MANUFACTURE OF COOLING HOLES FOR CERAMIC MATRIX COMPOSITE COMPONENTS

To provide systems and methods for machining openings of a component.SOLUTION: A laser system 100 includes features for machining an opening 210 into a component 200, such as a cooling hole for a CMC component of a gas turbine engine. The component can be oriented in a first position P1 and lasered...

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Bibliographische Detailangaben
Hauptverfasser:	ALAN JOSEPH PARVIS, TIMOTHY FRANCIS ANDREWS, MARK SAMUEL BAILEY
Format:	Patent
Sprache:	eng ; jpn
Schlagworte:	AIR INTAKES FOR JET-PROPULSION PLANTS BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBUSTION ENGINES CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL GAS-TURBINE PLANTS HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING WEAPONS WELDING WORKING BY LASER BEAM
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Beschreibung
Zusammenfassung:	To provide systems and methods for machining openings of a component.SOLUTION: A laser system 100 includes features for machining an opening 210 into a component 200, such as a cooling hole for a CMC component of a gas turbine engine. The component can be oriented in a first position P1 and lasered while oriented in the first position to form a portion of the opening. The component is then oriented to a second position P2 and lasered while oriented in the second position to form another portion of the opening. The component is alternated between the first and second positions until the predetermined geometry of the opening is formed. The component is oriented in the first and second positions such that a laser beam can machine the component without clipping areas that are not desired to be machined.SELECTED DRAWING: Figure 3 【課題】構成要素の開口部を機械加工するためのシステムおよび方法の提供。【解決手段】レーザシステム１００は、ガスタービンエンジンのＣＭＣ構成要素用の冷却孔のような、構成要素２００に開口部２１０を機械加工するための機構を含む。構成要素は、第１の位置Ｐ１に配向され、第１の位置に配向されている間にレーザ加工され、開口部の一部を形成する。次いで、構成要素は、第２の位置Ｐ２に配向され、第２の位置に配向されている間にレーザ加工され、開口部の別の部分を形成する。構成要素は、開口部の所定の幾何学的形状が形成されるまで、第１および第２の位置の間で交互に配置される。構成要素は、レーザビームが機械加工されることが望ましくない領域をクリッピングすることなく構成要素を機械加工することができるように、第１および第２の位置に配向される。【選択図】図３