CN109622923B - Preparation method of aircraft engine blade base - Google Patents
Preparation method of aircraft engine blade base Download PDFInfo
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- CN109622923B CN109622923B CN201811497592.7A CN201811497592A CN109622923B CN 109622923 B CN109622923 B CN 109622923B CN 201811497592 A CN201811497592 A CN 201811497592A CN 109622923 B CN109622923 B CN 109622923B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D19/00—Casting in, on, or around objects which form part of the product
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
Abstract
A preparation method of an aircraft engine blade base comprises the following steps of A, providing a casting device, wherein the casting device comprises a casting base, a positioning template and a casting cavity, and fixing the blade. And B, casting a low-melting-point alloy in the casting cavity, and taking out the blade after the low-melting-point alloy is cooled and solidified. And step C, providing a dissolving and shaping device, wherein the dissolving and shaping device comprises a shaping base, the shaping base is provided with a hot oil cavity, and an alloy part which is below the first horizontal plane and wraps the locking piece groove covering the top of the tenon tooth is immersed in hot oil in the hot oil cavity, so that the rectangular block is prepared. According to the preparation method of the blade base of the aircraft engine, provided by the invention, the measurement period of the blade can be greatly shortened by preparing the standard base, and meanwhile, the production cost and the maintenance cost can be reduced.
Description
Technical Field
The invention relates to the technical field of aero-engine production, in particular to a method for preparing a base for measuring blade parts in the production process of turbine blades of small and medium-sized aero-engines.
Background
In the manufacturing process of the aircraft engine, the turbine blade can be formed by casting a single blade part in a precision casting mode, and then the single blade part is assembled on the flange plate to form a turbine whole.
FIG. 1a is a schematic perspective view of a first stage turbine blade; FIG. 1b is a schematic perspective view of a two-stage turbine blade; FIG. 1c is a schematic perspective view of a free-turbine blade; FIG. 2a is a schematic illustration of a blade profile sizing of the first stage turbine blade of FIG. 1 a; FIG. 2b is a schematic illustration of platform sizing of the first stage turbine blade of FIG. 1 a; FIG. 2c is a schematic illustration of a measurement of the tip tab slot dimensions of the dovetail for the stage one turbine blade of FIG. 1 a; in fig. 2c, a schematic front view and a schematic left view of the measuring fixture during the measuring process are shown.
Referring to fig. 1a-2c, in the manufacturing process of a gas turbine, for each individual turbine blade casting produced through a precision casting process, it is generally required to measure the blade profile size of the blade body 11, the size of the platform 12 and the size of the locking plate slot 131 at the top of the tenon tooth 13 after the turbine blade 1 is cast, so as to judge whether the cast single blade is a qualified product.
In the existing measurement process, for the measurement of the blade profile size, as shown in fig. 2a, a pair of rolling rods 2 (corresponding special rolling rods 2, that is, rolling rods 2 with different diameters are designed for different types of blades 1) are required to clamp the tenon tooth 13 on a special vice, during the measurement, the rolling rods 2 are firstly aligned for establishing a coordinate system used during the blade measurement, and then a special measuring tool (not shown in the figure) is used for measuring the blade profile size of the blade body 11.
For the measurement of the dimension of the flange 12, as shown in fig. 2b, a special measuring tool is used to clamp all the tenon teeth 13, expose the flange 12, and measure the dimension of the flange 12 with a special measuring tool (not shown).
For the dimension measurement of the locking piece slot 131 at the top of the tenon tooth 13, as shown in fig. 2c, a special measurement tool needs to be used to clamp the tenon tooth 13 and expose the top tooth portion, so that the locking piece slot 131 can not be blocked, and then a special measurement tool (not shown in the figure) is used to measure the relevant dimension of the locking piece slot 131.
Although each individual turbine blade 1 produced by the precision casting process has a cylindrical process boss 14 with dimensional accuracy guaranteed, the process boss 14 is mainly used for clamping and positioning of subsequent machining processes in the existing production process, and the process boss 14 is not physically used (for example, clamping, positioning and the like) in the existing measurement process.
