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1. 发明授权

US08480366B2 Recessed metering standoffs for airfoil baffle 有权
标题翻译：翼形挡板的嵌入式计量支座
公开(公告)号：US08480366B2
公开(公告)日：2013-07-09
申请号：US13272784
申请日：2011-10-13
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs are recessed into a surface of either the baffle or the airfoil body such that a height of the standoffs is greater than the spacing.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支座凹入到挡板或翼型体的表面中，使得支座的高度大于间隔。

2. 发明申请

US20100247327A1 RECESSED METERING STANDOFFS FOR AIRFOIL BAFFLE 有权
标题翻译：空气压缩机的压力计量标准
公开(公告)号：US20100247327A1
公开(公告)日：2010-09-30
申请号：US12411851
申请日：2009-03-26
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs maintain minimum spacing between the liner body and the airfoil body. In one embodiment, the standoffs are recessed into a surface of either the baffle or the airfoil body. In another embodiment, the standoffs are elongated to meter flow between the liner body and the airfoil body.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支架保持衬套主体和翼型体之间的最小间距。在一个实施例中，支座凹入到挡板或翼型体的表面中。在另一个实施例中，支座是伸长的，用于测量衬套主体和翼型体之间的流量。

3. 发明授权

US08109724B2 Recessed metering standoffs for airfoil baffle 有权
标题翻译：翼形挡板的嵌入式计量支座
公开(公告)号：US08109724B2
公开(公告)日：2012-02-07
申请号：US12411851
申请日：2009-03-26
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： B64C11/24
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs maintain minimum spacing between the liner body and the airfoil body. In one embodiment, the standoffs are recessed into a surface of either the baffle or the airfoil body. In another embodiment, the standoffs are elongated to meter flow between the liner body and the airfoil body.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支架保持衬套主体和翼型体之间的最小间距。在一个实施例中，支座凹入到挡板或翼型体的表面中。在另一个实施例中，支座是伸长的，用于测量衬套主体和翼型体之间的流量。

4. 发明申请

US20120034100A1 RECESSED METERING STANDOFFS FOR AIRFOIL BAFFLE 有权
标题翻译：空气压缩机的压力计量标准
公开(公告)号：US20120034100A1
公开(公告)日：2012-02-09
申请号：US13272784
申请日：2011-10-13
申请人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Stacy T. Malecki , Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18
CPC分类号： F01D5/189 , F05D2230/21 , F05D2240/126 , F05D2240/127 , F05D2250/70 , F05D2260/202
摘要： An internally cooled airfoil comprises an airfoil body, a baffle and a plurality of standoffs. The airfoil body is shaped to form leading and trailing edges, and pressure and suction sides surrounding an internal cooling channel. The baffle is disposed within the internal cooling channel and comprises a liner body having a perimeter shaped to correspond to the shape of the internal cooling channel and to form a cooling air supply duct. The baffle includes a plurality of cooling holes extending through the liner body to direct cooling air from the supply duct into the internal cooling channel. The standoffs maintain minimum spacing between the liner body and the airfoil body. The standoffs are recessed into a surface of either the baffle or the airfoil body such that a height of the standoffs is greater than the spacing.
摘要翻译：内部冷却的翼型件包括翼型本体，挡板和多个支座。翼型体成形为形成前缘和后缘，围绕内部冷却通道的压力和吸力侧。挡板设置在内部冷却通道内，并且包括衬套主体，其具有成形为对应于内部冷却通道的形状的周边并且形成冷却空气供应管道。挡板包括多个冷却孔，其延伸穿过衬套主体，以将冷却空气从供应管道引导到内部冷却通道中。支架保持衬套主体和翼型体之间的最小间距。支座凹入到挡板或翼型体的表面中，使得支座的高度大于间隔。

