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1. 发明申请

US20160348527A1 SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT 审中-公开
标题翻译：具有陶瓷基质复合材料密封部分的SHROUD CARTRIDGE
公开(公告)号：US20160348527A1
公开(公告)日：2016-12-01
申请号：US14721620
申请日：2015-05-26
申请人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
IPC分类号： F01D11/08 , F01D25/24 , F01D25/00
CPC分类号： F01D11/08 , F01D9/04 , F01D25/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2240/55 , F05D2300/6033
摘要： A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.
摘要翻译：提供了一种用于在燃气涡轮发动机中径向包围涡轮的罩。护罩包括限定销接收载体孔的载体和陶瓷基质复合材料（CMC）密封段，陶瓷基体复合材料（CMC）密封段包括具有面向涡轮机的表面的弓形凸缘和限定销接收密封部分孔的部分。密封段孔与弧形凸缘径向间隔开间隔法兰，该间隔法兰从弧形凸缘径向向外延伸，以在细长销的密封段孔内接收。细长销延伸穿过承载孔和密封段孔，并且细长销具有至少八分之八英寸的横向横截面尺寸。

2. 发明授权

US09963990B2 Ceramic matrix composite seal segment for a gas turbine engine 有权
公开(公告)号：US09963990B2
公开(公告)日：2018-05-08
申请号：US14721705
申请日：2015-05-26
申请人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
IPC分类号： F01D11/08 , F01D25/24 , F01D9/04
CPC分类号： F01D11/08 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/24 , F05D2300/6033
摘要： A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.

3. 发明申请

US20160348528A1 CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE 有权
标题翻译：陶瓷基体复合材料密封段用于气体涡轮发动机
公开(公告)号：US20160348528A1
公开(公告)日：2016-12-01
申请号：US14721705
申请日：2015-05-26
申请人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Douglas David Dierksmeier , Jun Shi , Todd Engel
IPC分类号： F01D11/08 , F01D25/24
CPC分类号： F01D11/08 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/24 , F05D2300/6033
摘要： A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
摘要翻译：一种陶瓷基体复合材料（CMC）密封段，用于分段涡轮机罩，用于在燃气涡轮发动机中径向包围涡轮机。 CMC密封段包括具有面向涡轮的表面的弧形凸缘和限定用于接收细长销的孔的部分，孔的长度为其中接收的细长销的长度的至少70％。 CMC密封段由载体承载，其中至少一个细长销被接收在孔内。限定销接收孔的CMC密封段部分通过从弧形凸缘径向向外延伸的间隔凸缘与弓形凸缘径向间隔开。

4. 发明申请

US20170044920A1 TURBINE SHROUD HAVING CERAMIC MATRIX COMPOSITE SEAL SEGMENT 审中-公开
标题翻译：具有陶瓷基体复合材料密封部分的涡轮机
公开(公告)号：US20170044920A1
公开(公告)日：2017-02-16
申请号：US14721651
申请日：2015-05-26
申请人： Daniel Kent Vetters , David J. Thomas , Douglas David Dierksmeier , Jun Shi , Todd Engel
发明人： Daniel Kent Vetters , David J. Thomas , Douglas David Dierksmeier , Jun Shi , Todd Engel
IPC分类号： F01D11/12 , F01D9/02
CPC分类号： F01D11/12 , F01D9/02 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2250/15 , F05D2260/30 , F05D2260/38 , F05D2260/941 , F05D2300/6033
摘要： A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
摘要翻译：一种用于在包括载体，陶瓷基体复合（CMC）密封段和细长销）的燃气涡轮发动机中径向包围可旋转涡轮机的分段涡轮机罩。载体限定销接收载体孔，CMC密封段限定销接收密封部分孔。细长销延伸穿过承载孔和密封段孔。销接收载体孔包括悬臂构件，使得载体孔的长度足以在涡轮机的运行期间在承载孔和承载孔内的销之间实现径向弯曲。