As shown in fig. 2a, in the conventional blade measurement process, the theoretical reference coordinate system of the blade 1 is generally established by using the rolling rods 2 tightly clamping the tenon teeth 13 of the blade 1 (generally, the first pair of concave parts clamped at two sides of the top teeth of the tenon teeth 13 as shown in fig. 2 a) to establish a datum plane, that is, an x-y plane is established according to the axes of two theoretically parallel rolling rods 2, the axis of the cylindrical process boss 14 of the blade 1 is taken as a z-axis, the intersection point of the z-axis and the x-y plane is taken as an origin, the x-axis passes through the origin and is parallel to the axis of the rolling rods 2, and the y-axis is perpendicular to the x-axis. In the theoretical reference coordinate system of the blade 1, the z-axis is used to indicate the position relationship among the blade body 11, the platform 12 and the tenon tooth 13, and it is usually directed in the direction from the tenon tooth 13 to the blade body 11, and the x-axis and the y-axis are mainly used to indicate the tooth shape of the tenon tooth 13, so the directions of the x-axis and the y-axis can be adjusted according to the need (e.g. the matching convenience with the reference coordinate system of the measuring tool during the measurement), that is, the direction of the x-axis may be the direction from the air inlet side of the blade to the air outlet side, or vice versa, and the direction of the y-axis may be the direction from the basin side to the back side of the blade, or vice versa.
During the measurement with different measuring tools or for different types of blades, the theoretical reference coordinate system can be translated according to the actual conditions of the measuring tools, i.e. for the measuring instruments to facilitate reading, the origin of the theoretical reference coordinate system of the blade 1 can be moved in the direction of the three coordinate axes by Δ x, Δ y, Δ z, respectively, so as to be able to coincide with the reference coordinate system of the measuring instrument. Of course, it will be appreciated by those skilled in the art that the theoretical reference frame of the blade may also be rotated as shown in figures 2b, 2c in order to facilitate operation of the surveying instrument.
As described above, for different turbine blades as shown in fig. 1a to 1c, the existing measurement process methods are all that, when measuring the blade profile of the blade body 11, a dedicated measurement tool is used to clamp the tenon tooth 13 (for example, a first pair of concave parts on both sides of the top tooth of the tenon tooth 13 are clamped by a pair of rolling bars 2 on a dedicated vice) to expose the blade profile, and the size of the blade profile is measured by positioning the tenon tooth 13; when the relevant dimension of the locking piece slot 131 at the top of the tenon tooth 13 is measured, replacing a special measuring tool, clamping most of the tenon teeth 13 and exposing the tops of the tenon teeth, thereby measuring the relevant dimension of the locking piece slot 131; when the size of the flange plate 12 is measured, a plurality of sets of special measuring tools need to be replaced according to the change of the measuring position, the tenon tooth 13 is clamped to expose the measured position of the flange plate 12, and the relevant size is measured.
The existing measuring method has a complex and complicated process, for example, when the blade profile is measured, in the process of clamping the roller bars 2 by using a vice, the horizontal degree of the two roller bars 2 can finally influence the precision of the blade profile data obtained by measurement, so that an operator has to have rich experience to ensure the efficiency of the process of clamping the roller bars 2; and for the special measuring tool for measuring the flange plate 12 and the locking plate groove 131, as shown in fig. 2b and 2c, if the gap of the installation groove is too large, the blade state after clamping is difficult to ensure to be consistent, and if the gap is too small, the blade is difficult to be installed, so that the manufacturing difficulty of the installation groove is large, and the precision is difficult to ensure. Moreover, in order to avoid damage to the blade, the hardness of the material used for manufacturing the special measuring tool (especially the mounting groove position) is generally lower than that of the blade 1, so that the mounting groove is easily worn during use, and the size is changed.
In the measuring process, each measuring part needs a special tool, so that each blade needs multiple sets of special tools, and the production cost is high. In addition, the large number of the tools also causes great management difficulty and increases the maintenance difficulty of the tools. And because the whole process is manually operated, the clamping and measuring process of each size requires a skilled operation skill of an operator.
The existing measuring process has low operation efficiency. For at least hundreds of finished products of various blade precision castings in each batch in actual production, each blade needs to be measured, so that the measuring process needs to consume a long time, and the measuring process can become one of important factors for prolonging the whole production period.
