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81.发明申请公开(公告)号：US20160376921A1
公开(公告)日：2016-12-29
申请号：US15004436
申请日：2016-01-22
CPC分类号： F01D25/12 , F01D9/02 , F01D11/08 , F01D11/20 , F01D25/005 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2260/20 , F05D2260/201 , F05D2300/6033 , Y02T50/672 , Y02T50/676
摘要： A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Cooling air is directed onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.
摘要翻译： 适用于燃气涡轮发动机的涡轮机罩包括多个金属载体段和安装到相应的金属载体段的多个叶片轨道段。 当在燃气涡轮发动机中暴露于高温时，冷却空气被引导到叶片轨道段上以冷却叶片轨道段。
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公开(公告)号：US20160356164A1
公开(公告)日：2016-12-08
申请号：US15173126
申请日：2016-06-03
IPC分类号： F01D5/28 , F23R3/00 , F01D5/14 , B29C65/48 , F01D5/30 , F01D9/04 , C23C16/04 , B29C65/02 , F02C3/04 , F01D5/22
CPC分类号： F01D5/284 , B29C65/02 , B29C65/48 , B29L2031/7504 , F01D25/005 , F01D25/246 , F02K1/04 , F05D2240/11 , F05D2240/12 , F05D2300/2261 , F05D2300/6033 , F05D2300/611 , F05D2300/614 , F23M2900/05004 , F23R3/007 , F23R2900/00018
摘要： An assembly comprising a ceramic matrix composite component, a monolithic insert, and a polymer char and a method for producing the same. The ceramic matrix composite component may include an exterior surface, with the monolithic insert bonded to the exterior surface of the ceramic matrix composite component. The polymer char may be sandwiched between the monolithic insert and the exterior surface of the ceramic matrix composite that may bond the monolithic insert to the ceramic matrix composite component.
摘要翻译： 包括陶瓷基复合材料组件，整体嵌件和聚合物炭的组件及其制造方法。 陶瓷基复合材料组件可以包括外表面，整体嵌入件结合到陶瓷基复合元件的外表面。 聚合物炭可以夹在整体式插入件和陶瓷基质复合材料的外表面之间，可将整体式嵌件与陶瓷基复合材料部件结合。
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公开(公告)号：US20160348523A1
公开(公告)日：2016-12-01
申请号：US15159163
申请日：2016-05-19
CPC分类号： F01D11/005 , F01D9/02 , F05D2240/11 , F05D2270/65 , Y02T50/672
摘要： An assembly for use in a gas turbine engine is disclosed. The assembly includes a first component arranged adjacent to a second component to form a gap therebetween and a pressure activated seal that resists flow through the gap.
摘要翻译： 公开了一种用于燃气涡轮发动机的组件。 该组件包括邻近第二部件设置的第一部件，以在其间形成间隙，以及阻止流过间隙的压力活化密封件。
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公开(公告)号：US20160290140A1
公开(公告)日：2016-10-06
申请号：US15066701
申请日：2016-03-10
IPC分类号： F01D5/22
CPC分类号： F01D5/225 , F01D11/08 , F01D25/246 , F05D2240/11 , F05D2260/30 , F05D2300/6033 , Y02T50/672
摘要： A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.
摘要翻译： 燃气涡轮发动机组件包括支撑部件和支撑部件。 支撑部件包括被支撑部件接合的特征。 支撑的部件包括含陶瓷的材料。
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公开(公告)号：US20160258320A1
公开(公告)日：2016-09-08
申请号：US15056345
申请日：2016-02-29
CPC分类号： F01D25/005 , F01D5/147 , F01D5/189 , F01D5/282 , F01D5/284 , F01D9/041 , F01D9/065 , F05D2220/32 , F05D2230/23 , F05D2230/60 , F05D2240/80 , F05D2300/6012 , F05D2300/6033 , Y02T50/672
摘要： A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.
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公开(公告)号：US20160245102A1
公开(公告)日：2016-08-25
申请号：US15049672
申请日：2016-02-22
CPC分类号： F01D11/005 , F01D11/08 , F01D25/246 , F05D2240/11 , F05D2250/182 , F05D2260/36 , F05D2300/6033 , Y02T50/672
摘要： A turbine shroud for a gas turbine engine is disclosed in this paper. The turbine shroud includes a ceramic-matrix composite blade track. The ceramic-matrix composite blade track includes a plurality of track segments located circumferentially adjacent to one another to form a track ring. Features of the track segments provide tortuous paths for gasses trying to pass through the ceramic-matrix composite blade track that may reduce leakage through the blade track.
摘要翻译： 本文中公开了一种用于燃气涡轮发动机的涡轮罩。 涡轮机罩包括陶瓷基复合材料刀片轨道。 陶瓷基复合材料刀片轨道包括彼此周向相邻的多个轨道段，以形成轨道环。 轨道段的特征为试图通过陶瓷 - 矩阵复合叶片轨道的气体提供曲折的路径，这可以减少通过叶片轨迹的泄漏。
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公开(公告)号：US20160177743A1
公开(公告)日：2016-06-23
申请号：US14797916
申请日：2015-07-13
摘要： Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material. A core of the airfoils is surrounded by the at least one layer of ceramic-containing fiber/matrix material.
摘要翻译： 公开了一种燃气涡轮发动机的固定叶片和旋转叶片，其包括由陶瓷基复合材料形成的翼型件。 翼型件包括至少一层含陶瓷的基体材料和悬浮在基体材料中的含陶瓷的增强纤维。 翼片的核心被至少一层含陶瓷的纤维/基质材料包围。
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公开(公告)号：US20160123164A1
公开(公告)日：2016-05-05
申请号：US14869559
申请日：2015-09-29
CPC分类号： F01D25/005 , F01D5/282 , F01D5/284 , F01D9/042 , F01D9/065 , F05D2230/642 , F05D2300/6033 , Y02T50/672 , Y02T50/673
摘要： A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.
摘要翻译： 本文介绍了一种用于燃气涡轮发动机的叶片组件。 叶片组件包括内平台，外平台和含陶瓷的翼型。 含陶瓷的翼型件从内平台延伸到外平台。 由金属材料制成的加固翼梁通过含陶瓷的翼型的中空芯从内平台延伸到外平台。
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公开(公告)号：US11725535B2
公开(公告)日：2023-08-15
申请号：US16107012
申请日：2018-08-21
CPC分类号： F01D25/005 , F01D5/282 , F01D5/284 , F01D9/042 , F01D9/065 , F05D2230/642 , F05D2300/6033 , Y02T50/60
摘要： A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil.
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公开(公告)号：US11466858B2
公开(公告)日：2022-10-11
申请号：US16599756
申请日：2019-10-11
摘要： A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.
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