5. 发明申请

US20100209229A1 Airfoil inserts, flow-directing elements and assemblies thereof 有权
标题翻译：翼型插件，导流元件及其组件
公开(公告)号：US20100209229A1
公开(公告)日：2010-08-19
申请号：US12378681
申请日：2009-02-18
申请人： Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D9/041 , F01D5/189 , F01D9/065
摘要： Disclosed are examples of flow-directing elements, airfoil inserts, and assemblies thereof. A flow-directing element has an inner buttress with an airfoil extending outwardly therefrom. The airfoil includes a cavity that extends within the airfoil to an exit port disposed in the inner buttress. A shelf disposed about the buttress defines the exit port, and the shelf includes a discourager extending into the cavity. An airfoil insert has a tubular body, with an outlet at one end. A plate affixed to the body at the outlet partially blocks the outlet, and includes a tab extending away from the body and defining a portion of an outlet periphery. Upon assembly of the flow directing element and the insert, the tab interacts with the discourager to direct a coolant to the exit port while restricting leakage of the coolant back into the cavity, between the airfoil insert and the flow-directing element.
摘要翻译：公开了流动引导元件，翼型件插件及其组件的示例。导流元件具有内侧支撑，其中从其向外延伸的翼型件。翼型件包括在翼型件内延伸到设置在内侧支柱中的出口的空腔。围绕支撑架设置的搁架限定出口，并且搁架包括延伸到空腔中的挡板。机翼插入件具有管状体，在一端具有出口。在出口处固定到主体的板部分地阻挡出口，并且包括远离主体延伸并限定出口周边的一部分的突出部。在流动引导元件和插入件的组装时，突片与捣实器相互作用以将冷却剂引导到出口端口，同时将冷却剂的泄漏返回到空腔中，在翼型件插入件和导流元件之间。

6. 发明授权

US08353668B2 Airfoil insert having a tab extending away from the body defining a portion of outlet periphery 有权
标题翻译：翼型插入件具有远离本体延伸的突出部，限定出口周边的一部分
公开(公告)号：US08353668B2
公开(公告)日：2013-01-15
申请号：US12378681
申请日：2009-02-18
申请人： Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
发明人： Tracy A. Propheter-Hinckley , Amanda Jean Learned , Shawn J. Gregg
IPC分类号： F01D5/18 , F01D9/02
CPC分类号： F01D9/041 , F01D5/189 , F01D9/065
摘要： Disclosed are examples of flow-directing elements, airfoil inserts, and assemblies thereof. A flow-directing element has an inner buttress with an airfoil extending outwardly therefrom. The airfoil includes a cavity that extends within the airfoil to an exit port disposed in the inner buttress. A shelf disposed about the buttress defines the exit port, and the shelf includes a discourager extending into the cavity. An airfoil insert has a tubular body, with an outlet at one end. A plate affixed to the body at the outlet partially blocks the outlet, and includes a tab extending away from the body and defining a portion of an outlet periphery. Upon assembly of the flow directing element and the insert, the tab interacts with the discourager to direct a coolant to the exit port while restricting leakage of the coolant back into the cavity, between the airfoil insert and the flow-directing element.
摘要翻译：公开了流动引导元件，翼型件插件及其组件的示例。导流元件具有内侧支撑，其中从其向外延伸的翼型件。翼型件包括在翼型件内延伸到设置在内侧支柱中的出口的空腔。围绕支撑架设置的搁架限定出口，并且搁架包括延伸到空腔中的挡板。机翼插入件具有管状体，在一端具有出口。在出口处固定到主体的板部分地阻挡出口，并且包括远离主体延伸并限定出口周边的一部分的突出部。在流动引导元件和插入件的组装时，突片与捣实器相互作用以将冷却剂引导到出口端口，同时将冷却剂的泄漏返回到空腔中，在翼型件插入件和导流元件之间。