Disclosure of Invention
The technical problem to be solved by the present invention is to provide a method for manufacturing a blade base of an aircraft engine, so as to reduce or avoid the aforementioned problems.
In order to solve the technical problems, the invention provides a method for preparing an aircraft engine blade base, the base is used for measuring the blade profile size of a blade body of a turbine blade, the size of a flange plate and the size of a locking plate groove at the top of a tenon tooth, the base is a rectangular block which is cast and formed by low-melting point alloy and surrounds the tenon tooth, the locking plate groove is not covered by the low-melting point alloy, the turbine blade is provided with a theoretical reference coordinate system, the z axis of the theoretical reference coordinate system is coincident with the axis of a process boss of the blade, the x-y plane of the theoretical reference coordinate system can be established by two axes of a clamping state of two standard rolling rods which can clamp a first pair of concave parts at two sides of the top tooth of the tenon tooth, the intersection point of the z axis and the x-y plane is an origin, and the x axis passes through the origin and is parallel to the axes of the rolling rods, the y-axis is perpendicular to the x-axis. The rectangular block comprises a first side elevation, a second side elevation, a third side elevation and a fourth side elevation which are sequentially connected, the first side elevation and/or the third side elevation is parallel to an x axis of the theoretical reference coordinate system, the second side elevation and/or the fourth side elevation is parallel to a y axis of the theoretical reference coordinate system, the rectangular block further comprises a first horizontal plane which is perpendicular to a z axis of the theoretical reference coordinate system and close to the locking piece groove, and the minimum distance between the top surface of the rectangular block and the edge plate in the z axis direction is not less than 2 mm. Which comprises the following steps of,
step A, providing casting equipment, wherein the casting equipment comprises a casting base, a positioning sample plate and a casting cavity, the casting base is connected with a first lifting arm capable of lifting, the first lifting arm is rotatably connected with a first process boss fixing device through a bearing, the process boss of the blade is inserted and installed in the first process boss fixing device, the blade is hoisted on the first lifting arm, the positioning sample plate corresponding to the blade is installed on the casting base, and the positioning sample plate 42 is attached to the edge plate to fix the blade.
And B, pouring a low-melting-point alloy in the casting cavity, and taking out the blade provided with the rectangular block after the low-melting-point alloy is cooled and solidified.
And step C, providing a dissolving and shaping device, wherein the dissolving and shaping device comprises a shaping base 51, the shaping base is connected with a second lifting arm capable of lifting, the second lifting arm is provided with a second process boss fastening device, the process boss of the blade is inserted into the second process boss fixing device, so that the blade is hung on the second lifting arm, the shaping base is provided with a hot oil cavity, the hot oil cavity is arranged below the second lifting arm, hot oil with the temperature not lower than 180 ℃ is injected into the hot oil cavity, and an alloy part of the locking piece groove, which is wrapped and covers the top of the tenon tooth, below the first horizontal plane is immersed into the hot oil of the hot oil cavity, so that the locking piece groove is exposed from the rectangular block. And lifting the second suspension arm to enable the tenon tooth to be separated from contact with hot oil in the hot oil cavity, so that the rectangular block is prepared.
Preferably, in step a, at least one side of the casting cavity is formed by a removable flapper.
Preferably, in step a, at least one side surface of the casting cavity is an inclined surface inclined outward.
Preferably, in step a, the casting cavity is a T-shaped cavity, and the T-profile of the casting cavity is a horizontal profile for forming the first horizontal plane.
Preferably, in step C, the second process boss fixing device is rotatably connected to the second boom through a bearing, and the rectangular block rotates the blade at a rotation speed of 10-20 rpm while being immersed in hot oil.
According to the preparation method of the blade base of the aircraft engine, the standardized base is prepared, so that the measurement period of the blade can be greatly shortened, and meanwhile, the production cost and the maintenance cost can be reduced.
