RU2786291C1 - Method for manufacturing a guide vane for an aircraft engine compressor - Google Patents

Abstract

FIELD: turbine construction.

SUBSTANCE: invention relates to the field of turbine construction, more specifically to methods for manufacturing compressor guide vanes for a gas turbine engine, mainly for aircraft. The guide vanes of the compressor are made of a composite material, the manufacture of which includes cutting the layers for the blades, their final design is made in a mold. The finished blade on the peripheral side has a shank for fastening in the rim, on the opposite side of the blade for fastening in the support ring there is a shank with the profile of the last root section of the blade, such a shank simplifies the manufacture of composite material layers and a mold for pressing the blades. The rim is formed by winding from threads or bundles with subsequent polymerization, the holes for the blade shanks are made by punching or milling. The support ring consists of inlet and outlet half rings, for the manufacture of which layers of composite material are cut, they are placed in a mold, the mold is pressed, polymerized and disassembled, thus obtaining inlet and outlet support half rings, which have grooves for attaching the blade root. The assembly of the guide vane apparatus is carried out by installing the blade roots in the holes of the rim, then after installing all the blade roots in one of the support semi-rings, the second support semi-ring is laid, aligning the grooves of the latter with the blade roots. Both supporting half rings are compressed, for example, by bolts, while the blade roots are firmly fixed in the support ring.

EFFECT: significant simplification of the technological process and reduction of labor intensity.

1 cl, 7 dwg

Description

The invention relates to the field of turbine engineering, more precisely to methods for manufacturing compressor guide vanes from a composite material for a gas turbine engine, mainly for aircraft.

Known is the “Method of manufacturing an aircraft engine compressor guide vane” (patent RU No. 2661429, published on 07/16/2018), which allows to obtain products from a composite material with increased strength characteristics.

SUBSTANCE: method for manufacturing a compressor guide vane apparatus from a composite material includes cutting layers of blade material, pressing them in a mold, placing and centering the blades in an assembly mold, and pressing the apparatus. When cutting, the layers of the composite material go beyond the contour of the blade from the side of the root section to a length greater than the length of the arch of the support ring between adjacent blades, and from the side of the peripheral section to a length greater than the length of the rim arc between adjacent blades. The material is impregnated with a binder within the contour of the blade and placed in a mold in which the aerodynamic profile of the blade is formed, a part of the support ring and rim 1–20 mm long is formed on the root and peripheral sections of the blade. The vanes are then placed in a separator which provides the nominal arrangement of the vanes in the mold. Next, the material that extends beyond the contour of the blades is impregnated, and a support ring and a rim are preliminarily formed in the cavities of the separator, after which threads or bundles are wound on the outer surface of the rim, impregnated with a binder, placed in the mold separator, a punch is installed on which, in place of its contact with the support ring, threads or bundles impregnated with a binder are preliminarily wound and pressed, while the outer surfaces of the rim are formed in the matrix, the outer surfaces of the support ring are formed in the punch, the internal aerodynamic surfaces, the gas path of the rim and the support ring are formed in the separator.

However, the use of this method creates certain difficulties in the production of the guide vane, because. it is required to impregnate a part of the composite material with a binder when pressing the blades, and the material that goes beyond the contour of the blade is impregnated when placed in the mold separator.

Known is the "Method of manufacturing a guide vane apparatus for an aircraft engine compressor" (patent RU No. 2766040, publ. 07.02.2022), adopted as a prototype, which allows to obtain products from composite materials with increased strength characteristics.

A method for manufacturing a compressor guide vane apparatus from a composite material includes cutting the layers of the material of the blades, while additionally cutting at least one layer, including the material of the back, leading edge and trough. The mold is filled from laying the back material, and is completed by laying the trough material on top. Next, the blades are pressed in a mold, placed and centered in an assembly mold, and the apparatus is pressed. When cutting, the layers of the composite material go beyond the contour of the blade from the side of the root section to a length greater than the length of the arch of the support ring between adjacent blades, and from the side of the peripheral section to a length greater than the length of the rim arc between adjacent blades. The material is impregnated with a binder within the contour of the blade and placed in a mold in which the aerodynamic profile of the blade is formed, a part of the support ring and rim 1–20 mm long is formed on the root and peripheral sections of the airfoil. The vanes are then placed in a separator that provides the nominal position of the vanes in the mold. Next, the material that extends beyond the contour of the blades is impregnated, and a support ring and a rim are preliminarily formed in the cavities of the separator, after which threads or a bundle impregnated with a binder are wound on the outer surface of the rim, the separator is placed in a mold, a punch is installed on which, in place of it contact with the support ring, threads or a bundle impregnated with a binder are preliminarily wound and pressed, while the outer surfaces of the rim are formed in the matrix, the outer surfaces of the support ring are formed in the punch, the internal aerodynamic surfaces of the gas path of the rim and the support ring are formed in the separator.

