公开(公告)号：US20190086336A1

公开(公告)日：2019-03-21

申请号：US15706958

申请日：2017-09-18

Applicant: United Technologies Corporation

Inventor： Zhong Ouyang ,  Kevin D. Smith

IPC: G01N21/71 ,  G01N21/84

Abstract: Apparatus and associated methods relate to predicting precursor to coating spallation. Heat is provided to a first surface of a member. A time sequence of thermal images is captured of the first surface and/or a second surface of the member. Each of the images includes a two-dimensional array of image data. Each of the image data of the two-dimensional array of image data corresponds to an xy-coordinate pair. A two-dimensional array of thermal diffusivities is calculated based on the captured time sequence of thermal images. Each of the thermal diffusivities of the two-dimensional array of thermal diffusivities corresponds to the xy-coordinate pair. Each of the calculated thermal diffusivities of the two dimensional array of thermal diffusivities are compared with a predetermined threshold. If the calculated thermal diffusivity is greater than the predetermined threshold, then precursor to coating spallation of the thermal barrier coating at the corresponding xy-coordinate pair is predicted.

公开(公告)号：US10048133B2

公开(公告)日：2018-08-14

申请号：US14640750

申请日：2015-03-06

Applicant: United Technologies Corporation

Inventor： Kevin D. Smith ,  David A. Raulerson ,  Zhong Ouyang ,  Lisa J. Brasche

IPC: F01D17/08 ,  G01J5/00 ,  G01J5/08 ,  G01J5/06 ,  F01D5/18

Abstract: A thermal inspection system is provided for a gas turbine engine hot section component with a cooling passage. This thermal inspection system includes a fluid subsystem operable to supply a fluid into the cooling passage. The thermal inspection system also includes a thermal camera subsystem operable to monitor a fluid temperature difference of the fluid exiting the cooling passage relative to the input temperature of the fluid supplied to the cooling passage.

公开(公告)号：US20210172859A1

公开(公告)日：2021-06-10

申请号：US16706211

申请日：2019-12-06

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Zhong Ouyang ,  Andrew DeBiccari ,  Nicholas M. LoRicco ,  William J. Brindley ,  Kathryn Macauley ,  Christopher J. Bischof

IPC: G01N17/04 ,  B64F5/60 ,  B64D27/12 ,  G01R33/12

Abstract: A method is provided that involves rotational equipment that includes a case and a first rotor blade within the case. During the method, a probe is arranged within the case adjacent the first rotor blade. A magnetic characteristic of the first rotor blade is measured using the probe. Presence of internal corrosion within the first rotor blade is determined based on the measured magnetic characteristic.

公开(公告)号：US11002638B2

公开(公告)日：2021-05-11

申请号：US16361303

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Zhong Ouyang ,  Andrew DeBiccari ,  William J. Brindley ,  Xuan Liu

IPC: G01M15/14 ,  G01N23/046 ,  G01N27/82

Abstract: A magnetoscop inspection system includes a magnetoscop, a computed tomography unit, and a corrosion model unit. The magnetoscop measures a permeability at a plurality of inspection points of a turbine component. The computed tomography unit generates a measured profile of a hollowed portion of the turbine component based at least in part on the permeability at the measured inspection points. The corrosion model unit stores in memory at least one reference computed tomography profile of a known turbine component. The magnetoscop inspection system determines a structural integrity of the turbine component based on a comparison between the measured profile and the reference profile corresponding to the turbine component currently under inspection.

公开(公告)号：US10816507B2

公开(公告)日：2020-10-27

申请号：US16359550

申请日：2019-03-20

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Zhong Ouyang ,  Andrew DeBiccari ,  William J. Brindley ,  Kathryn Macauley

IPC: G01N27/72 ,  G01M15/14 ,  G01R33/12

Abstract: Disclosed is an apparatus and method for inspecting a component of a gas turbine engine, which includes a sleeve configured to surround a component of a gas turbine engine, the sleeve including: a pair of opposing wall members being secured to each other at at least one of a pair of opposite ends; an internal cavity located between the pair of opposing wall members, wherein the internal cavity extends from one end of the sleeve to an opposite end of the sleeve; and a plurality of orifices extending through the pair of opposing wall members, and wherein a probe is inserted in each orifice in one of the pair of opposing wall members to determine the state of the internal cavities of a gas turbine component and determine the structural integrity of the component.

公开(公告)号：US20200300731A1

公开(公告)日：2020-09-24

申请号：US16361303

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Zhong Ouyang ,  Andrew DeBiccari ,  William J. Brindley ,  Xuan Liu

IPC: G01M15/14 ,  G01N27/82 ,  G01N23/046

Abstract: A magnetoscop inspection system includes a magnetoscop, a computed tomography unit, and a corrosion model unit. The magnetoscop measures a permeability at a plurality of inspection points of a turbine component. The computed tomography unit generates a measured profile of a hollowed portion of the turbine component based at least in part on the permeability at the measured inspection points. The corrosion model unit stores in memory at least one reference computed tomography profile of a known turbine component. The magnetoscop inspection system determines a structural integrity of the turbine component based on a comparison between the measured profile and the reference profile corresponding to the turbine component currently under inspection.

公开(公告)号：US20200256831A1

公开(公告)日：2020-08-13

申请号：US16271003

申请日：2019-02-08

Applicant: United Technologies Corporation

Inventor： Xuan Liu ,  Andrew DeBiccari ,  Zhong Ouyang ,  Christopher J. Bischof ,  William J. Brindley

IPC: G01N27/82 ,  F01D5/18

Abstract: Disclosed is a method of detecting mixed mode corrosion of a turbine airfoil. The method includes heat treating the turbine airfoil at a temperature of 1600 to 2100° F. in a Ni/Co oxide reducing atmosphere; and scanning the heat treated turbine airfoil with a magnetometer to determine the presence of mixed mode corrosion, wherein the turbine airfoil comprises a nickel superalloy and has internal passages.