Drawings
The drawings are only for purposes of illustrating and explaining the present invention and are not to be construed as limiting the scope of the present invention. Wherein the content of the first and second substances,
FIG. 1a is a schematic perspective view of a first stage turbine blade;
FIG. 1b is a schematic perspective view of a two-stage turbine blade;
FIG. 1c is a schematic perspective view of a free-turbine blade;
FIG. 2a is a schematic illustration of a blade profile sizing of the first stage turbine blade of FIG. 1 a;
FIG. 2b is a schematic illustration of platform sizing of the first stage turbine blade of FIG. 1 a;
FIG. 2c is a schematic illustration of a measurement of the tip tab slot dimensions of the dovetail for the stage one turbine blade of FIG. 1 a;
FIG. 3a is a schematic view of a base prepared by a method for preparing an aircraft engine blade base according to an embodiment of the invention, used for measuring the profile dimension of a turbine blade;
FIG. 3b is a schematic illustration of platform sizing of the turbine blade of FIG. 3 a;
FIG. 3c is a schematic illustration of a tooth top cleat slot size measurement taken on the turbine blade of FIG. 3 a;
FIG. 4a is a schematic partial cross-sectional structural view of a casting apparatus for preparing the susceptor of FIG. 3 a;
FIG. 4b is a schematic partial cross-sectional structural view of the casting apparatus of FIG. 4a in a top view;
fig. 5 is a schematic partial sectional structural view of a dissolution reshaping apparatus for reshaping the rectangular block prepared in fig. 4 a.
Detailed Description
In order to more clearly understand the technical features, objects, and effects of the present invention, embodiments of the present invention will now be described with reference to the accompanying drawings. Wherein like parts are given like reference numerals.
FIG. 1a is a schematic perspective view of a first stage turbine blade; FIG. 2a is a schematic illustration of a blade profile sizing of the first stage turbine blade of FIG. 1 a; FIG. 3a is a schematic view of a base prepared by a method for preparing an aircraft engine blade base according to an embodiment of the invention, used for measuring the profile dimension of a turbine blade; FIG. 3b is a schematic illustration of platform sizing of the turbine blade of FIG. 3 a; FIG. 3c is a schematic diagram of a tooth top cleat slot size measurement taken on the turbine blade of FIG. 3 a; 4a is a schematic partial cross-sectional structural view of a casting apparatus for preparing the susceptor of FIG. 3 a; FIG. 4b is a schematic partial cross-sectional structural view of the casting apparatus of FIG. 4a in a top view; fig. 5 is a partial cross-sectional structural schematic view of a dissolution reshaping apparatus for cutting the rectangular block prepared in fig. 4 a. Referring to fig. 1a, 2a and 3a-5, the invention provides a method for preparing an aircraft engine blade base, the base is used for measuring the blade profile size of a blade body 11 of a turbine blade 1, the size of a flange plate 12 and the size of a locking plate groove 131 at the top of a tenon tooth 13, the base is a rectangular block 3 which is formed by casting a low-melting-point alloy and surrounds the tenon tooth 13, the locking plate groove 131 is not covered by the low-melting-point alloy and exposes the rectangular block 3, the turbine blade 1 is provided with a theoretical reference coordinate system, the z axis of the theoretical reference coordinate system is coincident with the axis of a process boss 14 of the blade 1, the x-y plane of the theoretical reference coordinate system can be established by two standard rolling rods 2 which can clamp a first pair of concave parts at two sides of a top tooth of the tenon tooth 13 in a clamping state, the intersection point of the z axis and the x-y plane is an origin, the x-axis passes through the origin and is parallel to the axis of the roller 2, and the y-axis is perpendicular to the x-axis. The rectangular block 3 comprises a first side elevation, a second side elevation, a third side elevation and a fourth side elevation which are connected in sequence, the first side elevation and/or the third side elevation is parallel to the x axis of the theoretical reference coordinate system, the second side elevation and/or the fourth side elevation is parallel to the y axis of the theoretical reference coordinate system, the rectangular block 3 further comprises a first horizontal plane 31 which is perpendicular to the z axis of the theoretical reference coordinate system and close to the locking piece groove 131, and the minimum distance between the top surface of the rectangular block and the flange plate 12 in the z axis direction is not less than 2 mm. Which comprises the following steps of,
step A, providing a casting device 4, wherein the casting device 4 comprises a casting base 41, a positioning template 42 and a casting cavity 43, the casting base 41 is connected with a first lifting arm 411 which can be lifted, a bearing is arranged on the first lifting arm 411, a first process boss fixing device 44 is rotatably connected through a bearing, the process boss 14 of the blade 1 to be tested is inserted and installed in the first process boss fixing device 44, the blade 1 is locked in the first process boss fixing device 44 through a screw, so that the blade 1 is hung on the first suspension arm 411, by adjusting and locking the position of the first boom 411 in the vertical direction, the directions of the x, y, z axes of the theoretical reference frame of the blade 1 can be fixed, but the blade 1 (i.e. the theoretical reference frame) can be rotated on the first boom 411. Then, the positioning template 42 corresponding to the blade 1 to be measured is mounted on the casting base 41, so that the angular direction of the blade 1 can be fixed by the contact between the positioning template 42 and the flange 12 of the blade 1, and thus all degrees of freedom of the blade 1 are fixed.
