公开(公告)号：US10287896B2

公开(公告)日：2019-05-14

申请号：US14916310

申请日：2014-08-13

Applicant: United Technologies Corporation

Inventor： John J. Marcin, Jr. ,  Steven J. Bullied ,  Dilip M. Shah ,  Alan D. Cetel

IPC: F01D5/28 ,  F01D5/14 ,  B23K20/02 ,  B23K101/00 ,  B23K103/08

Abstract: A blade (60; 60-2) comprises an airfoil (61) and an attachment root (63). The blade has a tipward zone (80; 80-2; 80-2, 81) and a rootward zone (82; 82-2, 81; 82). The rootward zone has a single crystal structure. The tipward zone has a single crystal structure. The crystalline orientations of the rootward zone and tipward zone are at least 15° out of registry with each other.

公开(公告)号：US20170306782A1

公开(公告)日：2017-10-26

申请号：US15137503

申请日：2016-04-25

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Katelyn Kwoka ,  Alan D. Cetel ,  Venkatarama K. Seetharaman ,  Michael G. McCaffrey

IPC: F01D11/08 ,  F01D5/12 ,  F01D25/00 ,  F01D25/12 ,  F01D9/04 ,  F01D11/00

CPC classification number: F01D11/08 ,  F01D5/12 ,  F01D9/041 ,  F01D11/005 ,  F01D25/005 ,  F01D25/12 ,  F05D2220/32 ,  F05D2230/00 ,  F05D2240/56 ,  F05D2300/175 ,  F05D2300/177 ,  F05D2300/506 ,  F16J15/3288 ,  F16J15/3292

Abstract: An embodiment of a turbine assembly includes, among other possible things, a first component including a first component surface, a second component including a second component surface spaced apart from the first component surface, and a brush seal disposed between the first component and the second component. The brush seal includes, among other things, a first bristled region extending in a first direction from a backing plate, and sealingly engaging one of the first component surface and the second component surface. At least one of the backing plate and the first bristled region includes a nickel-based superalloy material having at least 40% of a Ni3(Al,X) precipitate phase, X being a metallic or refractory element other than Al.

公开(公告)号：US20170259330A1

公开(公告)日：2017-09-14

申请号：US15605087

申请日：2017-05-25

Applicant: United Technologies Corporation

Inventor： Steven J. Bullied ,  Dilip M. Shah ,  Alan D. Cetel ,  John J. Marcin

IPC: B22D19/16 ,  B22D27/04 ,  F01D5/14

CPC classification number: B22D19/16 ,  B22D27/045 ,  F01D5/147 ,  F05D2230/211

Abstract: An alloy part is cast in a mold (280) having a part-forming cavity (292, 294, 296). The method comprises pouring a first alloy into the mold. The pouring causes: a surface (550) of the first alloy in the part-forming cavity to raise relative to the part-forming cavity; a branch flow of the poured first alloy to pass upwardly through a first portion (304) of a passageway; and the branch flow to pass downwardly through a second portion (310), of the passageway; solidifying some of the first alloy in the passageway to block the passageway while at least some of the first alloy in the part-forming cavity remains molten. A second alloy is poured into the mold atop the first alloy and solidified.

公开(公告)号：US09687910B2

公开(公告)日：2017-06-27

申请号：US14651926

申请日：2013-12-13

Applicant: United Technologies Corporation

Inventor： Steven J. Bullied ,  Dilip M. Shah ,  Alan D. Cetel ,  John J. Marcin

IPC: B22D19/16 ,  B22D27/04

CPC classification number: B22D19/16 ,  B22D27/045 ,  F01D5/147 ,  F05D2230/211

Abstract: An alloy part is cast in a mold (280) having a part forming cavity (292, 294, 296). The method comprises pouring a first alloy into the mold. The pouring causes: a surface (550) of the first alloy in the part forming cavity to raise relative to the part forming cavity; a branch flow of the poured first alloy to pass upwardly through a first portion (304) of a passageway; and the branch flow to pass downwardly through a second portion (310), of the passageway; solidifying some of the first alloy in the passageway to block the passageway while at least some of the first alloy in the part forming cavity remains molten. A second alloy is poured into the mold atop the first alloy and solidified.

