RU2464149C2 - 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 and get pressed against machined surface by deformable element.

EFFECT: higher precision and efficiency.

4 dwg

Description

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

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

There is also known a processing method in which the grinding 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 sanding belt 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 sanding belt 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 grinding performance due to the reduction of the longitudinal feed of a narrow sanding belt along the machined curved edge of the blade feather.

The known method is the closest to the invention in technical essence and the achieved result and is accepted by the applicant as a prototype.

The technical result of this invention is to improve the accuracy of rounding the curved edge of the pen blade of a gas turbine and increase processing productivity.

The specified technical result is achieved by the fact that in the method of grinding the curved edges of the feather of the blades of gas turbine engines with a narrow grinding belt adjacent to the surface to be machined and moving along the feather of the blade, the grinding of the curved edge of the feather of the blade of a gas turbine is carried out vibrating in the direction perpendicular to the longitudinal axis of the feather blade of the blade, narrow a tape moving along the edge of the pen, resting on spaced apart rollers and pressed against the workpiece surface elastically deformable element.

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 grinding the edges of the feather blades;

figure 3 is a diagram of the clip of the tape by an elastically deformable element;

figure 4 - scheme of operation of an elastically deformable element.

The method of grinding the blades of gas turbine engines is as follows.

The blade 1 with its locking part 2 is fixed on the machine, in the swinging holder 3. Vibrating in the direction perpendicular to the longitudinal axis of the feather blade 1, the sanding belt 4 is pressed by a deformable clip 5 with a force P to the machined edge 6 of the feather blade 1. The blade 1 begins to swing on a certain angle around its longitudinal axis, and a vibrating sanding belt, supported on spaced apart rollers 7, receives longitudinal movement along the variable radii of curvature R ₁ and R _{2 the} machined edge Ki 6 pen blade 1.

Grinding occurs - rounding of the curved edge 6 of the feather of the blade 1 while tracking changes in the angular position of the contacting portion of the curved edge of the feather with a sanding belt pressed to the work surface by an elastically deformable clip (element) 5.

The use of this invention will improve the accuracy of rounding of the curved edge of the pen blade of a gas turbine and increase processing productivity.

Information sources

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

2. Grinding technology in mechanical engineering. SPb .: Polytechnic, 2007, p. 396 - prototype.

Claims (1)

A method of grinding the curved edges of the feather of the blades of gas turbine engines with a narrow sanding belt adjacent to the surface to be machined and moving along the feather of the blade, characterized in that the grinding of the curved edge of the feather of the blade of a gas turbine is carried out with tracking the angular position of the contacting portion of the curved edge of the feather of the pen vibrating in the direction of the perpendicular axis a feather of the blade, with a sanding belt resting on support rollers spaced apart from each other and pressed against brabatyvaemoy surface of the elastically deformable element.

Images