The first process boss fixing device 44 is provided with an insertion hole which is matched (clearance fit) with the process boss 14, and a fixing screw is connected in the insertion hole, so that the connection relationship between the blade 1 and the first process boss fixing device can be fixed by inserting the process boss 14 into the insertion hole and tightening the screw. The process boss 14 of the blade 1 is mounted on the first process boss fixture 44, which makes it possible to fix, immovable, but rotatable along the bearing center, the x, y, z directions of the theoretical reference coordinate system of the blade 1. For different types of turbine blades, a dedicated positioning template 42 can be manufactured for each type of the blade 1, as shown in fig. 4a and 4b, the positioning template 42 can be fixedly connected with the casting base 41 through fastening screws, and through the auxiliary positioning of the positioning template 42, the blade 1 connected with the process boss fastening device 44 can be ensured to stably stay in the casting cavity 43, and the theoretical reference coordinate system of the blade 1 can be ensured to be parallel to the coordinate system of the side wall of the casting cavity 43. That is, two opposite side walls of the casting cavity 43 are respectively parallel to the x-axis and the y-axis of the theoretical reference coordinate system, and when the different types of blades 1 are replaced, the different types of blades 1 can be positioned only by loosening fastening screws, and removing and replacing the corresponding positioning templates 42.
In fig. 4a and 4b, the casting cavity 43 is shown as a single piece, but it will be understood by those skilled in the art that as a casting cavity, at least one side of the casting cavity 43 may be formed by a removable flap for facilitating removal of the rectangular block 3 after casting, and of course, at least one side of the casting cavity 43 may be inclined to the outside.
The casting cavity 43 may be a T-shaped cavity as shown in fig. 4a, so that the T-shaped surface 431 of the casting cavity 43 may be used as a horizontal surface for forming the first horizontal surface 31, and since the casting process completely covers the locking piece groove 131 covering the top of the tenon tooth 13, the casting cavity 43 may be a T-shaped cavity, which may prevent the first horizontal surface 31 formed by the T-shaped surface 431 from being damaged in the subsequent process of removing the excessive low-melting-point alloy structure and may be used as a reference surface for facilitating subsequent operations.
The side wall of the casting cavity 3 where the positioning template 42 is located and the adjacent side walls can be used as forming side walls for ensuring that at least two side walls of the rectangular block 3 can be respectively parallel to the x axis and the y axis of the theoretical reference coordinate system of the blade 1.
And step B, casting a low-melting-point alloy in the casting cavity 43, brushing the low-melting-point alloy with a brush dipped in cold water after casting, waiting for about 5 seconds, loosening the screw of the process boss fixing device 44 after the low-melting-point alloy is cooled and solidified, taking down the movable baffle of the casting cavity 43 when at least one side surface of the casting cavity 43 is formed by a detachable movable baffle, and lifting the suspension arm 411 to take out the blade 1 provided with the rectangular block 3. When at least one side of the casting cavity 43 is inclined outwardly. The boom 411 can be lifted directly and the blade 1 provided with the rectangular block 3 can be taken out.
