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：US10012238B2

公开(公告)日：2018-07-03

申请号：US14695178

申请日：2015-04-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Thomas J. Robertson ,  James O. Hansen ,  Mark Quinn

IPC: F04D29/00 ,  F04D29/38 ,  F01D5/14 ,  F01D5/28 ,  F01D5/30

CPC classification number: F04D29/388 ,  F01D5/147 ,  F01D5/288 ,  F01D5/3015 ,  F01D5/3092 ,  F05D2220/36 ,  F05D2300/50 ,  Y02T50/672

Abstract: A fan blade capable of dissipating a buildup of electrostatic charge configured for operation within the fan assembly of a gas turbine engine. The fan blade has a fan blade body covered in a static dissipative coating. A conductive ground tab is attached to the front face of an airfoil root of the fan blade. Connected to the ground tab, a conductive flow path travels up the neck portion of the airfoil and along a lower portion of the fan blade. As static charge builds up on the fan blade, the electrostatic charge migrates down the fan blade and into the conductive flow path. Traveling along the conductive flow path the buildup of electrostatic charge accumulates on the conductive ground tab and exits the fan blade through contact with a disc rotor covering touching the conductive ground tab.

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。

公开(公告)号：US20160215784A1

公开(公告)日：2016-07-28

申请号：US14917485

申请日：2014-08-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee M. Drozdenko ,  James O. Hansen ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Jesse C. Meyer ,  Brandon A. Gates ,  Richard B. Bergethon ,  Michael A. Morden

IPC: F04D29/02 ,  F04D29/32 ,  F04D29/64 ,  F04D29/38

CPC classification number: F04D29/023 ,  F01D5/288 ,  F04D29/324 ,  F04D29/325 ,  F04D29/388 ,  F04D29/644 ,  F05D2240/303 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/6033

Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.

Abstract translation: 翼型件（100）包括沿翼型件的翼型（102）的至少一部分具有基底（120）。 护套（122）具有容纳衬底的一部分（160）的通道（144）。 稀松布（200）在基材和护套之间。 间隔物（220）位于护套和衬底之间并且具有多个间隔开的部分（232,234），其间隔开间隔开的部分。

公开(公告)号：US20160201482A1

公开(公告)日：2016-07-14

申请号：US14915964

申请日：2014-09-02

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Joseph Parkos, Jr. ,  James O. Hansen ,  Jesse C. Meyer

IPC: F01D5/28 ,  C23F1/00

CPC classification number: F01D5/286 ,  C23F1/00 ,  F01D5/28 ,  F01D5/288 ,  F04D29/324 ,  F05D2220/32 ,  F05D2220/36 ,  F05D2230/20 ,  F05D2240/30 ,  F05D2240/303 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2300/121 ,  F05D2300/133 ,  Y02T50/672 ,  Y02T50/673

Abstract: An airfoil includes an aluminum airfoil body with a pressure side, suction side, leading edge and trailing edge; and a titanium foil layer covering at least part of one of the pressure side and the suction side.

Abstract translation: 机翼包括具有压力侧的铝翼型本体，吸力侧，前缘和后缘; 以及覆盖压力侧和吸入侧中的一方的至少一部分的钛箔层。

公开(公告)号：US11156104B2

公开(公告)日：2021-10-26

申请号：US16255976

申请日：2019-01-24

Applicant: United Technologies Corporation

Inventor： Jesse C. Meyer ,  Joseph Jalowka ,  John D. Riehl ,  Raymond P. Martina ,  James O. Hansen

IPC: F01D5/28 ,  C09J5/02 ,  C09J5/04 ,  C09J5/06 ,  B32B15/04 ,  C22C21/00

Abstract: The present disclosure provides methods and systems for the bonding of dissimilar substrates. For example, a first substrate may be coupled to a second substrate by a composite joint between the first substrate and the second substrate. The composite joint may be comprised of a first adhesive material and a second adhesive material. The first adhesive material may be disposed on the first substrate, and the second adhesive material may be disposed to the first adhesive material. The composite joint between the first substrate and the second substrate may provide an isolation layer therebetween, preventing galvanic corrosion.

公开(公告)号：US10982683B2

公开(公告)日：2021-04-20

申请号：US15039929

申请日：2014-11-25

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Lee Drozdenko ,  James O. Hansen ,  Jesse C. Meyer ,  Maria C. Kirejczyk ,  Scot A. Webb ,  Brandon A. Gates ,  Richard B. Bergethon

IPC: F04D29/38 ,  B32B7/12 ,  F01D5/28 ,  F01D5/14 ,  F01D5/12 ,  B32B5/02 ,  B32B15/14 ,  B32B15/20 ,  F04D29/02 ,  F04D29/32

Abstract: A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed.

公开(公告)号：US10704127B2

公开(公告)日：2020-07-07

申请号：US15075795

申请日：2016-03-21

Applicant: United Technologies Corporation

Inventor： John Richard Palitsch ,  James O. Hansen ,  Nicolas Figueiredo ,  Daniel Gynther ,  Stephen E. Graushinsky ,  John H. Nortrup

IPC: C22F1/04 ,  B21H7/16 ,  F01D5/28 ,  F01D5/30

Abstract: A method of forming an airfoil includes placing a material onto a die that is heated to a predetermined temperature to pre-heat the material to a first temperature, while the die is in an open position. The method further includes closing the die at a predetermined rate and holding the die in a closed position for a predetermined period of time at a first force. The method still further includes removing the part from the die, cooling the die, placing the part onto the die, and closing the die at a second force.

公开(公告)号：US10677068B2

公开(公告)日：2020-06-09

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 ,  B23P15/04 ,  F01D5/16

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.