公开(公告)号：US20170291367A1

公开(公告)日：2017-10-12

申请号：US15441630

申请日：2017-02-24

Applicant: United Technologies Corporation

Inventor： Sergei F. Burlatsky ,  Dmitri Novikov ,  William J. Brindley ,  David Ulrich Furrer

IPC: B29C67/00 ,  G05B19/042 ,  B33Y30/00 ,  B33Y50/02 ,  B33Y10/00

CPC classification number: B33Y10/00 ,  B29C64/153 ,  B29C64/386 ,  B29C67/00 ,  B33Y30/00 ,  B33Y50/00 ,  B33Y50/02 ,  G05B19/0426 ,  G05B2219/49023 ,  G06F17/5086 ,  G06F2217/12 ,  Y02P90/265

Abstract: A method of evaluating and validating additive manufacturing operations includes generating a multidimensional space defined by a plurality of bounds, each of the bounds being defined on a distinct parameter of an additive manufacturing process and each of the parameters affecting the occurrence of a keyhole porosity flaw, each of the parameters being a dimension in a multi-dimensional coordinate system, determining a coordinate position of at least one additive manufacturing operation within the multi-dimensional coordinate system, and categorizing the operation as free of keyhole porosity flaws when the coordinate position is within the multi-dimensional space.

公开(公告)号：US20160305255A1

公开(公告)日：2016-10-20

申请号：US15100663

申请日：2014-11-19

Applicant: United Technologies Corporation

Inventor： Iuliana Cernatescu ,  Thomas J. Watson ,  James O. Hansen ,  David Ulrich Furrer ,  Randy P. Salva

IPC: F01D5/28 ,  C30B29/52 ,  F01D5/14

CPC classification number: F01D5/28 ,  C30B29/52 ,  F01D5/147 ,  F05D2220/36 ,  F05D2250/74 ,  F05D2300/173 ,  F05D2300/605 ,  F05D2300/606 ,  Y02T50/673

Abstract: An airfoil includes an airfoil body that extends at least between leading and trailing edges, first and second sides, and radially inner and outer ends. The airfoil body includes an aluminum alloy that has a controlled crystallographic texture with respect to a predefined three-dimensional coordinate system. The airfoil can be used in the fan of a gas turbine engine.

Abstract translation: 翼型件包括至少在前缘和后缘之间延伸的翼型件本体，第一和第二侧以及径向内端和外端。 翼型体包括相对于预定义的三维坐标系具有受控的结晶组织的铝合金。 翼型可用于燃气轮机的风扇。

公开(公告)号：US20160238021A1

公开(公告)日：2016-08-18

申请号：US14623245

申请日：2015-02-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： David Ulrich Furrer ,  Christopher W. Strock ,  Joseph G. Hillebrand ,  Matthew E. Bintz ,  Thomas D. Kasprow

IPC: F04D29/32 ,  F04D29/02

CPC classification number: F04D29/324 ,  F01D5/20 ,  F01D5/288 ,  F04D29/023 ,  F05D2230/90 ,  F05D2240/303 ,  F05D2240/304 ,  F05D2240/307 ,  F05D2300/611 ,  Y02T50/672 ,  Y02T50/673

Abstract: A compressor airfoil has a leading edge, a trailing edge, and a radially outboard edge connecting the leading edge and the trailing edge. The leading edge is formed according to a leading edge tip profile and the trailing edge is formed according to a trailing edge tip profile. The leading edge tip profile and/or trailing edge tip profile has a chamfer and/or a radius. In this manner, contact stress experienced by the compressor airfoil such as upon contact with a surrounding abradable seal are ameliorated. The leading edge tip profile and/or trailing edge tip profile are coated with an abrasive coating such as to enhance fitting of the abradable seal to the path of the compressor airfoil upon such contact.

Abstract translation: 压缩机翼型件具有连接前缘和后缘的前缘，后缘和径向外侧边缘。 前缘是根据前缘尖端轮廓形成的，后缘根据后缘尖端轮廓形成。 前缘末端轮廓和/或后缘末端轮廓具有倒角和/或半径。 以这种方式，可以改善压缩机翼型的接触应力，例如与周围的可磨损密封件接触时的接触应力。 引导边缘末端轮廓和/或后缘末端轮廓涂覆有磨料涂层，以便在这种接触时增强可磨损密封件与压缩机翼型件的路径的配合。

公开(公告)号：US20160024925A1

公开(公告)日：2016-01-28

申请号：US14774923

申请日：2013-12-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： D. Slade Stolz ,  David Ulrich Furrer ,  Samir V Patel ,  Raymond C Benn ,  Alan D Cetel

IPC: F01D5/00 ,  F01D5/12 ,  F01D5/30 ,  F01D5/02

CPC classification number: F01D5/005 ,  B23P6/002 ,  B23P6/04 ,  B23P6/045 ,  F01D5/02 ,  F01D5/12 ,  F01D5/3007 ,  F01D5/3023 ,  F05D2230/10 ,  F05D2230/12 ,  F05D2230/14 ,  F05D2230/80 ,  F05D2240/20 ,  Y10T29/49318

Abstract: A process for rejuvenating a turbine disk having a plurality of slots includes the steps of determining a depth of a damaged layer containing M23C6 carbide dissolution; and removing the damaged layer from the slots in accordance with the determined depth.

Abstract translation: 一种用于使具有多个槽的涡轮盘再生的方法包括以下步骤：确定含有M23C6碳化物溶解的损伤层的深度; 并根据确定的深度从槽中去除损坏的层。