However, the use of this method creates certain difficulties in the production of the guide vane, because. requires impregnation of a binder part of the composite material for pressing the blades, and the material that extends beyond the contour of the blade is impregnated with a binder before laying the blades in the mold separator.

This invention solves the problem of creating a method that excludes the use of the technological operation "impregnation with a binder of the source material" before pressing the blades, while leaving in its original state the material that goes beyond the contour of the blade, which is impregnated with a binder before being placed in the assembly mold.

The problem is solved by the fact that the guide vanes are made entirely of prepreg. In the mold, a blade is made with two shanks for mounting in the rim and the support ring, which is obtained by pressing in the form of a front half-ring and a rear half-ring, connected after the installation of the blades.

Fig. 1, fig. 2 is a general view of the compressor guide vanes.

Fig. 3 spatula.

Fig. 4 cutting layers of blade material.

Fig. 5 cut a layer of blade material, including material: back, leading edge and trough.

Fig. 6 enlarged section of the mold with a blade.

Fig. 7 view of the rim along arrow B.

The guide vane apparatus (Fig. 1, Fig. 2) contains blades 1, a rim 2, a support ring 3, consisting of an input support semi-ring 4 and an output support semi-ring 5. Strong pinching of the blade in the apparatus is achieved by the fact that the blade is attached with a shank 6 in the hole 14 of the rim 2 (Fig. 3, Fig. 7), and for fastening in the groove 15 of the support ring 3, the blade has a shank 7, made according to the profile of the last root section of the pen 8 (Fig. 7), such a shank simplifies the manufacture of layers of composite material and molds for blade design.

A method for manufacturing a compressor guide vane apparatus from a composite material includes: cutting different sizes (Fig. 4) of layers of the material of the blades 1, while at least one layer includes a composite material: back 9, leading edge 10 and trough 11 (Fig. 5 ). Filling the mold begins with laying the material of the back 9 in the matrix 12, then the layers of the material of the blade 8 (Fig. 4) and the last material of the trough 11 is laid (Fig. 6). The punch 13 is installed and the mold is pressed and heated to the polymerization temperature of the composite material used. After disassembling the mold, a guide vane is obtained, having a shank 6 for installation in the rim 2 and a shank 7 for mounting in the groove 15 of the support ring 3 (Fig. 1, Fig. 2, Fig. 3, Fig. 7). The rim is produced by winding from threads or tows, polymerization is carried out, and holes 14 for the shank 6 of the blade 1 are produced by cutting on a press or milling (Fig. 7). For the manufacture of support semi-rings 4, 5, layers of composite material are cut, which are placed in a mold, pressed and polymerized, after disassembling the mold, a support semi-ring is obtained. The assembly of the guide vane apparatus is performed in the following order: the blade 1 with the shank 6 (Fig. 1, Fig. 2, Fig. 3) enters the hole 14 (Fig. 7) of the rim 2, and the shank 7 is placed in the grooves 15 of one of the supporting semirings, for example, the input 4, after placing all the blades, the output support semi-ring 5 is installed, aligning the grooves 15 with the shanks 7 of the blades (Fig. 2). Then both supporting half-rings are pressed, for example, with bolts, which ensures tight fastening of the blades.

This invention solves the problem of manufacturing the guide vanes of an aircraft engine compressor from a composite material with a significant simplification of the technological process and a decrease in the labor intensity of production, in addition, any defective part can be replaced during operation.

Claims (1)

A method for manufacturing an aircraft engine compressor guide vane apparatus from a composite material, including cutting material for blades, the final design of which is carried out in a mold, winding a rim from threads or bundles with subsequent polymerization, production of a support ring, while forming the internal aerodynamic surfaces of the rim gas path and support ring, characterized in that the blade on the peripheral side has a shank for fastening in the rim, a shank with a profile of the last root section of the blade feather for fastening in the support ring, holes in the rim for the blade shank are made by punching on a press or by milling, for the support half ring they are cut layers of composite material, put them in a mold, press, polymerize and disassemble the mold, thus obtaining inlet and outlet half rings that have grooves for fixing the blade root, assembling the blade apparatus t from the installation of the blade roots in the holes of the rim, then after installing all the blades with the shafts, the second support semi-ring is laid in one of the support semi-rings, aligning the grooves of the latter with the blade roots, both support semi-rings are compressed, for example, by bolts, while the blade roots are firmly fixed in the support ring.

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