Tandem turbine blade multi-station hard clamping electromachining method and device
A turbine blade, multi-station technology, applied in the field of machining, can solve the problems of the performance index decline and fracture of the turbine blade, and achieve the effect of eliminating the risk of corroding the surface of the casting, accurate positioning, and eliminating repeated clamping errors.
Active Publication Date: 2018-01-16
AECC AVIATION POWER CO LTD
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Problems solved by technology
The final residual low-melting point alloy is easy to dissolve the surface of the casting under high-temperature conditions when the aero-engine is working, resulting in a decrease in the performance indicators of the turbine blade or even breaking it, which may cause various accidents
Method used
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[0034] The present invention will be further described below in conjunction with the accompanying drawings.
[0035] refer to Figure 1 to Figure 8 The tandem turbine blade multi-station hard-clamp electric machining device of the present invention comprises a long rectangular base 1 with switchable magnetic force as a base body, and a plurality of rectangular bases with switchable magnetic force are arranged at equal intervals on the long rectangular base 1 which can be used for the previous blade. An integrated positioning block 2 that can position the back point of the body leaf and can also position the exhaust edge of the next blade body;
[0036] The long rectangular base 1 with switchable magnetic force is also provided with an exhaust side positioning block 3 for positioning the exhaust side of the blade body and a blade back positioning block 4 for point positioning of the blade back profile;
[0037]The exhaust side positioning block 3 is arranged at the front end o...
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The invention discloses a tandem turbine blade multi-station hard clamping electromachining method and device. The device comprises a long rectangular base with switchable magnetic force, the long rectangular base is used as a base body, and multiple integral positioning blocks are arranged on the long rectangular base with switchable magnetic force at equal intervals; an exhaust edge positioningblock used for positioning a blade body exhaust edge and a blade back positioning block used for conducting point positioning on the blade back profile surface are further arranged on the long rectangular base with switchable magnetic force; a radial positioning block is detachably positioned and mounted on one side of the long rectangular base with switchable magnetic force; a bridge which stretches across above the integral positioning blocks, the exhaust edge positioning block and the blade back positioning block is mounted on the long rectangular base with switchable magnetic force, multiple compression screw rods used for self-locking and compressing blade bodies penetrate through the bridge and are connected with the bridge in a threaded mode, a certain included angle is formed between the compression screw rods and the mounting plane of the long rectangular base with switchable magnetic force, and thus after the compression screw rods are screwed tightly, the blade body exhaustedge and blade back positioning points can be positioned automatically without existence of gaps.
Description
【Technical field】 [0001] The invention is applied to the field of mechanical processing of aeroengine turbine guide vanes and similar parts, and in particular relates to a multi-station hard clamping electrical machining method and device for serial turbine blades. 【Background technique】 [0002] At present, most of the high-pressure turbine guide vanes in the advanced aero-engine and gas turbine products currently in service in my country adopt a single-blade integral casting and welding double-connected air-cooled turbine guide vane structure. The upper and lower ends of the mounting head have machining allowances that need to be removed by machining. Machining requires the use of the six-point positioning principle for clamping and positioning processing. The six positioning points of the casting are respectively located on the exhaust side of the blade body, the point positioning on the blade back and the upper end surface. Existing processing technique is to adopt the ...
Claims
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Login to View More IPC IPC(8): B23H7/02B23H11/00
Inventor 温学兵崔保卫冯所宁王冬王文博杨嘉高敏雀张军全
Owner AECC AVIATION POWER CO LTD