A kind of aero-engine is without installing plate compressor stator blade processing method
Technical field
The invention belongs to aero-engine compressor blade processing technology, relate to the improvement of aero-engine without installing plate compressor stator blade processing method, be specifically related to a kind of aero-engine without installing plate compressor stator blade processing method.
Background technology
Certain h type engine h compressor one is without installing plate stator blade structure see Fig. 1, and blade is made up of blade tip 1, blade 2, exhaust limit 3, blade root 4 and leading edge 5.Blade tip 1 is made up of three sections of curved surfaces, and blade root 4 is with step, and leading edge 5 is the molded line changed with exhaust limit 3.At present, the main method of processing without installing plate stator blade is: 1) adopt die forging blank or plate, first numerical control milling blade profile, then polishing blade profile, final cutting blade tip and blade root.The method need process blade profile, complex process, and working (machining) efficiency is low, and blade profile profile tolerance qualification rate is low; 2) adopt plate, first rolling blade profile, then cut off blade tip and blade root.The method complex process, working (machining) efficiency is low.
Summary of the invention
The object of this invention is to provide the processing method of a kind of aero-engine compressor without installing plate stator blade, to ensure blade profile profile tolerance, improve working (machining) efficiency, shorten the process-cycle.
For achieving the above object, the present invention adopts following technical scheme:
1) milling inlet and outlet limit: adopt fine forge piece as without installing plate stator blade blank, blank comprises blade, be positioned at the exhaust limit of blade side, be positioned at the leading edge of blade opposite side, be positioned at first false boss of blade one end and be positioned at the second false boss of the blade other end, wherein blade comprises blade tip and blade root, blade tip connects the first false boss, blade root fastenings second false boss, the second false boss end face is that sharf is to benchmark;
With the positioning and clamping processing gas inlet limit, basin side of the first false boss, the second false boss, the second false boss end face and blade and exhaust limit on CNC milling machine, leading edge stays 0.05mm ~ 0.15mm surplus with exhaust limit;
2) polishing inlet and outlet limit: polishing leading edge and exhaust limit, makes the size and dimension on leading edge and exhaust limit meet designing requirement;
3) Linear cut blade tip and blade root: with the basin side of blade, the first false boss, the second false boss and the second false boss end face positioning and clamping on numerically controlled wire cutting machine, processing blade tip and blade root, remove the first false boss and the second false boss;
4) pincers are repaiied: pincers repair blade tip and blade root, removal step 3) in be retained in Linear cut remelted layer on blade tip and blade root, and make the surface roughness of blade tip and blade root meet designing requirement.
The leading edge of described blank has 2mm ~ 3mm allowance with exhaust limit.
Described step 2) in polishing on polishing machine, adopt bob and nylon wheel to carry out.
Described step 4) employing file repaiied by middle pincers and sand paper carries out.
Compared with prior art, the beneficial effect that the present invention has: the invention proposes the improvement processing method of a kind of aero-engine without installing plate stator blade, repair by carrying out milling intake and exhaust limit, polishing intake and exhaust limit, Linear cut blade tip blade root and pincers to finish forge blank, processing obtains aero-engine without installing plate compressor stator blade.The present invention has the following advantages: 1) the method adopts finish forge blank, ensure that blade type profile tolerance of a surface and surface quality, makes the blade obtained meet designing requirement; Because blank adopts fine forge piece, so make the qualification rate of obtained blade high, overcome the working (machining) efficiency that causes owing to adopting die forging blank or plate in prior art and the low problem of qualification rate; 2) method work flow provided by the invention is simple, effectively improves working (machining) efficiency, shortens the process-cycle.
Accompanying drawing explanation
Fig. 1 is that certain h type engine h compressor is a kind of without installing plate stator blade structural representation;
Fig. 2 is that certain h type engine h compressor is a kind of without installing plate stator blade blank schematic diagram;
Fig. 3 be the second false boss along A-A in Fig. 2 to sectional view.
In figure, 1 is blade tip, and 2 is blade, and 3 is exhaust limit, and 4 is blade root, and 5 is leading edge, and 6 is the first false boss, and 7 is the second false boss, and 8 is the second false boss end face.
Detailed description of the invention
Below in conjunction with accompanying drawing, the present invention is described in detail.
Aero-engine of the present invention is fine forge piece without the blank of installing plate stator blade, blahk structure is see Fig. 2 and Fig. 3, blank comprises blade 2, be positioned at the exhaust limit 3 of blade 2 side, be positioned at the leading edge 5 of blade 2 opposite side, be positioned at first false boss 6 of blade 2 one end and be positioned at the second false boss 7 of blade 2 other end, wherein blade 2 comprises blade tip 1 and blade root 4, blade tip 1 connects the first false boss 6, blade root 4 connects the second false boss 7, blade 2 does not have surplus, leading edge 5 has 2mm ~ 3mm allowance with exhaust limit 3, second false boss end face 8 is that sharf is to benchmark, its procedure of processing is:
1) milling inlet and outlet limit: with the positioning and clamping processing gas inlet limit, basin side 5 of the first false boss 6, second false boss 7, second false boss end face 8 and blade 2 and exhaust limit 3 on CNC milling machine, leading edge 5 stays 0.05mm ~ 0.15mm surplus with exhaust limit 3.
2) polishing inlet and outlet limit: use bob and nylon wheel polishing leading edge 5 and be vented limit 3 on polishing machine, ensures that leading edge 5 meets designing requirement with the size and dimension being vented limit 3.
3) Linear cut blade tip and blade root: with the basin side of blade 2, the first false boss 6, second false boss 7 and the second false boss end face 8 positioning and clamping on numerically controlled wire cutting machine, processing blade tip 1 and blade root 4, remove the first false boss 6 and the second false boss 7.
4) pincers are repaiied: clamp with file and sand paper and repair blade tip 1 and blade root 4, removal step 3) in be retained in Linear cut remelted layer on blade tip 1 and blade root 4, and ensure that the surface roughness of blade tip 1 and blade root 4 meets designing requirement.