公开(公告)号：US20180051360A1

公开(公告)日：2018-02-22

申请号：US15237976

申请日：2016-08-16

Applicant: United Technologies Corporation

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

IPC: C22C1/03 ,  C22C19/05 ,  B22D21/00 ,  B22D27/04 ,  C30B11/00 ,  C30B29/52

CPC classification number: C22C1/03 ,  B22D21/005 ,  B22D27/04 ,  C22C19/00 ,  C22C19/03 ,  C22C19/056 ,  C30B11/00 ,  C30B29/52

Abstract: A formable nickel based superalloy composition including a two phase γ/γ′ precipitation hardenable nickel base superalloy with a sum of primarily γ′ forming elements in atom % is in the range of about 10-16, forming about a 40-64 volume % of the γ′ precipitate, cast in form of a single crystal.

公开(公告)号：US09802248B2

公开(公告)日：2017-10-31

申请号：US14905904

申请日：2014-07-11

Applicant: United Technologies Corporation

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

IPC: B22D25/02 ,  B22D27/04 ,  B22D19/00 ,  B22D19/16 ,  B22C9/10 ,  B22C9/04 ,  B22C21/14 ,  B22C7/02 ,  B22C9/06 ,  B22C9/24 ,  B22D15/00 ,  B22D21/02 ,  B22D29/00

CPC classification number: B22D25/02 ,  B22C7/02 ,  B22C9/043 ,  B22C9/06 ,  B22C9/10 ,  B22C9/101 ,  B22C9/108 ,  B22C9/24 ,  B22C21/14 ,  B22D15/00 ,  B22D19/00 ,  B22D19/0072 ,  B22D19/16 ,  B22D21/025 ,  B22D27/045 ,  B22D29/00 ,  B22D29/001

Abstract: A method for casting an article comprises a first region and a second region. The method comprises casting an alloy in a shell, the shell having a casting core protruding from a first metal piece; and deshelling and decoring to remove the shell and core and leave the first region formed by the first piece and the second region formed by the casted alloy.

公开(公告)号：US20170088926A1

公开(公告)日：2017-03-30

申请号：US14867232

申请日：2015-09-28

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: C22F1/10 ,  C22C19/05

CPC classification number: C22F1/10 ,  C22C19/056

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：US20160325387A1

公开(公告)日：2016-11-10

申请号：US15211238

申请日：2016-07-15

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Edward R. Szela ,  Daniel A. Bales ,  Alan D. Cetel

IPC: B23P6/04 ,  B23K9/04 ,  B23K10/02 ,  B23K26/34 ,  B23K31/02 ,  F01D9/02 ,  C22C19/07 ,  C22C19/03 ,  C22F1/10 ,  F01D5/00 ,  F01D5/12 ,  B23K1/00 ,  B23K35/30

CPC classification number: B23P6/045 ,  B23K1/0018 ,  B23K9/04 ,  B23K10/027 ,  B23K26/34 ,  B23K31/02 ,  B23K35/3033 ,  B23K35/3046 ,  B23K2101/001 ,  B23K2103/08 ,  B23P6/007 ,  C22C19/03 ,  C22C19/057 ,  C22C19/07 ,  C22F1/10 ,  C23C4/01 ,  C23C4/18 ,  C23C28/02 ,  C23C30/00 ,  F01D5/005 ,  F01D5/12 ,  F01D5/288 ,  F01D9/02 ,  F05D2220/30 ,  F05D2230/31 ,  F05D2230/40 ,  F05D2230/80 ,  F05D2230/90 ,  F05D2300/229 ,  Y10T29/49318

Abstract: A method for repairing, refurbishing, or replacing a turbine engine component or sub-component includes the steps of providing a turbine engine component or sub-component having a site to be repaired, refurbished, or replaced providing a repair or replacement material having a sulfur content, which sulfur content is less than 10 ppm, and applying the repair or replacement material to the site on the turbine engine component to effect the repair, the refurbishment, or the replacement.

Abstract translation: 一种用于修理，翻新或更换涡轮发动机部件或子部件的方法包括提供具有待修理，翻新或替换的部位的涡轮发动机部件或子部件的步骤，提供具有硫的修复或更换材料 含量小于10ppm的含量，以及将修理或更换材料应用于涡轮发动机部件上的部位进行修理，翻新或更换。

公开(公告)号：US20160222801A1

公开(公告)日：2016-08-04

申请号：US14916310

申请日：2014-08-13

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D5/28 ,  B23K20/02 ,  F01D5/14

CPC classification number: F01D5/28 ,  B23K20/02 ,  B23K2101/001 ,  B23K2103/08 ,  F01D5/147 ,  F05D2220/32 ,  F05D2230/236 ,  F05D2240/307 ,  F05D2300/175 ,  F05D2300/607

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.

Abstract translation: 叶片（60; 60-2）包括翼型件（61）和附接根部（63）。 叶片具有尖端区域（80; 80-2; 80-2,81）和向后区域（82; 82-2,81; 82）。 根部区域具有单晶结构。 顶端区域具有单晶结构。 根部区域和向前区域的结晶取向相互之间至少为15°。

公开(公告)号：US20150328681A1

公开(公告)日：2015-11-19

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: B22D27/04 ,  B22D19/16

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.

Abstract translation: 合金部件铸造在具有部分形成腔体（292,294,296）的模具（280）中。 该方法包括将第一合金倒入模具中。 浇注原因：部件形成腔中的第一合金的表面（550）相对于部件形成腔体升高; 倾倒的第一合金的分支流向上通过通道的第一部分（304）; 并且所述分支流向下通过所述通道的第二部分（310）; 固化通道中的一些第一合金以阻挡通道，同时部件形成空腔中的至少一些第一合金保持熔融。 将第二合金倒入第一合金顶部的模具中并固化。

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.