公开(公告)号：US11534780B2

公开(公告)日：2022-12-27

申请号：US16557317

申请日：2019-08-30

Applicant: General Electric Company

Inventor： Ambarish Jayant Kulkarni ,  Hrishikesh Keshavan ,  Mehmet Dede ,  Bernard Patrick Bewlay ,  Guanghua Wang ,  Byron Pritchard ,  Michael Solomon Idelchik

IPC: B05B7/04 ,  B05B12/08 ,  B05B7/02 ,  B05B1/20 ,  B05B7/00 ,  B05B7/08 ,  B05B7/16 ,  B05B1/04 ,  B05B7/14 ,  F01D5/00

Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

公开(公告)号：US20220243612A1

公开(公告)日：2022-08-04

申请号：US17167435

申请日：2021-02-04

Applicant: General Electric Company

Inventor： Byron Andrew Pritchard, JR. ,  Deepak Trivedi ,  Ambarish Jayant Kulkarni ,  Michael Robert Millhaem

IPC: F01D25/00 ,  B08B3/00 ,  B08B9/00

Abstract: An inflatable device equipped with a guiding mechanism and methods of installing the inflatable device to form a temporary barrier within a gas turbine engine are provided. In one aspect, an inflatable device includes a backbone and an inflatable bladder connected thereto. The backbone is formed of a flexible and inextensible material. The inflatable bladder is formed of an expandable material. To install the inflatable device within an annular chamber of a gas turbine engine, the backbone is inserted into a first access port of the engine and is moved circumferentially around the annulus of the chamber. The backbone is retrieved through a second access port. The inflatable bladder is moved into position within the chamber by pushing the backbone into the first access port and/or pulling the backbone out of the second access port. When positioned in place, the inflatable bladder is inflated to form an annular seal.

公开(公告)号：US11261797B2

公开(公告)日：2022-03-01

申请号：US16180459

申请日：2018-11-05

Applicant: General Electric Company

Inventor： Liangde Xie ,  Ambarish Jayant Kulkarni ,  Byron Andrew Pritchard, Jr. ,  Matthew Charles Sabo

IPC: F02C7/00 ,  F02C7/30 ,  F02C7/22

Abstract: A vapor-based system and method for treating one or more components of a gas turbine engine. The system includes a treatment compound contained in a storage vessel. The storage vessel being operably coupled to a delivery module. The delivery module delivering the treatment compound at one or more locations of the gas turbine engine such that the treatment compound is a vapor when exposed to an engine air-path.

公开(公告)号：US20220056812A1

公开(公告)日：2022-02-24

申请号：US17518901

申请日：2021-11-04

Applicant: General Electric Company

Inventor： Ambarish Jayant Kulkarni ,  Bernard Patrick Bewlay ,  Byron Andrew Pritchard, JR. ,  Nicole Jessica Tibbetts ,  Michael Edward Eriksen ,  Eric John Telfeyan

IPC: F01D25/00 ,  F02C7/30 ,  B08B9/00 ,  B08B3/02

Abstract: A method for cleaning components of a gas turbine engine is presented. The method includes introducing a working fluid into a gas flow path or a cooling circuit defined by the one or more components of the gas turbine engine such that the working fluid impinges upon a surface of the one or more components of the gas turbine engine, wherein the working fluid includes a plurality of detergent droplets entrained in a flow of steam. A system for cleaning components of a gas turbine engine are also presented.

公开(公告)号：US20210323008A1

公开(公告)日：2021-10-21

申请号：US17360567

申请日：2021-06-28

Applicant: General Electric Company

Inventor： Ambarish Jayant Kulkarni ,  Hrishikesh Keshavan ,  Mehmet Dede ,  Bernard Patrick Bewlay ,  Guanghua Wang ,  Byron Pritchard ,  Michael Solomon Idelchik

IPC: B05B7/04 ,  B05B1/20 ,  B05B1/30 ,  B05B7/08 ,  F01D5/28 ,  B05B7/02 ,  B05B7/14 ,  F01D5/00 ,  B05B7/00 ,  B05B7/16 ,  B05B1/04

Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

公开(公告)号：US20210131305A1

公开(公告)日：2021-05-06

申请号：US17089331

申请日：2020-11-04

Applicant: General Electric Company

Inventor： Hrishikesh Keshavan ,  Ambarish Jayant Kulkarni ,  Margeaux Wallace ,  Byron Andrew Pritchard, JR. ,  Almed M. Elkady ,  Atanu Saha ,  Mamatha Nagesh ,  Bernard Patrick Bewlay

IPC: F01D25/08 ,  C23C4/11 ,  C23C4/02

Abstract: A coated component of a gas turbine engine includes a substrate defining a surface, a thermal barrier coating deposited on the surface of the substrate, a region of the component where the thermal barrier coating has spalled from the substrate, a layer of environmental contaminant compositions formed on one or more of the thermal barrier coating or the region of the component where the thermal barrier coating has spalled from the substrate in response to an initial exposure of the component to high operating temperatures of the gas turbine engine, and a thermal barrier coating (TBC) restoration coating deposited at least on the region of the component where there thermal barrier coating has spalled from the substrate.

