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公开(公告)号：US20150184306A1
公开(公告)日：2015-07-02
申请号：US14644954
申请日：2015-03-11
Applicant: United Technologies Corporation
Inventor： Joseph Parkos, Jr. , James O. Hansen , Christopher J. Hertel , Andrew J. Murphy , Ashley P. Phillips , Jay Thomas Abraham
IPC: C25D1/00
CPC classification number: C25D1/00 , C25D1/02 , F01D5/147 , F04D29/324 , F05D2230/30 , F05D2230/90 , F05D2240/303 , F05D2300/603
Abstract: An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.
Abstract translation: 用于保护翼型的电铸护套包括护套主体和心轴插入件。 护套主体包括前缘。 护套主体包括压力侧壁和相对的吸力侧壁，侧壁在前缘相交并且远离前缘延伸以在侧壁之间限定空腔。 护套主体包括在前缘和腔之间的头部。 心轴插入件位于压力侧和吸力侧壁之间，并且包括大致楔形的几何形状。 一种用于保护翼型件的方法包括：1）将心轴插入件固定到心轴上; 2）将护套主体电镀到心轴和心轴插入件上; 3）从护套主体中取出心轴，使得护套空腔限定在护套主体内; 和4）将翼型件固定在护套腔内。
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公开(公告)号：US10781827B1
公开(公告)日：2020-09-22
申请号：US15872171
申请日：2018-01-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Jason Elliott , Daniel C. Falk , Myron L. Klein , Ethan C. Drew , James H. Moffitt , Darryl Whitlow , Byron R. Monzon , Jay Thomas Abraham , William R. Graves
Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 27.5-28.5 inches (699-724 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 13.0-14.0 inches (330-356 mm). The airfoil element includes at least two of a first mode with a frequency of 34±10% Hz, a second mode with a frequency of 90±10% Hz, a third mode with a frequency of 178±10% Hz, a fourth mode with a frequency of 222±10% Hz, a fifth mode with a frequency of 307±10% Hz and a sixth mode with a frequency of 389±10% Hz.
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公开(公告)号：US10294573B2
公开(公告)日：2019-05-21
申请号：US14644954
申请日：2015-03-11
Applicant: United Technologies Corporation
Inventor： Joseph Parkos, Jr. , James O. Hansen , Christopher J. Hertel , Andrew J. Murphy , Ashley P. Phillips , Jay Thomas Abraham
Abstract: An electroformed sheath for protecting an airfoil includes a sheath body and a mandrel insert is provided. The sheath body includes a leading edge. The sheath body includes a pressure side wall and an opposed suction side wall, which side walls meet at the leading edge and extend away from the leading edge to define a cavity between the side walls. The sheath body includes a head section between the leading edge and the cavity. The mandrel insert is positioned between the pressure side and suction side walls, and includes a generally wedge-shaped geometry. A method for protecting an airfoil includes: 1) securing a mandrel insert to a mandrel; 2) electroplating a sheath body onto the mandrel and the mandrel insert; 3) removing the mandrel from the sheath body so that a sheath cavity is defined within the sheath body; and 4) securing the airfoil within the sheath cavity.
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公开(公告)号：US20180202299A1
公开(公告)日：2018-07-19
申请号：US15408882
申请日：2017-01-18
Applicant: United Technologies Corporation
Inventor： James R. Murdock , James H. Moffitt , Scot A. Webb , Jay Thomas Abraham , Maria C. Kirejczyk
CPC classification number: F01D5/28 , F01D5/3092 , F04D29/023 , F05D2220/323 , F05D2220/36 , F05D2230/60 , F05D2240/303 , F05D2260/95 , F05D2300/121 , F05D2300/125 , F05D2300/133 , F05D2300/1616 , F05D2300/50 , Y02T50/671
Abstract: A blade for a gas turbine engine. The blade having: an airfoil formed from a first material; a protective sheath disposed on a leading edge of the airfoil, the protective sheath being formed from a second material, the first material being galvanically incompatible with the second material and the first material being less noble than the second material; a non-conductive material disposed between the protective sheath and the airfoil so that they are electrically isolated from each other; a sacrificial anode in contact with the blade, wherein the sacrificial anode is formed from a third material that is less noble than the first material such that it will corrode before the first material if the non-conductive material disposed between the protective sheath and the airfoil is compromised and the first material and the second material are no longer electrically isolated from each other.
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