-
公开(公告)号：US11131314B2
公开(公告)日：2021-09-28
申请号：US15265294
申请日：2016-09-14
Applicant: United Technologies Corporation
Inventor： David A. Welch
Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.
-
公开(公告)号：US10562100B2
公开(公告)日：2020-02-18
申请号：US15226147
申请日：2016-08-02
Applicant: United Technologies Corporation
Inventor： David A. Welch
Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.
-
公开(公告)号：US20180073519A1
公开(公告)日：2018-03-15
申请号：US15265294
申请日：2016-09-14
Applicant: United Technologies Corporation
Inventor： David A. Welch
IPC: F04D29/38
CPC classification number: F04D29/023 , F01D5/147 , F01D5/28 , F04D29/324 , F05D2220/36 , F05D2250/11 , F05D2300/612
Abstract: An airfoil includes a leading edge, a trailing edge, a pressure side extending between the leading and the trailing edge, and a suction side that is disposed opposite the pressure side extending between the leading edge and the trailing edge. The airfoil further includes a spar and a structural member. The spar defines the leading edge. The structural member is bonded to the spar.
-
公开(公告)号：US09702375B2
公开(公告)日：2017-07-11
申请号：US14322527
申请日：2014-07-02
Applicant: United Technologies Corporation
Inventor： Mark W. Costa , Thomas J. Robertson, Jr. , David A. Welch
CPC classification number: F04D29/526 , F01D11/18 , F01D25/246 , F02C7/045 , F04D29/644 , F05D2230/642 , Y02T50/672 , Y10T29/49229
Abstract: A gas turbine engine includes a liner disposed around a flowpath. The liner has a forward end, a radially outer surface, and a radially inner surface. A hole extends axially into the forward end of the liner between the radially outer surface and the radially inner surface, and an engagement member is partially disposed in the hole and extends axially forward from the forward end of the liner.
-
15.发明申请公开(公告)号：US20160032833A1
公开(公告)日：2016-02-04
申请号：US14774035
申请日：2014-03-12
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Thomas J. Robertson, JR. , Mark W. Costa , David A. Welch
IPC: F02C7/045
Abstract: A cartridge for a fan case of a gas turbine engine includes an inlet acoustic liner section integrated with a thermally conforming liner section.
Abstract translation: 用于燃气涡轮发动机的风扇壳体的盒包括与热适应衬套部分一体化的入口声学衬垫部分。
-
Patent Agency Ranking
公开(公告)号：US11156100B2
公开(公告)日：2021-10-26
申请号：US16209448
申请日：2018-12-04
Applicant: United Technologies Corporation
Inventor： David A. Welch
Abstract: A blade fabrication method is provided and includes additively manufacturing a core, securing the core to a mandrel, electroforming a leading edge sheath directly onto the core and the mandrel and removing the mandrel from the core and the leading edge sheath.
-
公开(公告)号：US11136888B2
公开(公告)日：2021-10-05
申请号：US16163690
申请日：2018-10-18
Applicant: United Technologies Corporation
Inventor： Jason Husband , James Glaspey , David A. Welch
Abstract: An airfoil for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil section that extends from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction. The airfoil section defines a pressure side and a suction side separated in a thickness direction, and the airfoil section includes a metallic sheath that defines an internal cavity receiving a composite core. The root section defines at least one bore dimensioned to receive a retention pin. At least one damping element is received in the internal cavity and that selectively causes the airfoil section to stiffen.
-
公开(公告)号：US10730112B2
公开(公告)日：2020-08-04
申请号：US15226147
申请日：2016-08-02
Applicant: United Technologies Corporation
Inventor： David A. Welch
Abstract: A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body.
-
公开(公告)号：US10208709B2
公开(公告)日：2019-02-19
申请号：US15091066
申请日：2016-04-05
Applicant: United Technologies Corporation
Inventor： David A. Welch
Abstract: A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.
-
公开(公告)号：US20170284202A1
公开(公告)日：2017-10-05
申请号：US15091066
申请日：2016-04-05
Applicant: United Technologies Corporation
Inventor： David A. Welch
CPC classification number: F02K3/06 , F01D5/3007 , F01D5/3023 , F01D5/3053 , F01D5/323 , F01D5/326 , F02C7/04 , F04D29/322 , F04D29/644 , F05D2220/36 , F05D2230/70
Abstract: A gas turbine engine includes a fan forward of a primary flowpath inlet. The fan includes multiple fan blades distributed radially about, and connected to, a hub. A fan nacelle is positioned radially outward of the fan and includes an inner diameter. The inner diameter is sloped relative to an engine axis such that a forward portion of the fan nacelle has a smaller inner diameter than an aft portion of the fan nacelle. A fan blade spacer is disposed between a radially inward facing surface of at least one fan blade and a radially outward facing surface of the hub. The fan blade spacer has a radial thickness at least equal to a slope drop of the fan nacelle.
-
-
-
-
-
-
-
-
-
Search Results
21
records
(took 0.038 seconds)
