A method for precision machining of spout parts
A technology of precision machining and parts, which is applied in the field of precision machining of spout parts, can solve problems such as difficult to guarantee the technical conditions of parts and surface roughness requirements, and achieve the effect of improving surface quality, improving production efficiency, and improving quality
Active Publication Date: 2017-09-29
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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Problems solved by technology
[0003] In view of the fact that it is difficult to guarantee the technical conditions and surface roughness requirements of the nozzle parts in the prior art by using ordinary internal and external cylindrical grinders, the technical problem to be solved by the present invention is to provide a nozzle that can improve the qualification rate and production efficiency of the parts. Method for precision machining of similar parts
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[0049] The present invention will be further elaborated below in conjunction with the accompanying drawings of the description.
[0050] A method for precision machining of spout parts of the present invention comprises the following steps:
[0051] 1) Using a dual-spindle turning-milling compound machining center and a precision CNC universal internal grinding machine, the parts are turned and milled in one clamping state and the inner and outer profiles of the parts are ground;
[0052] 2) UGCAM programming is adopted on the turning-milling compound machining center, and the correctness of the machining program is verified by virtual simulation technology;
[0053] 3) Design the processing route, process method, positioning reference and process parameters of nozzle parts.
[0054] The processing route of nozzle parts is:
[0055] Bar stock; turning and milling outer surface and inner cavity (such as Figure 6 As shown, it includes the first outer circle 4, the first inne...
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Abstract
The invention relates to a method for precision machining of nozzle type parts. The method comprises the following steps that (1) a turn milling composite machining center with double spindles and a precision numerical control all-purpose internal grinding machine are adopted for turning and milling internal and external profiles of the parts and grinding and machining the internal and external profiles of the parts in a one-time clamping state respectively; (2) a UGCAM program is adopted on the turn milling composite machining center, and a virtual simulation technology is applied to verify the correctness of a machining program; and (3) the machining process route, process method, positioning standard and process parameters of the nozzle type parts are designed. Twenty procedures of machining of an original common numerical control device are reduced to be existing fifteen procedures for the similar parts, six finish machining procedures after original heat treatment are reduced to be one procedure, five procedures are omitted, and by turning and milling the internal and external profiles of nozzles and precisely grinding the internal and external profiles of the nozzles in the one-time clamping state, the technical problem that the machining technological conditions and surface roughness of the parts are difficult to ensure is solved, and the aim of replacing grinding with finish grinding is achieved.
Description
technical field [0001] The invention relates to a processing technology of aero-engine parts, in particular to a method for precise processing of nozzle parts. Background technique [0002] The nozzle is an important part on the main fuel nozzle of the engine. It has a complex structure, high requirements for dimensional accuracy and technical conditions, and low requirements for surface roughness. It is a small precision part, such as figure 1 , 2 , 3, 4 shown. The coaxiality of the nozzle center hole 1 relative to the inner hole 2 is not greater than The circular runout of the inner cone surface 3 relative to the inner hole 2 is not greater than The coaxiality of the first outer circle 4 relative to the inner hole 2 is not greater than The surface roughness of the central hole 1, the inner tapered surface 3 and the first inner end surface 5 are all Ra0.2, and the verticality of the first inner end surface 5 and the outer end surface 6 relative to the inner hole 2 is...
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IPC IPC(8): B23P15/00
CPCB23P15/00
Inventor 魏鉴梅金英卓郑艳铭张晶韩帅
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION