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1.再颁专利Borescope inspection port device for gas turbine engine and gas turbine engine using same 有权用于燃气轮机发动机和燃气轮机的喷射器检查口装置公开(公告)号：USRE43928E1
公开(公告)日：2013-01-15
申请号：US13171708
申请日：2011-06-29
Applicant: Brian Ellis Clouse , David P. Dube
Inventor： Brian Ellis Clouse , David P. Dube
IPC: F04D29/00
CPC classification number: F01D17/02 , F05D2260/80
Abstract: An adapter to permit borescope access inside a gas turbine engine including a compressor stator having a plurality of compressor stator segments comprises a body portion defining a bore extending longitudinally therethrough from a first end to be disposed adjacent to outside surfaces of adjacent compressor stator segments to a second end to be disposed adjacent to inside surfaces of adjacent compressor stator segments. The bore permits a borescope to enter therethrough. The adapter further comprises an attachment portion for circumferentially coupling at least one compressor stator segment to an outer casing of the gas turbine engine.
Abstract translation: 允许在包括具有多个压缩机定子段的压缩机定子的燃气涡轮发动机内进行管道镜访问的适配器包括主体部分，其限定从第一端纵向延伸穿过的孔，以邻近邻近的压缩机定子段的外表面设置到 邻近邻近的压缩机定子段的内表面设置的第二端。 孔允许管道内窥镜进入其中。 适配器还包括用于将至少一个压缩机定子段周向地联接到燃气涡轮发动机的外壳的附接部分。
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公开(公告)号：US06439842B1
公开(公告)日：2002-08-27
申请号：US09715325
申请日：2000-11-17
Applicant: Myron Daniel Toomey , Brian Ellis Clouse , Michael Thomas Hogan , Craig Robert Jacobson
IPC: F01D1712
CPC classification number: F01D11/08 , F01D11/18 , F01D17/162 , F01D25/243
Abstract: A stator case for a gas turbine engine having a stator and a rotor. The rotor has a plurality of circumferential rows of blades. Each blade extends radially outward from a root to a tip. The case includes a tubular shell extending axially between a forward end and an aft end. The shell has an interior surface defining a hollow interior sized and shaped for receiving at least a portion of the rotor of the gas turbine engine. The case also includes a circular forward flange extending radially outward from the forward end of the shell and a circular aft flange extending radially outward from the aft end of the shell. In addition, the case includes a circular rib extending radially outward from the shell between adjacent rows of blades. The rib is sized and shaped for adjusting transient deflections of the shell to generally match transient deflections of the tips of the plurality of rotor blades to reduce a transient clearance between the interior surface of the tubular shell and the tips of the rotor blades.
Abstract translation: 一种用于具有定子和转子的燃气涡轮发动机的定子箱。 转子具有多个圆周排的叶片。 每个叶片从根部向径向向外延伸到尖端。 壳体包括在前端和后端之间轴向延伸的管状壳体。 壳体具有限定中空内部的内表面，其尺寸和形状用于容纳燃气涡轮发动机的转子的至少一部分。 壳体还包括从壳体的前端径向向外延伸的圆形前凸缘和从壳体的后端径向向外延伸的圆形后凸缘。 此外，壳体包括从相邻的叶片行之间的壳体径向向外延伸的圆形肋。 肋的尺寸和形状适于调整外壳的瞬时偏转，以大体上匹配多个转子叶片的尖端的瞬时偏转，以减小管状壳体的内表面与转子叶片的尖端之间的瞬时间隙。
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公开(公告)号：US09404580B2
公开(公告)日：2016-08-02
申请号：US13445998
申请日：2012-04-13
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
CPC classification number: F16J15/0887 , F01D11/12 , F01D25/246 , F05D2230/642 , F05D2240/11 , F05D2250/75 , F05D2260/37 , F05D2260/38 , F16J15/0893 , Y10T29/49826
Abstract: The sealing apparatus and method of assembling the same is disclosed. The sealing apparatus may comprise a resilient member and a sealing member. The resilient member may define a cavity having a closed end and an open end. The resilient member may include a first wall having a first inner sealing surface and a second wall having a second inner sealing surface. The first and second walls may be joined at the closed end. The sealing member may be disposed at least partially in the cavity in sealing engagement with the first and second inner sealing surfaces. The sealing member may comprise an upper plurality of layered finger seals and a lower plurality of layered finger seals.
Abstract translation: 公开了密封装置及其组装方法。 密封装置可以包括弹性构件和密封构件。 弹性构件可以限定具有封闭端和开口端的空腔。 弹性构件可以包括具有第一内密封表面的第一壁和具有第二内密封表面的第二壁。 第一和第二壁可在封闭端连接。 密封构件可以至少部分地设置在与第一和第二内部密封表面密封接合的空腔中。 密封构件可以包括多个多层分层指状密封件和多个分层的指状密封件。
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公开(公告)号：US20130270777A1
公开(公告)日：2013-10-17
申请号：US13445998
申请日：2012-04-13
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
CPC classification number: F16J15/0887 , F01D11/12 , F01D25/246 , F05D2230/642 , F05D2240/11 , F05D2250/75 , F05D2260/37 , F05D2260/38 , F16J15/0893 , Y10T29/49826
Abstract: The sealing apparatus and method of assembling the same is disclosed. The sealing apparatus may comprise a resilient member and a sealing member. The resilient member may define a cavity having a closed end and an open end. The resilient member may include a first wall having a first inner sealing surface and a second wall having a second inner sealing surface. The first and second walls may be joined at the closed end. The sealing member may be disposed at least partially in the cavity in sealing engagement with the first and second inner sealing surfaces. The sealing member may comprise an upper plurality of layered finger seals and a lower plurality of layered finger seals.
Abstract translation: 公开了密封装置及其组装方法。 密封装置可以包括弹性构件和密封构件。 弹性构件可以限定具有封闭端和开口端的空腔。 弹性构件可以包括具有第一内密封表面的第一壁和具有第二内密封表面的第二壁。 第一和第二壁可以在封闭端连接。 密封构件可以至少部分地设置在与第一和第二内部密封表面密封接合的空腔中。 密封构件可以包括多个多层分层指状密封件和多个分层的指状密封件。
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公开(公告)号：US20130230386A1
公开(公告)日：2013-09-05
申请号：US13409758
申请日：2012-03-01
Applicant: Paul W. Baumann , Charles H. Warner , Brian Ellis Clouse
Inventor： Paul W. Baumann , Charles H. Warner , Brian Ellis Clouse
CPC classification number: F01D11/003 , F01D11/00 , F02C7/28 , F02C7/36 , F05D2220/36 , F05D2260/40311 , Y10T29/49229
Abstract: A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.
Abstract translation: 公开了一种用于燃气涡轮发动机的高压压缩机的后端的扩散器密封件。 扩散器密封件包括联接到扩散器壳体的流动引导架。 流动导向架还耦合到静态密封件。 静密封件接合旋转密封件，并允许空气在后方向通过静态和旋转密封件。 流动导向架还耦合到整流罩和整流罩/轮毂支撑件。 流动导向架支撑整流罩相对于后轮毂的间隔位置，使得流经静态和旋转密封件的空气在整流罩和后轮毂的前表面之间通过。 整流罩/轮毂支撑件从流动引导支撑件向前延伸并且接合整流罩的后表面，从而限制后轮毂和整流罩在向后方向的运动。 这种设计有助于防止零件或碎屑刺穿后轮毂并进入高压涡轮机，即使是风扇叶片或风扇叶片脱落事件。
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Patent Agency Ranking
公开(公告)号：US09506367B2
公开(公告)日：2016-11-29
申请号：US13554273
申请日：2012-07-20
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
CPC classification number: F01D11/08 , F01D25/246 , F05D2240/11 , Y10T29/49297
Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的叶片外部空气密封件（BOAS）包括其中包括径向内表面和径向外表面的密封体，所述径向内表面和径向外表面在前缘部分和 后缘部分和密封台面，其从密封体延伸并且包括从径向内表面径向向内延伸的向内指向的延伸部。
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公开(公告)号：US09447695B2
公开(公告)日：2016-09-20
申请号：US13409758
申请日：2012-03-01
Applicant: Paul W. Baumann , Charles H. Warner , Brian Ellis Clouse
Inventor： Paul W. Baumann , Charles H. Warner , Brian Ellis Clouse
CPC classification number: F01D11/003 , F01D11/00 , F02C7/28 , F02C7/36 , F05D2220/36 , F05D2260/40311 , Y10T29/49229
Abstract: A diffuser seal for an aft end of a high pressure compressor of a gas turbine engine is disclosed. The diffuser seal includes a flow guide carrier coupled to the diffuser case. The flow guide carrier is also coupled to a static seal. The static seal engages a rotary seal and permits air flow through the static and rotary seals in the aft direction. The flow guide carrier is also coupled to a fairing and a fairing/hub support. The flow guide carrier supports the fairing in a spaced-apart position with respect to the rear hub so that air flowing through the static and rotary seals passes between a forward surface of the fairing and the rear hub. The fairing/hub support extends forward from the flow guide support and engages an aft surface of the fairing thereby limiting movement of the rear hub and fairing in the aft direction. This design helps to prevent parts or debris from piercing the rear hub and entering the high pressure turbine in the even of a fan blade-out or fan blade-off event.
