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公开(公告)号：US11280201B2
公开(公告)日：2022-03-22
申请号：US16600875
申请日：2019-10-14
发明人： Adam P. Generale , Lucas Dvorozniak , San Quach , Bryan P. Dube
IPC分类号： F01D5/18
摘要： An airfoil vane includes an airfoil section including an outer wall that defines an internal cavity; and a baffle situated in the internal cavity, the baffle including a baffle wall that defines a central cavity having a leading end and a trailing end corresponding to a leading end and a trailing end of the airfoil section, and a tail extending from the baffle wall, the tail including at least one feature configured to disturb an airflow surrounding the tail. A baffle for the airfoil vane assembly and a method of assembling a ceramic matrix composite airfoil vane are also disclosed.
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公开(公告)号：US10975706B2
公开(公告)日：2021-04-13
申请号：US16250804
申请日：2019-01-17
摘要： A stator vane may comprise an airfoil extending between a first platform and a second platform, the airfoil including a core extending relatively orthogonal to the first platform and the second platform, at least one of the first platform or second platform comprising a frustic load transmission feature, wherein the frustic load transmission feature comprises at least a first angular surface disposed proximate a platform edge, wherein the first angular surface is defined by a non-orthogonal angle θ with respect to an outer platform surface.
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公开(公告)号：US10808549B2
公开(公告)日：2020-10-20
申请号：US16049987
申请日：2018-07-31
摘要： An airfoil includes a platform that has platform leading and trailing ends, lateral side faces, and inner and outer faces. An airfoil portion extends outwardly from the inner face of the platform. The airfoil portion includes airfoil leading and trailing ends and side walls that join the airfoil leading and trailing ends. The platform includes a cooling passage that has an inlet at a forward location, outlet slots at the platform trailing end, and an intermediate passage portion that extends from the inlet to the outlet slots. The intermediate passage portion includes a common manifold region that feeds the outlet slots. The platform includes a rib that is elongated in a length direction between the platform leading and trailing ends. The rib divides two of the cooling passages such that the two cooling passages are fluidly unconnected with each other in the platform.
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公开(公告)号：US20200158018A1
公开(公告)日：2020-05-21
申请号：US16197835
申请日：2018-11-21
发明人： Adam P. Generale , Bryan P. Dube
摘要： An internally cooled component for a gas turbine engine includes a component having one or more exterior walls defining an internal component cavity configured for a cooling airflow to flow therethrough. An internal component rib extends into the internal component cavity from the one or more exterior walls. An insert is positioned in the internal component cavity, and a flow discourager is positioned at the insert and is configured to prevent the cooling airflow from flowing past the internal component rib.
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公开(公告)号：US10072516B2
公开(公告)日：2018-09-11
申请号：US14838407
申请日：2015-08-28
发明人： Jesse M. Carr , Bryan P. Dube
CPC分类号： F01D9/041 , F01D9/042 , F01D25/246 , F01D25/28 , F02C3/04 , F05D2220/32 , F05D2240/12 , F05D2240/80 , Y02T50/672 , Y02T50/673
摘要： A vane arc segment includes a radially inner and outer platforms and an airfoil mechanically clamped between the platforms. The airfoil has an airfoil section that extends radially between radially inner and outer fairing platforms. At least one of the fairing platforms includes forward and aft sides, circumferential sides, and a gas path side and an opposed radial side. The radial side includes a plurality of protrusions that have faces that are oriented substantially normal to, respectively, radial, tangential, and axial load transmission directions of the airfoil such that the faces, respectively, primarily bear radial, tangential, and axial load transmissions of the airfoil.
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公开(公告)号：US20160108755A1
公开(公告)日：2016-04-21
申请号：US14878555
申请日：2015-10-08
发明人： Jesse M. Carr , Bryan P. Dube
CPC分类号： F01D25/12 , F01D5/186 , F01D9/041 , F02C7/18 , F05D2220/32 , F05D2230/10 , F05D2240/122 , F05D2240/123 , F05D2240/304 , F05D2240/305 , F05D2240/35 , F05D2260/202 , F05D2260/97 , F05D2270/114 , F23R3/002 , F23R2900/03042 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component includes an exterior pressure side with a plurality of cooling holes located in the exterior pressure side. A relief cut surrounds at least one of the plurality of cooling holes.
摘要翻译： 燃气涡轮发动机部件包括具有位于外部压力侧的多个冷却孔的外部压力侧。 减压切割围绕多个冷却孔中的至少一个。
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公开(公告)号：US11125093B2
公开(公告)日：2021-09-21
申请号：US16659737
申请日：2019-10-22
IPC分类号： F01D11/00
摘要： A vane includes a ceramic vane piece that defines first and second vane platforms and a hollow airfoil section that joins the first and second vane platforms. A structural platform adjacent the first platform defines a radial seal slot. A seal has a radial leg and an axial leg. The radial leg extends in the radial seal slot and the axial leg extends in an interface between the structural platform and the first vane platform.
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公开(公告)号：US20210156271A1
公开(公告)日：2021-05-27
申请号：US16690989
申请日：2019-11-21
IPC分类号： F01D9/04
摘要： An airfoil piece includes a first vane platform, a second vane platform, and a hollow airfoil section that joins the first vane platform and the second vane platform. The hollow airfoil section includes a collar projection which extends past the first vane platform. The collar projection includes at least one radial tab projecting therefrom. An airfoil assembly and a method of assembling a vane are also disclosed.
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公开(公告)号：US20210148241A1
公开(公告)日：2021-05-20
申请号：US16689529
申请日：2019-11-20
发明人： Howard J. Liles , Bryan P. Dube , Bryan H. Farrar
IPC分类号： F01D9/04
摘要： An airfoil assembly includes an airfoil. The airfoil has first and second platforms and an airfoil between the first and second platforms. A support ring is configured to retain the first platform. The support ring has a lip which extends radially inward from the support ring. The lip is configured to engage an axial face of the first platform. The lip has a primary retention feature and a secondary retention feature. The primary and secondary retention features are configured to retain the first face of the first platform with respect to the annular ring. A support structure for an airfoil and a method of retaining an airfoil assembly are also disclosed.
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公开(公告)号：US20210131296A1
公开(公告)日：2021-05-06
申请号：US16672611
申请日：2019-11-04
发明人： Jon E. Sobanski , Bryan P. Dube
摘要： A gas turbine engine component includes a vane arc segment that defines an axis. The vane arc segment includes an airfoil section and first and second platforms. The airfoil section has a first radial end, a second radial end, a first side, a second side, a leading edge, and a trailing edge. The airfoil section has associated characteristics, including a center of pressure and an aerodynamic load vector through the center of pressure. The first platform defines a first side chevron face that has a leading leg and a trailing leg that meet at an angle. The leading leg is elongated along a centerline that is non-axially oriented with respect to the axis, the leading leg meets the leading face at a leading first side corner. The leading first side corner is located outside of the aerodynamic load vector relative to the leading edge of the airfoil section.
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