Step C, providing a dissolving and shaping device 5, wherein the dissolving and shaping device 5 comprises a shaping base 51, the shaping base 51 is connected with a second lifting arm 511 capable of lifting, the second lifting arm 511 is provided with a second process boss fastening device 54, the process boss 14 of the blade 1 to be measured is inserted and installed in the second process boss fixing device 54, the blade 1 is locked in the second process boss fixing device 54 through a screw, the blade 1 is hung on the second lifting arm 511, the shaping base 51 is provided with a hot oil cavity 52, the hot oil cavity 52 is arranged below the second lifting arm 511, hot oil with the temperature not lower than 180 ℃ is filled in the hot oil cavity 52, and the alloy part, which is wrapped and covered on the top of the tenon tooth 13, below the first horizontal plane 31 can be immersed in the hot oil cavity 52 by adjusting the height position of the second lifting arm 511, this causes the alloy covering the tab slot 131 at the top of the tenon tooth 13 to be dissolved, thereby exposing the tab slot 131 from the rectangular block 3. The second boom 511 is lifted to bring the tenon tooth 13 out of contact with the hot oil of the hot oil chamber 52, and the blade 1 is removed, completing the preparation of the rectangular block 3.
As shown in fig. 5, an oil outlet may be disposed at the bottom of the hot oil chamber 52, and an oil filling port may be disposed at the top thereof, so that the hot oil chamber 52 may be connected to the hot oil circulation processing apparatus 6 through a pipeline, thereby ensuring the temperature of the hot oil in the hot oil chamber 52 and timely recovering the low melting point alloy dissolved in the hot oil.
The hot oil circulation treatment device 6 may comprise a cooling tank (not shown) and a heater (not shown) connected in sequence, and the specific structure may refer to the structure of the cooling tank and the heater adopted in the blade cavity low melting point alloy removing device provided by the inventor's team in chinese patent 201611189008.2, and will not be described herein again.
After the blade 1 is hung on the second process boss fixing device 54, the z-axis position of the blade 1 is fixed on the second suspension arm 511, so that the position of the rectangular block 3 of the blade 1 immersed in the hot oil chamber 52 can be controlled by controlling the lifting and lowering of the second suspension arm 511. Of course, as shown in fig. 5, the dimension of the top surface of the hot oil chamber 52 in at least one direction is set to be smaller than the dimension of the rectangular block 3, so that the contact between the first horizontal surface 31 and the top surface of the hot oil chamber 52 can control the position of the rectangular block 3 immersed in the hot oil, and since the hot oil is externally heated and then injected into the hot oil chamber 52, the overall temperature of the shaping base 51 around the hot oil chamber 52 can be ensured without causing melting deformation of the first horizontal surface 31, thereby simplifying the operation process of this step.
If the rectangular block 3 is left to stand in hot oil only, it usually takes 10-15 minutes to ensure that the alloy covering the tab slot 131 is completely dissolved.
The second process boss fixing device 54 may also be rotatably connected to the second suspension arm 511 through a bearing, so that after the blade 1 is hoisted and immersed in hot oil, the blade 1 may be rotated, thereby increasing the speed of dissolving the alloy, and in order to better control the rotation of the blade 1, the second process boss fixing device 54 may be fixedly connected to the bearing on the second suspension arm 511, and may be provided with a rod portion 541 extending out of the top surface of the second suspension arm 511, so that the motor 7 may be connected by a belt, a gear, and the like arranged on the extended rod portion 541, thereby more precisely controlling the rotation speed of the blade 1.
When the rotating speed of the blade 1 is controlled to be 10-20 revolutions per minute, the rectangular block 3 is soaked in hot oil for 5-8 minutes to completely dissolve the alloy coating the locking piece groove 131.
Because the low-melting-point alloy has good hardness and strength, the rectangular block 3 surrounding the tenon tooth 13 is formed by casting the low-melting-point alloy, and the low-melting-point alloy shrinks towards the tenon tooth 13 after being cooled, solidified and shaped, so that the tenon tooth 13 is firmly clamped by the tooth profile of the tenon tooth 13.