7. 发明授权

US08348613B2 Airflow influencing airfoil feature array 有权
标题翻译：气流影响翼型特征阵列
公开(公告)号：US08348613B2
公开(公告)日：2013-01-08
申请号：US12413649
申请日：2009-03-30
申请人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
发明人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
IPC分类号： B64C11/00
CPC分类号： F01D5/189 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/2214 , F05D2260/22141
摘要： An example gas turbine engine airfoil includes an airfoil wall establishing a cavity that extends axially from an airfoil leading edge portion to an airfoil trailing edge portion and extends radially from an airfoil inner end to an airfoil outer end. The cavity is configured to receive a baffle that is spaced from the airfoil leading edge portion such that an impingement cooling area is established between the airfoil leading edge portion and the baffle when the baffle is received within the cavity. An array of nonuniformly distributed features is disposed on the airfoil wall within the impingement cooling area. The features are configured to influence airflow within the impingement cooling area.
摘要翻译：一个示例性的燃气涡轮发动机翼型件包括一个翼型壁，其形成一个空腔，其从翼型件前缘部分轴向延伸到翼型件后缘部分，并从翼型件内端径向延伸到翼型件外端。空腔构造成接收与翼型件前缘部分间隔开的挡板，使得当挡板接收在空腔内时，在翼型件前缘部分和挡板之间建立冲击冷却区域。不均匀分布的特征阵列设置在冲击冷却区域内的翼型壁上。这些特征被配置成影响冲击冷却区域内的气流。

8. 发明申请

US20100247284A1 AIRFLOW INFLUENCING AIRFOIL FEATURE ARRAY 有权
标题翻译：气流影响气流特征阵列
公开(公告)号：US20100247284A1
公开(公告)日：2010-09-30
申请号：US12413649
申请日：2009-03-30
申请人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
发明人： Shawn J. Gregg , Tracy A. Propheter-Hinckley , Amanda Jean Learned
IPC分类号： F01D5/18 , F01D25/08
CPC分类号： F01D5/189 , F05D2240/121 , F05D2240/303 , F05D2260/201 , F05D2260/2214 , F05D2260/22141
摘要： An example gas turbine engine airfoil includes an airfoil wall establishing a cavity that extends axially from an airfoil leading edge portion to an airfoil trailing edge portion and extends radially from an airfoil inner end to an airfoil outer end. The cavity is configured to receive a baffle that is spaced from the airfoil leading edge portion such that an impingement cooling area is established between the airfoil leading edge portion and the baffle when the baffle is received within the cavity. An array of nonuniformly distributed features is disposed on the airfoil wall within the impingement cooling area. The features are configured to influence airflow within the impingement cooling area.
摘要翻译：一个示例性的燃气涡轮发动机翼型件包括一个翼型壁，其形成一个空腔，其从翼型件前缘部分轴向延伸到翼型件后缘部分，并从翼型件内端径向延伸到翼型件外端。空腔构造成接收与翼型件前缘部分间隔开的挡板，使得当挡板接收在空腔内时，在翼型件前缘部分和挡板之间建立冲击冷却区域。不均匀分布的特征阵列设置在冲击冷却区域内的翼型壁上。这些特征被配置成影响冲击冷却区域内的气流。

9. 发明授权

US09222364B2 Platform cooling circuit for a gas turbine engine component 有权
标题翻译：用于燃气涡轮发动机部件的平台冷却回路
公开(公告)号：US09222364B2
公开(公告)日：2015-12-29
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
IPC分类号： F01D9/02 , F01D5/18
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路平台的路径一侧。平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。

10. 发明申请

US20140047843A1 PLATFORM COOLING CIRCUIT FOR A GAS TURBINE ENGINE COMPONENT 有权
标题翻译：用于气体涡轮发动机部件的平台冷却回路
公开(公告)号：US20140047843A1
公开(公告)日：2014-02-20
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
IPC分类号： F02C7/18 , F01D25/12 , F02C3/04 , F01D9/02
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
摘要翻译：根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路平台的路径一侧。平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。

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