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。

公开(公告)号：US12083625B2

公开(公告)日：2024-09-10

申请号：US16839753

申请日：2020-04-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Xiaomei Fang ,  Christopher J. Hertel ,  John D. Riehl ,  John W. Connell ,  Frank L. Palmieri ,  John W. Hopkins

IPC: B23K26/359 ,  B23K26/0622 ,  B23K103/04

CPC classification number: B23K26/359 ,  B23K26/0622 ,  B23K2103/05

Abstract: Methods and systems for the laser surface treatment on stainless steel alloys and nickel alloys may include a computer may be programmed to set a laser path corresponding to a predetermined geometric pattern. A laser may be coupled to the computer and apply a pulsed laser beam to a contact surface of the substrate along the predefined geometric pattern. The pulsed laser beam may have a laser power between 0.1 W and 100 W, single pulse fluence 1 mJ/mm2 and 1025 mJ/mm2 and a laser speed between 25.4 cm/s and 127 cm/s. The laser may generate an open pore oxide layer on the contact surface of the substrate with a thickness of 0.1-1 μm, an open pore distance of 0.05-1 μm. The open pore oxide layer may have a topography corresponding to the predefined geometric pattern. The topography may contain open pore structures and promote adhesive bond performance.

公开(公告)号：US20190218914A1

公开(公告)日：2019-07-18

申请号：US15874477

申请日：2018-01-18

Applicant: United Technologies Corporation

Inventor： James O. Hansen ,  William R. Graves ,  Michael A. Weisse ,  Christopher J. Hertel ,  Daniel A. Bales

IPC: F01D5/14 ,  F01D5/28 ,  F02K3/06

Abstract: A fan of a gas turbine engine includes a plurality of fan blades secured to a rotor, each of the plurality of fan blades having an airfoil secured to the rotor at one end, wherein the airfoil comprises pockets filled with an elastomeric composite.

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

IPC: F01D5/14 ,  C25D1/00 ,  C25D1/02 ,  F04D29/32

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.

公开(公告)号：US10087948B2

公开(公告)日：2018-10-02

申请号：US14673287

申请日：2015-03-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee Drozdenko ,  James O. Hansen ,  Christopher J. Hertel ,  Steven T. Holland

IPC: F01D5/30 ,  F04D29/34 ,  B05D1/02 ,  B05D1/18 ,  B29C65/66 ,  F04D19/00 ,  F04D29/02 ,  F04D29/38 ,  B29K63/00 ,  B29K105/06 ,  B29L31/08

Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.

公开(公告)号：US20160290356A1

公开(公告)日：2016-10-06

申请号：US14673287

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Lee Drozdenko ,  James O. Hansen ,  Christopher J. Hertel ,  Steven T. Holland

IPC: F04D29/34 ,  F04D29/38 ,  B29C65/66 ,  B05D1/18 ,  B05D1/02 ,  F04D19/00 ,  F04D29/02

CPC classification number: F04D29/34 ,  B05D1/02 ,  B05D1/18 ,  B29C65/66 ,  B29K2063/00 ,  B29K2105/06 ,  B29L2031/082 ,  F01D5/3092 ,  F04D19/002 ,  F04D29/023 ,  F04D29/388 ,  F05D2220/36

Abstract: A fan blade and method of covering a fan blade root portion for a gas turbine engine are disclosed. The fan blade includes an airfoil having a leading edge end and a trailing edge end, a root portion having a first side surface extending from the leading edge end to the trailing edge end and a second side surface at an opposite side of the first side surface and extending from the leading edge end to the trailing edge end, and a covering disposed against the first side surface and the second side surface, wherein the covering is positioned against the root portion as a single member.

Abstract translation: 公开了一种风扇叶片和覆盖燃气轮机的风扇叶片根部的方法。 风扇叶片包括具有前缘端部和后缘端部的翼型件，根部部分具有从前缘端部延伸到后缘端部的第一侧表面和在第一侧表面的相对侧的第二侧表面 并且从所述前缘端延伸到所述后缘端部，以及覆盖物，其抵靠所述第一侧表面和所述第二侧表面设置，其中所述覆盖物作为单个构件抵靠所述根部部分定位。