Since the first side elevation and/or the third side elevation of the rectangular block 3 are parallel to the x-axis of the theoretical reference coordinate system, the second side elevation and/or the fourth side elevation are parallel to the y-axis of the theoretical reference coordinate system, and the first horizontal plane 31 is perpendicular to the z-axis of the theoretical reference coordinate system, i.e. the first horizontal plane 31 is parallel to the x-y plane, the reference coordinate system of the blade 1 can be defined by limiting the outer surface of the rectangular block 3, and the theoretical reference coordinate system of the blade 1 can be easily made parallel to the reference coordinate system of the measuring instrument, so that the blade 1 can be conveniently positioned and fixed by using similar fixtures capable of limiting at least three surfaces in each measuring stage, and the reference coordinate system of the measuring instrument can be conveniently adjusted to coincide with the theoretical reference coordinate system of the blade 1, the measuring tool and the measuring tool structure in each measuring process can be simplified. And improve the measurement efficiency.
The first side elevation and/or the third side elevation and the second side elevation and/or the fourth side elevation of the rectangular block 3 are mainly used for clamping and positioning, and in the subsequent measurement process, the reference coordinate system of the blade 1 can be controlled by positioning the process boss 14, so that the blade 1 and the flange plate 12 only need to be not too close to each other and have a certain distance (for example, the minimum distance is not less than 5mm, the maximum distance is not more than 30mm, and if the distance is too large, the rectangular block 3 is easy to have a large volume, and the energy consumption of the manufacturing process is wasted), therefore, in the step a, when the blade 1 to be measured is fixed, only the flange plate 12 needs to be kept at a certain distance from the side wall of the casting cavity 43, and of course, by arranging the positioning sample plate 42, the coordinate system of the rectangular block 3 cast by the same type of the blade 1 can be stabilized, thereby facilitating subsequent batch standardization measurement.
The minimum distance between the top surface of the rectangular block 3 and the flange 12 in the z-axis direction can be controlled to be larger than 2mm, so that the space requirement for measuring the size of the flange 12 can be ensured.
The minimum distance between the first horizontal surface 31 and the locking piece slot 131 in the z-axis direction can be greater than 1.5 mm. This leaves sufficient measurement space for the locking piece slot 131.
In practice, for 3 turbine blades of a certain type of engine, casting equipment can be combined into one set when the method is adopted, and the casting forming of different types of blade bases can be realized only by replacing the positioning templates. And the structure of the measuring tool and the measuring tool in the measuring process is greatly simplified, so that the preparation time for replacing the measuring tool is greatly shortened, and compared with the original process method in the background technology, the time for construction period can be shortened by about 50%. Moreover, because the measuring tools are reduced, the production cost is greatly reduced, and the tool cost can be reduced by about 60 percent compared with the original measuring method in the background technology. In the measuring process, because the planes such as the side vertical face and the horizontal plane of the rectangular block 3 are positioned and clamped, the high-precision loose block positioning in the background technology can be avoided, the manufacturing cost of the tool is reduced, and the difficulty in tool maintenance is also reduced.
According to the preparation method of the blade base of the aircraft engine, provided by the invention, the measurement period of the blade can be greatly shortened by preparing the standard base, and meanwhile, the production cost and the maintenance cost can be reduced.
It should be appreciated by those of skill in the art that while the present invention has been described in terms of several embodiments, not every embodiment includes only a single embodiment. The description is given for clearness of understanding only, and it is to be understood that all matters in the embodiments are to be interpreted as including technical equivalents which are related to the embodiments and which are combined with each other to illustrate the scope of the present invention.
The above description is only an exemplary embodiment of the present invention, and is not intended to limit the scope of the present invention. Any equivalent alterations, modifications and combinations can be made by those skilled in the art without departing from the spirit and principles of the invention.
