RU2464148C2 - Method of grinding gas turbine engine blade body curved edge - Google Patents

Abstract

FIELD: process engineering.

SUBSTANCE: invention relates to machine building and may be used for grinding gas turbine engine blade body curved edges. Blade is swung through definite angle about its lengthwise axis. Narrow grinding tape adjoining machined surface is displaced along blade body. Grinding is performed in following angular position of body curvilinear edge contact part by grinding tape. The latter oscillates in direction perpendicular to blade body lengthwise axis to rests upon spaced apart thrust rollers.

EFFECT: higher efficiency of grinding.

3 dwg

Description

The invention relates to the field of engineering, and in particular to a method for processing GTE blades, which allows polishing the curved edge of the feather of a gas turbine blade.

A known processing method that allows you to polish the curved edge of the feather of the blades of a gas turbine with a radius-tipped polishing circle moving along the feather of the blade with a slight longitudinal feed [1]. The disadvantage of this method is the low polishing performance.

There is also a known method of polishing, in which the processing of the curved edge of the feather of the blade of a gas turbine is made narrow, the width of which is less than the length of the surface to be treated, with a polishing tape adjacent to the surface to be processed and moving along the edge of the feather of the blade. In the known method, the plane of the polishing tape has a constant angular position and does not track changes in the angular position of the contacting portion of the curved edge of the pen [2]. The disadvantage of this method is the low productivity of polishing due to the reduction of the longitudinal feed of a narrow polishing tape along the machined curved edge of the pen blade.

The known method of polishing the curved edge of the pen blade of a gas turbine is the closest to the invention in terms of technical nature and the achieved result and is accepted by the applicant as a prototype.

The technical result of this invention is to increase the performance of polishing the fillet rounding of the curved edge of the pen blade of a gas turbine.

The specified technical result is achieved by the fact that in the method of polishing the curved edges of the feather of the blades of gas turbine engines with a narrow polishing tape adjacent to the surface to be machined and moving along the feather of the blade, the processing of the curved edge of the feather of the blade of a gas turbine is performed vibrating in the direction perpendicular to the plane of the blade’s pen, narrow polishing a tape moving along the edge of the pen, resting on spaced relative to each other support rollers.

The essence of the invention is illustrated by drawings, where:

Figure 1 shows a General view of the scapula;

Figure 2 - diagram of the process of processing the edges of the feather blades;

Figure 3 - diagram of the vibration of the tape.

The method of polishing blades of gas turbine engines is as follows.

The processed blade 1 has variable radii of curvature R ₁ and R _{2 of the} edge 6 of the feather of the blade 1.

The blade 1 with its locking part 2 is fixed on the machine, in the swinging holder 3. During processing, the blade starts swinging at a certain angle around its longitudinal axis, and a narrow polishing tape 4, which is vibrating in the direction perpendicular to the longitudinal axis of the feather blade 1, is supported on spaced apart relative to each other other supporting rollers, receives a longitudinal movement along the machined edge 5 of the pen blade 1.

There is a polishing of the curved edge 5 of the pen of the blade 1 with tracking changes in the angular position of the contacting portion of the curved edge of the pen with a polishing tape.

The use of this invention will increase the performance of polishing by rounding off the curved edge of the feather of the blades of a gas turbine.

Information sources

1. RF patent No. 2379170, IPC B24B 19/14, 2008, - analogue.

2. "Grinding technology in mechanical engineering" publishing house "Polytechnic" St. Petersburg, pp. 396, 2007, - prototype.

Claims (1)

A method of polishing the curved edges of the feather of the blades of gas turbine engines with a narrow polishing tape adjacent to the surface to be machined and moving along the feather of the blade, characterized in that the polishing of the curved edge of the feather of the blade of a gas turbine is made by monitoring the angular position of the contact portion of the curved edge of the pen with the adjacent polishing tape vibrating in the direction perpendicular to the longitudinal axis of the feather blade, and resting on spaced relative to each other support rollers.

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