Abstract translation: 公开了一种用于燃气涡轮发动机的高压压缩机的后端的扩散器密封件。 扩散器密封件包括联接到扩散器壳体的流动引导架。 流动导向架还耦合到静态密封件。 静密封件接合旋转密封件，并允许空气在后方向通过静态和旋转密封件。 流动导向架还耦合到整流罩和整流罩/轮毂支撑件。 流动导向架支撑整流罩相对于后轮毂的间隔位置，使得流经静态和旋转密封件的空气在整流罩和后轮毂的前表面之间通过。 整流罩/轮毂支撑件从流动引导支撑件向前延伸并且接合整流罩的后表面，从而限制后轮毂和整流罩在向后方向的运动。 这种设计有助于防止零件或碎屑刺穿后轮毂并进入高压涡轮机，即使是风扇叶片或风扇叶片脱落事件。
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公开(公告)号：US09115596B2
公开(公告)日：2015-08-25
申请号：US13568240
申请日：2012-08-07
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
CPC classification number: F01D25/00 , F01D11/125 , F01D11/127 , F01D11/24 , Y10T29/49297
Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的叶片外部空气密封件（BOAS）包括其中包括径向内表面和径向外表面的密封体，所述径向内表面和径向外表面在前缘部分和 后缘部分。 前缘部分和后缘部分中的至少一个包括实心壁和穿孔壁。 穿孔壁的至少一部分与固体壁间隔开，使得通道在固体壁和穿孔壁之间延伸。
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公开(公告)号：US20140044528A1
公开(公告)日：2014-02-13
申请号：US13568240
申请日：2012-08-07
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
IPC: F01D25/00
CPC classification number: F01D25/00 , F01D11/125 , F01D11/127 , F01D11/24 , Y10T29/49297
Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. At least one of the leading edge portion and the trailing edge portion includes a solid wall and a perforated wall. At least a portion of the perforated wall is spaced from the solid wall such that a passage extends between the solid wall and the perforated wall.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的叶片外部空气密封件（BOAS）包括其中包括径向内表面和径向外表面的密封体，所述径向内表面和径向外表面在前缘部分和 后缘部分。 前缘部分和后缘部分中的至少一个包括实心壁和穿孔壁。 穿孔壁的至少一部分与固体壁间隔开，使得通道在固体壁和穿孔壁之间延伸。
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公开(公告)号：US20140140825A1
公开(公告)日：2014-05-22
申请号：US13554273
申请日：2012-07-20
Applicant: Brian Ellis Clouse
Inventor： Brian Ellis Clouse
IPC: F01D11/08
CPC classification number: F01D11/08 , F01D25/246 , F05D2240/11 , Y10T29/49297
Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion and a seal land that extends from the seal body and includes an inward pointing extension that extends radially inwardly from the radially inner face.
Abstract translation: 根据本公开的示例性方面的用于燃气涡轮发动机的叶片外部空气密封件（BOAS）包括其中包括径向内表面和径向外表面的密封体，所述径向内表面和径向外表面在前缘部分和 后缘部分和密封台面，其从密封体延伸并且包括从径向内表面径向向内延伸的向内指向的延伸部。
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