[특허]In situ gas turbine prevention of crack growth progression

In situ gas turbine prevention of crack growth progression 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B23P-006/04 B23K-026/03 B23K-026/08 F01D-005/00 B23K-026/342 B23K-026/70 B23K-026/144 B23K-101/00 B23K-103/18
출원번호	US-0014075 (2016-02-03)
등록번호	US-10247002 (2019-04-02)
발명자 / 주소	Roberts, Herbert Chidsey Diwinsky, David Scott Grady, Wayne R.
출원인 / 주소	General Electric Company
대리인 / 주소	General Electric Company
인용정보	피인용 횟수 : 0 인용 특허 : 42

초록 ▼

A method for remotely stopping a crack in a component of a gas turbine engine is provided. The method can include inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine; positioning the tip adjacent to a defect within a surface of the component; temporarily attaching the tip adjacent to the defect within the surface on the component; supplying a new material to the area to fill the defect; and heating the new material to fuse the new material to the component within the defect.

대표청구항 ▼

1. A method of remotely stopping a crack in a component of a gas turbine engine, the method comprising: inserting an integrated repair interface attached to a cable delivery system within a gas turbine engine;positioning a tip adjacent to a defect within a surface of the component;temporarily attaching the tip adjacent to the defect within the surface on the component;heating a high temperature conduit with a heating element;supplying a new material to the high temperature conduit from external of the engine, wherein the new material is a particle powder comprising a plurality of solid particles;maintaining the new material in the high temperature conduit at a delivery temperature within about 25% of the melting point of the new material;supplying the new material at the delivery temperature to a working head;supplying the new material to the area to fill the defect; andheating the a base of the defect to fuse the new material to the component within the defect. 2. The method of claim 1, wherein the plurality of solid particles are supplied into the defect at a velocity of about 150 m/s to about 900 m/s. 3. The method of claim 1, wherein the plurality of solid particles is supplied into the defect at an average particle size of about 25 μm to about 150 μm. 4. The method of claim 1, wherein the plurality of solid particles is supplied into the defect at an average particle size of about 35 μm to about 75 μm. 5. The method of claim 1, wherein the new material is supplied into the defect as a particle powder at the delivery temperature. 6. The method of claim 5, wherein the particle powder is supplied into the defect at a temperature within about 10% of its melting point. 7. The method of claim 1, wherein the new material is supplied into the defect as a liquid. 8. The method of claim 1, wherein the high temperature conduit is formed from a ceramic material. 9. The method of claim 1, wherein the high temperature conduit further comprises: a heating element integrated into a wall of the high temperature conduit. 10. The method of claim 9, wherein the heating element is a resisting heating element comprising: a resistance wire. 11. The method of claim 10 wherein the resisting heating element provides heating within the high temperature conduit so as to maintain the delivery temperature. 12. The method of claim 1, further comprising: inserting an optical probe through the access port or an adjacent access port of the gas turbine engine, the optical probe being configured to provide a view of the defect within the gas turbine engine. 13. The method of claim 12, wherein positioning the tip end of the repair tool adjacent to the defect comprises positioning the tip end relative to the defect based on the view provided by the optical probe. 14. The method of claim 1, wherein the tip is attached using a tripod grip, a glue, or a vacuum sucker. 15. The method of claim 1 wherein the heating element provides heating within the high temperature conduit so as to maintain the delivery temperature. 16. The method of claim 1 wherein the high temperature conduit comprises: a material having a melting point greater than the melting point of the new material. 17. The method of claim 1, wherein the base of the defect is heated to a temperature of 1000° C. to 2000° C. 18. The method of claim 1 wherein the base of the defect is heated to a temperature of 1800° C. to 2000° C.

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