根接触面的第一，第二和第三根叶。第一，第二和第三根接触面中的每一个分别相对于径向根底部轴线成角度，具有第一，第二和第三根角度。第一根角小于第二根角，而第二根角基本上等于第三根角。涡轮机转子盘具有具有第一，第二和第三槽缝角度的空心形槽，第一槽角小于第二槽角度，第二槽角度基本上等于第三槽。燃气涡轮发动机在这里具有涡轮机转子。

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