公开(公告)号：US08126628B2

公开(公告)日：2012-02-28

申请号：US11833596

申请日：2007-08-03

Applicant: John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

Inventor： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

IPC: G06F19/00 ,  G06G7/70

CPC classification number: F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

Abstract translation: 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。

公开(公告)号：US20090037035A1

公开(公告)日：2009-02-05

申请号：US11833596

申请日：2007-08-03

Applicant: John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

Inventor： John Erik Hershey ,  Brock Estel Osborn ,  Donald Lee Gardner ,  Rafael Jose Ruiz ,  William Lee Herron

IPC: G06F17/18 ,  G06F15/18 ,  G06G7/48 ,  G06F17/00

CPC classification number: F01D11/24 ,  F02C9/00 ,  F02C9/26 ,  F02C9/48 ,  F05D2270/305 ,  F05D2270/44 ,  F05D2270/70

Abstract: A method and system adjusts blade tip clearance between rotating aircraft gas turbine engine blade tips and a surrounding shroud in anticipation of and before an engine command that changes an engine rotational speed. The method may include determining when to begin adjusting the tip clearance by expanding or contracting the shroud before the engine command and may be based on monitored aircraft and/or aircraft crew data indicative of the engine. The aircraft and/or aircraft crew data may include communications between aircraft crew and air traffic control authorities or air traffic control surrogates. Determining when to begin adjusting the tip clearance may include using learning algorithms which may use the aircraft gas turbine engine's operating experience and/or operating experience of other jet engines on an aircraft containing the aircraft gas turbine engine and/or on other aircraft.

Abstract translation: 一种方法和系统预期在改变发动机转速的发动机命令之前和之前调整旋转飞机燃气涡轮发动机叶片尖端和周围罩之间的叶片顶端间隙。 该方法可以包括通过在发动机命令之前扩展或收缩护罩来确定何时开始调整顶端间隙，并且可以基于指示发动机的受监视的飞行器和/或飞机机组数据。 飞机和/或飞机机组数据可以包括飞机机组人员和空中交通管制机构或空中交通管制代理人之间的通信。 确定何时开始调整尖端间隙可以包括使用学习算法，其可以使用飞机燃气涡轮发动机在包含飞机燃气涡轮发动机的飞机和/或其它飞行器上的其它喷气发动机的操作经验和/或操作经验。

公开(公告)号：US07597537B2

公开(公告)日：2009-10-06

申请号：US11303688

申请日：2005-12-16

Applicant: Michael Terry Bucaro ,  Rafael Jose Ruiz ,  Robert Joseph Albers ,  Scott Anthony Estridge ,  Roger Francis Wartner

Inventor： Michael Terry Bucaro ,  Rafael Jose Ruiz ,  Robert Joseph Albers ,  Scott Anthony Estridge ,  Roger Francis Wartner

IPC: F03B11/00 ,  F03D11/00

CPC classification number: F01D11/24

Abstract: A gas turbine engine thermal control apparatus includes at least one annular spray tube having spray holes oriented to impinge thermal control air onto a fillet between an outer casing and a forward thermal control ring and, in a more particular embodiment, into a center of the fillet. The apparatus may include an annular segmented stator shroud attached to the outer casing and circumscribing radial outer blade tips of turbine blades of a turbine rotor. A thermal air distribution manifold encircling a portion of the outer casing includes an annular supply tube connected in fluid supply relationship to plenums of header assemblies. The annular spray tube is connected to at least one of the plenums and may be elongated radially inwardly and axially. Baffles attached to radially outwardly facing surfaces of the panels may be contoured to form exhaust passages having exhaust passage inlets and outlets between the baffles and the panels.

Abstract translation: 燃气涡轮发动机热控制装置包括至少一个具有喷射孔的环形喷射管，所述喷射孔定向成将热控制空气冲击到外壳和向前热控制环之间的圆角上，并且在更具体的实施例中，进入圆角的中心 。 该装置可以包括附接到外壳并且包围涡轮转子的涡轮叶片的径向外叶片尖端的环形分段定子罩。 环绕外壳的一部分的热空气分配歧管包括以流体供应关系连接到集管组件的气室的环形供应管。 环形喷射管连接到至少一个通气室，并且可以径向向内和轴向地伸长。 附接到面板的径向向外表面的挡板可以被轮廓化以形成排气通道，其具有在挡板和面板之间的排气通道入口和出口。

公开(公告)号：US07891938B2

公开(公告)日：2011-02-22

申请号：US11688354

申请日：2007-03-20

Applicant: William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

Inventor： William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

IPC: F01B25/26

CPC classification number: G01B7/14 ,  F01D5/20 ,  F01D21/003 ,  G01B21/16

Abstract: A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being operable to measure blade tip clearances between radially outer turbine blade tips and an annular stator shroud circumscribing the blade tips. The blade tips may be squealer tips and the sensors operable to measure the distances between the sensors and tops of squealer tip walls and outwardly facing walls within cavities of the squealer tips. The probe may be operably connected to a controller for sending signals to the controller indicating the first and second distances for controlling an air valve used for active clearance control. Two or more of the probe may be used to determine rotor centerline offset.

Abstract translation: 多传感器间隙探头，其至少纵向和横向间隔开的第一和第二传感器可操作以分别测量传感器和纵向间隔开的旋转转子之间的第一和第二距离。 传感器可操作以测量径向外部涡轮叶片尖端与环绕叶片尖端的环形定子罩之间的叶片间隙。 叶片尖端可以是尖叫尖端，并且传感器可操作以测量传感器之间的距离，以及鸣叫器顶端壁之间的距离以及在尖叫尖端的空腔内的面向外壁的距离。 探头可以可操作地连接到控制器，用于向控制器发送信号，指示用于控制用于主动间隙控制的空气阀的第一和第二距离。 可以使用两个或更多个探头来确定转子中心线偏移。

公开(公告)号：US20090064522A1

公开(公告)日：2009-03-12

申请号：US11688354

申请日：2007-03-20

Applicant: William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

Inventor： William Lee Herron ,  Robert Joseph Albers ,  Rafael Jose Ruiz ,  Samhita Dasgupta

IPC: G01D21/00

CPC classification number: G01B7/14 ,  F01D5/20 ,  F01D21/003 ,  G01B21/16

Abstract: A multi sensor clearance probe with at least longitudinally and transversely spaced apart first and second sensors operable to measure first and second distances respectively between the sensors and a longitudinally spaced apart rotating rotor. The sensors being operable to measure blade tip clearances between radially outer turbine blade tips and an annular stator shroud circumscribing the blade tips. The blade tips may be squealer tips and the sensors operable to measure the distances between the sensors and tops of squealer tip walls and outwardly facing walls within cavities of the squealer tips. The probe may be operably connected to a controller for sending signals to the controller indicating the first and second distances for controlling an air valve used for active clearance control. Two or more of the probe may be used to determine rotor centerline offset.

Abstract translation: 多传感器间隙探头，其至少纵向和横向间隔开的第一和第二传感器可操作以分别测量传感器和纵向间隔开的旋转转子之间的第一和第二距离。 传感器可操作以测量径向外部涡轮叶片尖端与环绕叶片尖端的环形定子罩之间的叶片间隙。 叶片尖端可以是尖叫尖端，并且传感器可操作以测量传感器之间的距离，以及鸣叫器顶端壁之间的距离以及在尖叫尖端的空腔内的面向外壁的距离。 探头可以可操作地连接到控制器，用于向控制器发送信号，指示用于控制用于主动间隙控制的空气阀的第一和第二距离。 可以使用两个或更多个探头来确定转子中心线偏移。