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公开(公告)号：US20210381389A1
公开(公告)日：2021-12-09
申请号：US17228778
申请日：2021-04-13
申请人： GE Avio S.r.l.
摘要： An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.
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公开(公告)号：US11434765B2
公开(公告)日：2022-09-06
申请号：US17148635
申请日：2021-01-14
发明人： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
摘要： A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US20220098987A1
公开(公告)日：2022-03-31
申请号：US17388143
申请日：2021-07-29
申请人： GE Avio S.r.l.
发明人： Massimiliano Airaudo , Paolo Calza , Francesco Bertini , Matteo Renato Usseglio , Cristian Lizzer , Ernesto Sozio , Matteo Furfaro , Marco Thiene
摘要： A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.
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公开(公告)号：US20220243596A1
公开(公告)日：2022-08-04
申请号：US17523505
申请日：2021-11-10
发明人： Saurya Ranjan Ray , Francesco Bertini , Lyle Douglas Dailey , Jeffrey D. Clements , Jaikumar Loganathan , Simone Rosa Taddei
IPC分类号： F01D5/14
摘要： An airfoil assembly for a turbine engine comprising an outer band, an inner band radially spaced inwardly from the outer band to define an annular region, and multiple airfoils circumferentially spaced within the annular region. Each corresponding airfoil of the multiple airfoils can project from a surface at a root and can further include an outer wall defining a pressure side and a suction side. A projection can extend upwardly from the surface on the pressure side and a valley can extend into the surface on the suction side to define a contour in the surface.
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公开(公告)号：US20220220854A1
公开(公告)日：2022-07-14
申请号：US17529685
申请日：2021-11-18
IPC分类号： F01D5/14
摘要： A gas turbine engine comprising a set of circumferentially adjacent airfoils, the airfoils having an outer wall defining a pressure side and a suction side extending between a leading edge and a trailing edge to define a stream-wise direction, and between a root and a tip to define a span-wise direction, and a set of dimples provide on the outer wall of at least one of the airfoils, the set of dimples spaced in at least one of the stream-wise or span-wise directions.
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公开(公告)号：US20210270137A1
公开(公告)日：2021-09-02
申请号：US17148635
申请日：2021-01-14
发明人： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
IPC分类号： F01D5/14
摘要： A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US20140298651A1
公开(公告)日：2014-10-09
申请号：US14355983
申请日：2012-11-02
申请人： GE AVIO S.r.L.
发明人： Francesco Bertini
IPC分类号： F01D5/14
CPC分类号： F01D5/141 , F01D5/145 , F05D2230/00 , Y02T50/673 , Y10T29/49336
摘要： According to the method, a turbine aerofoil is made starting from a reference aerofoil, locally reducing the metallic exit angle at the trailing edge in two areas which substantially correspond, in use, to the position of the peaks of the secondary flows in the boundary layer.
摘要翻译： 根据该方法，从基准机翼开始制造涡轮机翼，在两个区域中局部减小后缘处的金属出口角，这两个区域在使用中基本对应于边界层中次流的峰值位置 。
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公开(公告)号：US20230130213A1
公开(公告)日：2023-04-27
申请号：US17876009
申请日：2022-07-28
发明人： Ernesto Sozio , Francesco Bertini , Jeffrey Donald Clements , Jonathan Ong , Lyle Douglas Dailey , Paul Hadley Vitt , Matteo Renato Usseglio
IPC分类号： F01D5/14
摘要： A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
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公开(公告)号：US11125089B2
公开(公告)日：2021-09-21
申请号：US16534724
申请日：2019-08-07
发明人： Francesco Bertini , Aspi Rustom Wadia , Lyle D. Dailey , Andrea Arnone , Filippo Rubechini , Matteo Giovannini , Paul Hadley Vitt , Jeffrey Donald Clements
摘要： A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.
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公开(公告)号：US20200049014A1
公开(公告)日：2020-02-13
申请号：US16490416
申请日：2018-03-06
发明人： Jeffrey Donald Clements , Paul Hadley Vitt , Francesco Bertini , Aspi Rustom Wadia , Ganesh Seshadri , Mahendran Manoharan , Ravikanth Avancha
摘要： A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
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