公开(公告)号：US20150321249A1

公开(公告)日：2015-11-12

申请号：US14651911

申请日：2013-12-13

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Dilip M. Shah ,  Alan D. Cetel

IPC: B22D25/02 ,  B22D21/06 ,  C22C19/05 ,  F01D5/28

CPC classification number: B22D25/02 ,  B22D19/16 ,  B22D21/025 ,  B22D21/06 ,  B22D27/045 ,  C22C19/057 ,  F01D5/14 ,  F01D5/147 ,  F01D5/28 ,  F05D2220/30 ,  F05D2230/21 ,  F05D2230/211 ,  F05D2300/131 ,  F05D2300/132 ,  F05D2300/133 ,  F05D2300/135 ,  F05D2300/17 ,  F05D2300/606 ,  F05D2300/609 ,  Y10T403/478

Abstract: A method is provided for casting an article such as a blade having an attachment root and an airfoil, the airfoil having a proximal end and a distal end. The method comprises introducing a molten alloy into a mold; and varying a composition of the introduced alloy during the introduction so as to produce a compositional variation.

Abstract translation: 提供了一种用于铸造诸如具有附接根部和翼型的叶片的制品的方法，所述翼型件具有近端和远端。 该方法包括将熔融合金引入模具中; 并且在引入期间改变引入的合金的组成以产生组成变化。

公开(公告)号：US20150075745A1

公开(公告)日：2015-03-19

申请号：US14488169

申请日：2014-09-16

Applicant: United Technologies Corporation

Inventor： John J. Marcin, JR. ,  Steven J. Bullied ,  Dilip M. Shah ,  Alan D. Cetel ,  Emily K. Kreek

IPC: B22D46/00 ,  B22C9/02

CPC classification number: B22D46/00 ,  B22C9/04 ,  B22D2/006 ,  B22D27/045 ,  B22D30/00

Abstract: A casting mold (260) comprises a shell (262) extending from a lower end (264) to an upper end (266) and having: an interior space (280) for casting metal; and an opening (268) for receiving metal to be cast. A plurality of thermocouples (900) are vertically-spaced from each other on the shell.

Abstract translation: 铸模（260）包括从下端（264）延伸到上端（266）的壳体（262），并且具有：用于铸造金属的内部空间（280）; 以及用于接收待铸造金属的开口（268）。 多个热电偶（900）在壳体上彼此垂直间隔开。

公开(公告)号：US20200088040A1

公开(公告)日：2020-03-19

申请号：US16131451

申请日：2018-09-14

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Alan D. Cetel ,  Venkatarama K. Seetharaman

IPC: F01D5/14 ,  B21J5/00 ,  B21J5/02 ,  B23P15/02 ,  C21D9/00 ,  C22F1/10 ,  F01D5/30

Abstract: A method for manufacturing a blade, the method includes casting a nickel alloy blade precursor having an airfoil and a root. The airfoil and the root are solution heat treating differently from each other. After the solution heat treating, the root is wrought processed. After the wrought processing, an exterior of the root is machined.

公开(公告)号：US20200024716A1

公开(公告)日：2020-01-23

申请号：US16214715

申请日：2018-12-10

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Alan D. Cetel ,  Venkatarama K. Seetharaman

IPC: C22F1/10 ,  C22C19/05

Abstract: A process includes solution heat treating a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate to dissolve the gamma prime precipitate in the nickel based superalloy; cooling the nickel based superalloy to about 85% of a solution temperature measured on an absolute scale to coarsen the gamma prime precipitate such that a precipitate structure is greater than about 0.7 micron size; and wrought processing the nickel based superalloy at a temperature below a recrystallization temperature of the nickel based superalloy. A material includes a nickel based superalloy with greater than about 40% by volume of gamma prime precipitate in which the precipitate structure is greater than about 0.7 micron size.

公开(公告)号：US10465545B2

公开(公告)日：2019-11-05

申请号：US15980855

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： Alan D. Cetel ,  Dilip M. Shah ,  Eric A. Hudson ,  Raymond Surace

IPC: F01D11/00 ,  F01D25/00

Abstract: Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.

公开(公告)号：US20190292920A1

公开(公告)日：2019-09-26

申请号：US15934332

申请日：2018-03-23

Applicant: United Technologies Corporation

Inventor： Dilip M. Shah ,  Alan D. Cetel ,  Venkatarama K. Seetharaman ,  Raymond Surace

IPC: F01D5/18

Abstract: A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.