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公开(公告)号：US10519868B2
公开(公告)日：2019-12-31
申请号：US15431907
申请日：2017-02-14
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Harry Lester Kington , Nagaraja S Rudrapatna , Vladimir K Tolpygo
Abstract: Systems and methods are provided for cleaning one or more cooling passages associated with a combustion chamber of a gas turbine engine. The gas turbine engine has a compressor section upstream from the combustion chamber. In one embodiment, a method includes: receiving a pressurized fluid from a source; directing the pressurized fluid through an inlet of a chamber such that a portion of a plurality of particles within the chamber is entrained within the pressurized fluid; and injecting the pressurized fluid with the entrained portion of the plurality of particles downstream from the compressor section through an end wall of a diffuser and deswirl system of the gas turbine engine or through a plenum upstream from the combustion chamber to clean the one or more cooling passages associated with the combustion chamber.
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公开(公告)号：US10933469B2
公开(公告)日：2021-03-02
申请号：US16126222
申请日：2018-09-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Vladimir K Tolpygo
Abstract: A method of forming an abrasive nickel-based alloy on a turbine blade tip includes producing or obtaining a metal powder that is mixed with a carbon powder to form a carbon-enriched metal powder. The metal powder includes a refractory element. The method further includes bonding the carbon-enriched metal powder to the turbine blade tip. The step of bonding includes raising the temperature of the carbon-enriched metal powder past its melting point, thereby causing the carbon to combine with the refractory elements to form abrasive carbide particles.
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公开(公告)号：US20200078867A1
公开(公告)日：2020-03-12
申请号：US16126222
申请日：2018-09-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Vladimir K Tolpygo
Abstract: A method of forming an abrasive nickel-based alloy on a turbine blade tip includes producing or obtaining a metal powder that is mixed with a carbon powder to form a carbon-enriched metal powder. The metal powder includes a refractory element. The method further includes bonding the carbon-enriched metal powder to the turbine blade tip. The step of bonding includes raising the temperature of the carbon-enriched metal powder past its melting point, thereby causing the carbon to combine with the refractory elements to form abrasive carbide particles.
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