5. 发明申请

US20160348526A1 SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT 审中-公开
标题翻译：具有陶瓷基质复合材料密封部分的SHROUD CARTRIDGE
公开(公告)号：US20160348526A1
公开(公告)日：2016-12-01
申请号：US14721590
申请日：2015-05-26
申请人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Joseph Lamusga , Rick Uskert
发明人： Daniel Kent Vetters , David J. Thomas , Ted Freeman , Joseph Lamusga , Rick Uskert
IPC分类号： F01D11/02
CPC分类号： F01D11/02 , F01D9/04 , F01D25/246 , F05D2300/6033
摘要： A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.
摘要翻译：提供了一种用于燃气涡轮发动机的分段涡轮机罩的陶瓷基体复合（CMC）密封段的筒。墨盒包括载体片段和CMC密封片段。载体段的表面和CMC密封段的表面形成靠近CMC密封段的整个周边的配合区域。载体段表面可以包括通道，并且可压缩配合元件可以设置在通道内。可以将空气供应到由载体和CMC密封段以及配合区域形成的空腔。

6. 发明申请

US20170044921A1 FLEXIBLY MOUNTED CERAMIC MATRIX COMPOSITE SEAL SEGMENTS 审中-公开
标题翻译：柔性安装陶瓷基体复合密封件
公开(公告)号：US20170044921A1
公开(公告)日：2017-02-16
申请号：US14721684
申请日：2015-05-26
申请人： Daniel Kent Vetters , Todd Engel , Matt Brandt
发明人： Daniel Kent Vetters , Todd Engel , Matt Brandt
IPC分类号： F01D11/12 , F01D25/24
CPC分类号： F01D11/12 , F01D9/04 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2260/30 , F05D2300/6033
摘要： A segmented turbine shroud for radially encasing a turbine in a gas turbine engine comprises a carrier comprising a flange; a ceramic matrix composite (CMC) seal segment comprising a portion defining a pin-receiving bore; an elongated pin extending through the pin-receiving bore; a bushing surrounding the elongated pin within the bore; and a flexible mounting member, the flexible mounting member being connected to the bushing and the carrier flange to thereby flexibly mount the CMC seal segment to the carrier.
摘要翻译：用于在燃气涡轮发动机中径向包围涡轮机的分段涡轮机罩包括：载体，其包括凸缘; 陶瓷基体复合材料（CMC）密封段，其包括限定销接收孔的部分; 延伸穿过销接收孔的细长销; 围绕孔内的细长销的衬套; 以及柔性安装构件，所述柔性安装构件连接到所述衬套和所述载体凸缘，从而将所述CMC密封段柔性地安装到所述载体上。

7. 发明授权

US09156549B2 Aircraft vertical lift device 有权
标题翻译：飞机垂直升降装置
公开(公告)号：US09156549B2
公开(公告)日：2015-10-13
申请号：US12980420
申请日：2010-12-29
申请人： Daniel Kent Vetters , Andrew Barlow
发明人： Daniel Kent Vetters , Andrew Barlow
IPC分类号： B64C29/00
CPC分类号： B64C29/0025
摘要： A lift device is disclosed that can be used to provide vertical lift to an aircraft or other vehicle. The lift device can include a fan that produces an airflow and a vane box that can direct the airflow. In one form the fan can be oriented at an angle relative to a reference plane in the aircraft. In another form the vane box can be oriented at an angle. The vane box can be structured to provide a maximum flow area between an aft flow vector and a forward flow vector.
摘要翻译：公开了可用于向飞行器或其他车辆提供垂直升降的升降装置。提升装置可以包括产生气流的风扇和可引导气流的叶片盒。在一种形式中，风扇可以相对于飞行器中的参考平面成一定角度定向。在另一种形式中，叶片箱可以以一定角度定向。叶片箱可以被构造成在后向流矢量和向前流动矢量之间提供最大流动面积。

8. 发明授权

US08438859B2 Integrated bypass engine structure 有权
标题翻译：集成旁路引擎结构
公开(公告)号：US08438859B2
公开(公告)日：2013-05-14
申请号：US12006980
申请日：2008-01-08
申请人： Daniel Kent Vetters
发明人： Daniel Kent Vetters
IPC分类号： F02C7/20
CPC分类号： F04D29/52 , F01D25/24 , F02K3/04
摘要： One form of the present invention contemplates an apparatus including a gas turbine engine core, wherein a gearbox accessory is mounted to the engine core and is substantially enclosed by an inner fairing. The apparatus can further include a nacelle having a plurality of panels, wherein the nacelle panels substantially enclose and overlap at least a portion of the inner fairing. The apparatus can further include a bypass duct defined between an exterior surface of the inner fairing and an interior surface of at least some of the nacelle panels. In additional and/or alternative forms a number of frame rods can also be used internal to the nacelle or nacelle panel. In some forms the frame rods can be connected between a front and rear frame.
摘要翻译：本发明的一种形式涉及一种包括燃气涡轮发动机芯的装置，其中齿轮箱附件安装在发动机芯上并且基本上由内部整流罩包围。该装置还可以包括具有多个面板的机舱，其中，所述机舱面板基本上包围并与所述内部整流罩的至少一部分重叠。该装置还可以包括限定在内部整流罩的外表面与至少一些机舱面板的内表面之间的旁路管道。在附加和/或替代形式中，许多框架杆也可以在机舱或机舱面板内部使用。在一些形式中，框架杆可以连接在前框架和后框架之间。

