公开(公告)号：US20150138342A1

公开(公告)日：2015-05-21

申请号：US14522793

申请日：2014-10-24

Applicant: United Technologies Corporation

Inventor： Christopher R. Brdar ,  Patrick Hinckley ,  Brian London ,  Larry R. Breen ,  Anita Rebarchak ,  Alan Matthew Finn ,  Chelsea Barr ,  Roger Neama ,  Michael Li

IPC: G01B11/28 ,  G01N21/88

CPC classification number: G01B11/285 ,  G01M5/0016 ,  G01M5/0033 ,  G01N21/8422 ,  G01N21/8851 ,  G01N2021/8874 ,  G01N2201/06113 ,  G01N2201/12

Abstract: A method of calculating an amount of visible damage on a component includes capturing an image of the component, identifying an area of visible damage, calculating a size of the area, and communicating the size of visible damage to a storage device. A system for evaluating coating loss is also disclosed.

Abstract translation: 计算组件上的可见损伤量的方法包括捕获部件的图像，识别可见损伤的区域，计算区域的尺寸，以及将可见损伤的大小传达到存储装置。 还公开了一种评估涂层损失的系统。

公开(公告)号：US20160273391A1

公开(公告)日：2016-09-22

申请号：US15029525

申请日：2014-09-04

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Steven W. Burd ,  Christopher R. Brdar ,  Derk S. Philippona

IPC: F01D25/30 ,  F01D25/14

Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.

Abstract translation: 用于燃气涡轮发动机的部件包括具有基板孔的基板和在基板上延伸一定长度的基板孔的涂层。 用于燃气涡轮发动机的衬套组件包括具有多个孔的热板和在热片上的涂层，其延伸多个孔的每一个的长度。 一种形成用于在燃气涡轮发动机的部件中提供膜冷却的孔的方法包括在基板中形成多个基板孔。 多个基板孔中的每一个限定基板内周边。 在形成多个基板孔之后，在基板上施加涂层以至少部分地在多个基板孔内的每一个中限定涂层内周边。 涂层内周面小于基板内周。

公开(公告)号：US10704424B2

公开(公告)日：2020-07-07

申请号：US15029525

申请日：2014-09-04

Applicant: United Technologies Corporation

Inventor： Steven W. Burd ,  Christopher R. Brdar ,  Derk S. Philippona

IPC: F01D25/30 ,  F01D25/14 ,  F02K1/82 ,  F02C7/12

Abstract: A component for a gas turbine engine includes a substrate with a substrate aperture and a coating on the substrate that extends a length of the substrate aperture. A liner assembly for a gas turbine engine includes a hot sheet with a multiple of apertures and a coating on the hot sheet that extends a length of each of the multiple of apertures. A method of forming an aperture to provide film cooling in a component of a gas turbine engine, includes forming a multiple of substrate apertures in a substrate. Each of the multiple of substrate apertures defines a substrate inner periphery. A coating is applied on the substrate after forming the multiple of substrate apertures to define a coating inner periphery at least partially within each of the multiple of substrate apertures. The coating inner periphery is smaller than the substrate inner periphery.