公开(公告)号：US10690055B2

公开(公告)日：2020-06-23

申请号：US15314490

申请日：2015-05-27

Applicant: General Electric Company

Inventor： Curtis Walton Stover ,  Jonathan Michael Rausch ,  Satoshi Atsuchi ,  Gulcharan Singh Brainch ,  Robert David Briggs ,  Ronald Scott Bunker ,  Ambarish Jayant Kulkarni ,  Michael Alan Meade ,  Byron Andrew Pritchard ,  Robert Proctor

IPC: F02C7/18 ,  F01D11/08 ,  F01D25/12 ,  F01D9/04 ,  F01D5/18 ,  F23R3/00

Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.

公开(公告)号：US10428683B2

公开(公告)日：2019-10-01

申请号：US14987883

申请日：2016-01-05

Applicant: General Electric Company

Inventor： Michael Edward Eriksen ,  David E. Caldwell ,  Nicole Jessica Tibbetts ,  Ambarish Jayant Kulkarni ,  Byron Andrew Pritchard, Jr.

IPC: B24C3/32 ,  F01D25/00 ,  B24C1/00 ,  C11D3/20 ,  C11D3/38 ,  C11D11/00 ,  C11D17/00 ,  B24C11/00 ,  C11D3/14

Abstract: The present disclosure is directed to a method for in-situ cleaning one or more components of a gas turbine engine using an abrasive gel detergent. More specifically, the gel detergent includes a plurality of abrasive particles suspended in a gel composition. Further, the abrasive particles include organic material. Moreover, the gel composition is formed of a mixture of detergent particles dissolved in a gel reactant. Thus, the method includes injecting the gel detergent into at least a portion of the gas turbine engine at a predetermined pressure. In addition, the method includes allowing the gel detergent to flow across or within one or more of the components of the gas turbine engine so as to clean one or more of the components.

公开(公告)号：US10227891B2

公开(公告)日：2019-03-12

申请号：US15472456

申请日：2017-03-29

Applicant: General Electric Company

Inventor： Michael Edward Eriksen ,  Keith Anthony Lauria ,  Ambarish Jayant Kulkarni ,  Byron Andrew Pritchard, Jr. ,  David Geoffrey Dauenhauer ,  Bernard Patrick Bewlay ,  Nicole Jessica Tibbetts

IPC: B08B9/00 ,  F01D25/00 ,  B08B3/00

Abstract: A wash system for a gas turbine engine includes a foam generating device configured for receiving and aerating a flow of wash fluid to generate a flow of foamed wash fluid having particular foam characteristics. The flow of foamed wash fluid passes through a distribution manifold where it is selectively directed through a plurality of wash lines to desired portions of the gas turbine engine. The wash system further includes a controller configured for manipulating the foam characteristics of the flow of foamed wash fluid and using the distribution manifold to selectively direct the flow of foamed wash fluid to desired portions of the gas turbine engine for optimal cleaning and improved engine efficiency.

公开(公告)号：US20180283209A1

公开(公告)日：2018-10-04

申请号：US15472456

申请日：2017-03-29

Applicant: General Electric Company

Inventor： Michael Edward Eriksen ,  Keith Anthony Lauria ,  Ambarish Jayant Kulkarni ,  Byron Andrew Pritchard, JR. ,  David Geoffrey Dauenhauer ,  Bernard Patrick Bewlay ,  Nicole Jessica Tibbetts

IPC: F01D25/00 ,  B08B3/00

CPC classification number: F01D25/002 ,  B08B3/003 ,  B08B3/02 ,  B08B9/00 ,  F05D2220/32

Abstract: A wash system for a gas turbine engine includes a foam generating device configured for receiving and aerating a flow of wash fluid to generate a flow of foamed wash fluid having particular foam characteristics. The flow of foamed wash fluid passes through a distribution manifold where it is selectively directed through a plurality of wash lines to desired portions of the gas turbine engine. The wash system further includes a controller configured for manipulating the foam characteristics of the flow of foamed wash fluid and using the distribution manifold to selectively direct the flow of foamed wash fluid to desired portions of the gas turbine engine for optimal cleaning and improved engine efficiency.