9. 发明申请

US20110250075A1 ROTOR BLADE ASSEMBLY 有权
标题翻译：转子叶片组件
公开(公告)号：US20110250075A1
公开(公告)日：2011-10-13
申请号：US12758856
申请日：2010-04-13
申请人： Daniel Kent Vetters
发明人： Daniel Kent Vetters
IPC分类号： F03B3/12 , F02C6/00 , B21K3/04
CPC分类号： F01D5/282 , B64C11/205 , B64D27/00 , B64D2027/005 , F01D5/288 , F02K3/06 , F04D29/023 , F04D29/324 , F05D2300/603 , Y02T50/66 , Y02T50/672
摘要： A rotor blade assembly is disclosed herein. The rotor blade assembly includes a composite blade portion extending a length from a root to a tip. A leading edge of the composite blade portion extends from the tip to an end point along the length between the tip and the root. The rotor blade assembly also includes a base portion fixed to the composite blade portion proximate to the root. The rotor blade assembly also includes a sheath extending around the composite blade portion. The sheath is positioned along the length adjacent to the base portion and between the root and the end point of the leading edge.
摘要翻译：本文公开了一种转子叶片组件。转子叶片组件包括从根部延伸到尖端的复合叶片部分。复合叶片部分的前缘沿尖端和根部之间的长度从尖端延伸到终点。转子叶片组件还包括固定到靠近根部的复合叶片部分的基部。转子叶片组件还包括围绕复合叶片部分延伸的护套。护套沿着与基部相邻的长度并且在前缘的根部和终点之间定位。

10. 发明授权

US08720815B2 Aircraft propulsion system 有权
标题翻译：飞机推进系统
公开(公告)号：US08720815B2
公开(公告)日：2014-05-13
申请号：US12768585
申请日：2010-04-27
申请人： Daniel Kent Vetters , Robert Wayne Cedoz , David Eames
发明人： Daniel Kent Vetters , Robert Wayne Cedoz , David Eames
IPC分类号： B64D27/00
CPC分类号： B64D27/10 , B64D27/26 , B64D2027/005 , B64D2027/026 , Y02T50/44 , Y02T50/64 , Y02T50/66
摘要： An aircraft propulsion system is disclosed herein. The aircraft propulsion system includes a core engine having an intake, a compressor section, a combustor section, and a turbine section arranged along a centerline axis. The aircraft propulsion system also includes a nacelle surrounding the core engine. The aircraft propulsion system also includes at least one free power turbine driven to rotate by exhaust gases exiting the turbine section. The aircraft propulsion system also includes at least one rotor module driven to rotate by at least one free power turbine. The aircraft propulsion system also includes first and second pylons extending away from the nacelle and operable to mount the core engine to an aircraft. The first and second pylons are spaced from one another on opposite sides of at least one plane containing the centerline axis and mirror one another across the at least one plane.
摘要翻译：这里公开了一种飞机推进系统。飞行器推进系统包括具有进气口的核心发动机，压缩机部分，燃烧器部分和沿中心轴线布置的涡轮部分。飞机推进系统还包括围绕核心发动机的机舱。飞行器推进系统还包括至少一个自由动力涡轮机，该自由动力涡轮机被排出涡轮部分的废气驱动旋转。飞行器推进系统还包括至少一个被至少一个自由动力涡轮机驱动旋转的转子模块。飞机推进系统还包括从机舱延伸的第一和第二塔架，并且可操作地将核心发动机安装到飞机上。第一和第二塔在包含中心线轴线的至少一个平面的相对侧上彼此间隔开，并且跨越至少一个平面相互镜像。

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