公开(公告)号：US20160040284A1

公开(公告)日：2016-02-11

申请号：US14810767

申请日：2015-07-28

Applicant: United Technologies Corporation

Inventor： Dmitri Novikov ,  Sergei F. Burlatsky ,  David Ulrich Fuller ,  David A. Litton

IPC: C23C14/54 ,  F01D25/00 ,  C23C14/24

CPC classification number: C23C14/54 ,  C23C14/228 ,  C23C14/243 ,  F01D25/005

Abstract: A method or control strategy in a coating apparatus for use in a coating process can include controlling differential gas pressures among multiple selected localized zones in a coating chamber with respect to each other. The controlled differential gas pressure of the multiple selected localized zones is used to influence how a coating deposits on at least one component. The localized zones can be selected from a first localized zone around the component, a second localized zone adjacent the source of coating material, a third localized zone that diverges from the second localized zone toward the first localized zone, and a fourth localized zone that circumscribes at least the third localized zone

Abstract translation: 在涂覆工艺中使用的涂覆装置中的方法或控制策略可以包括控制涂覆室中相对于彼此的多个选定局部区域中的差分气体压力。 多个选定的局部区域的受控差压气体压力用于影响涂层如何沉积在至少一个部件上。 局部区域可以从组件周围的第一局部区域，与涂层材料源相邻的第二局部区域，从第二局部区域向第一局部区域分叉的第三局部区域以及第四局部区域选择， 至少第三个本地化区域

公开(公告)号：US20160024955A1

公开(公告)日：2016-01-28

申请号：US14775927

申请日：2013-12-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Shahram Amini ,  Christopher W Strock ,  Sergei F Burlatsky ,  Dmitri Novikov ,  David Ulrich Fuller

IPC: F01D11/12 ,  F01D9/04 ,  B23K1/00 ,  B23K1/19 ,  C23C24/04 ,  B23K20/22 ,  B23K26/34 ,  B23K26/00 ,  C23C4/12 ,  F01D5/28 ,  B23K20/02

CPC classification number: F01D11/122 ,  B23K1/0006 ,  B23K1/19 ,  B23K20/02 ,  B23K20/22 ,  B23K26/0006 ,  B23K26/34 ,  B23K2103/16 ,  C23C4/04 ,  C23C4/134 ,  C23C24/04 ,  F01D5/288 ,  F01D9/041 ,  F01D11/12 ,  F01D11/20 ,  F05D2220/30 ,  F05D2230/236 ,  F05D2230/237 ,  F05D2230/312 ,  F05D2230/60 ,  F05D2230/90 ,  F05D2240/125 ,  F05D2240/307 ,  F05D2300/6032

Abstract: A turbine engine system includes a turbine engine component having an airfoil portion and a tip, which turbine engine component having a MAXMET composite bonded to the tip. The MAXMET composite has MAX phases in a metal matrix.

Abstract translation: 涡轮发动机系统包括具有翼型部分和尖端的涡轮发动机部件，该涡轮发动机部件具有结合到尖端的MAXMET复合材料。 MAXMET复合材料在金属基体中具有MAX相。