Claims (5)
1. A method for preparing an aircraft engine blade base, which is characterized in that the base is used for measuring the blade profile size of a blade body of a turbine blade, the size of a flange plate and the size of a locking plate groove at the top of a tenon, the base is a rectangular block which is formed by casting low-melting point alloy and surrounds the tenon, the locking plate groove is not covered by the low-melting point alloy, the turbine blade is provided with a theoretical reference coordinate system, the z axis of the theoretical reference coordinate system is coincident with the axis of a process boss of the blade, the x-y plane of the theoretical reference coordinate system is established by two axes of two standard rolling rods which can clamp a first pair of concave parts at two sides of the top tooth of the tenon in a clamping state, the intersection point of the z axis and the x-y plane is the original point, the x axis is parallel to the axes of the rolling rods through the original point, and the y axis is perpendicular to the x axis, the rectangular block comprises a first side elevation, a second side elevation, a third side elevation and a fourth side elevation which are connected in sequence, the first side elevation and/or the third side elevation is parallel to an x-axis of the theoretical reference coordinate system, the second side elevation and/or the fourth side elevation is parallel to a y-axis of the theoretical reference coordinate system, the rectangular block further comprises a first horizontal plane which is vertical to a z-axis of the theoretical reference coordinate system and close to the locking piece groove, and the minimum distance between the top surface of the rectangular block and the edge plate in the z-axis direction is not less than 2mm, and the rectangular block comprises the following steps,
step A, providing casting equipment, wherein the casting equipment comprises a casting base, a positioning sample plate and a casting cavity, the casting base is connected with a first lifting arm capable of lifting, the first lifting arm is rotatably connected with a first process boss fixing device through a bearing, the process boss of the blade is inserted and installed in the first process boss fixing device, the blade is hoisted on the first lifting arm, the positioning sample plate corresponding to the blade is installed on the casting base, the positioning sample plate is attached to the edge plate, and the blade is fixed,
step B, casting a low-melting-point alloy in the casting cavity, taking out the blade provided with the rectangular block after the low-melting-point alloy is cooled and solidified,
step C, providing a dissolving and shaping device, wherein the dissolving and shaping device comprises a shaping base, the shaping base is connected with a second lifting arm capable of lifting, the second suspension arm is provided with a second process boss fixing device, the process boss of the blade is inserted and installed in the second process boss fixing device, so that the blade is hoisted on the second suspension arm, the shaping base is provided with a hot oil cavity, the hot oil cavity is arranged below the second lifting arm, hot oil with the temperature not lower than 180 ℃ is injected into the hot oil cavity, so that the alloy part below the first horizontal plane and wrapping the locking piece groove covering the top of the tenon tooth is immersed into the hot oil in the hot oil cavity, thereby exposing the lock piece slot from the rectangular block, lifting the second suspension arm, and separating the tenon tooth from the hot oil of the hot oil cavity, thereby completing the preparation of the rectangular block.
2. The method of claim 1 wherein in step a, at least one side of the casting cavity is formed by a removable flapper.
3. The method of claim 1, wherein in step a, at least one side of the casting cavity is beveled to an outward slope.
4. The method of claim 1 wherein in step a, the casting cavity is a T-cavity and the T-profile of the casting cavity is a horizontal profile for forming the first horizontal surface.
5. The method of claim 1, wherein in step C, the second process boss fixture is rotatably coupled to the second boom arm by a bearing, and the rectangular block spins the blades at a speed of 10-20 rpm while immersed in hot oil.
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| CN201811497592.7A CN109622923B (en) | 2018-12-07 | 2018-12-07 | Preparation method of aircraft engine blade base |
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| CN201811497592.7A CN109622923B (en) | 2018-12-07 | 2018-12-07 | Preparation method of aircraft engine blade base |
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| CN109622923B true CN109622923B (en) | 2020-09-11 |
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| DE102009036405A1 (en) * | 2009-08-06 | 2011-02-10 | Mtu Aero Engines Gmbh | Repair of turbine components and solder alloy for this |
| CN202304719U (en) * | 2011-10-20 | 2012-07-04 | 常州市三维技术成套设备有限公司 | Arc fir tree blade root measuring device |
| CN105436838B (en) * | 2015-11-05 | 2018-02-23 | 西安航空动力股份有限公司 | A kind of moving turbine blade machining process |
| CN106767237B (en) * | 2016-11-23 | 2018-12-25 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of processing method controlling moving turbine blade tenon tooth wall thickness |
| CN107984340B (en) * | 2017-12-01 | 2019-06-11 | 中国航发沈阳黎明航空发动机有限责任公司 | Reference Transforming fixture and application method before a kind of essence casting blade tenon tooth is processed |
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