CN112414334B

CN112414334B - Use method of liquid supply device for measuring angle of small micropore of blade

Info

Publication number: CN112414334B
Application number: CN202011219129.3A
Authority: CN
Inventors: 初文潮; 屈涛; 廖鑫; 邹沙; 李加森; 金莱
Original assignee: AECC South Industry Co Ltd
Current assignee: AECC South Industry Co Ltd
Priority date: 2020-11-04
Filing date: 2020-11-04
Publication date: 2021-10-22
Anticipated expiration: 2040-11-04
Also published as: CN112414334A

Abstract

A method for using a liquid supply device for measuring the angle of a small micropore of a blade comprises the following steps of A, installing a rigidity measuring needle on a gas film hole, and then clamping the blade on a blade clamping seat. And step B, respectively finding and calibrating the positions of the Z axis of the blade, which are vertical and parallel to the projection light, simultaneously measuring and obtaining the measurement data of the rigid measurement needle assembled in the step A at the two positions, and step C, pulling out the rigid measurement needle to finish the acquisition of sample data. And D, obtaining the range of the image data of the liquid column in the optical measurement corresponding to the design data through calculation, measuring the measurement data of the coloring solution for other blades, and comparing the measurement data with the data range obtained through sample data calculation. The use method of the liquid supply device for measuring the angle of the small micropore of the blade provided by the invention greatly improves the measurement efficiency.

Description

Use method of liquid supply device for measuring angle of small micropore of blade

Technical Field

The invention relates to the technical field of measurement, in particular to a using method of a device for measuring the real angle of a small micropore on an aircraft engine blade by using liquid.

Background

For example, for a turbine blade, in order to ensure that the turbine blade still has good mechanical properties under high-temperature and high-pressure environments, the blade needs to be cast into a hollow structure, an exhaust channel is arranged in an inner cavity, and a plurality of film holes are processed on a blade body of the blade, particularly on an exhaust edge of the blade body, so that cold air entering the inner cavity can be sprayed out from the film holes of the blade body, and a layer of cold air protective layer is formed on the blade body while certain blade body heat is taken away, thereby further reducing the temperature of the blade body and ensuring that the blade is not ablated by high-temperature and high-pressure gas. Therefore, the angle of each air film hole has strict requirements, so that the cold air can be ensured to uniformly cover all areas of the blade body,

FIG. 1a is a schematic perspective view of an aircraft engine blade; FIG. 1b is a schematic perspective view of the blade of FIG. 1a from another perspective; FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a; FIG. 1d is a schematic cross-sectional structural view of the blade body of the blade of FIG. 1 a; FIG. 1e is a schematic diagram of the cross-sectional structure A-A of FIG. 1 d; wherein X, Y, Z marked in fig. 1c, 1d and 1e is a blade measurement coordinate system, which is defined in the ministry of aviation industry of china, and is not repeated herein. Referring to fig. 1a to 1e, the aircraft engine blade 100 adopts a hollow internal cooling structure, a first air inlet 11 which is formed by casting and communicated with an inner cavity and is close to one side of a front edge and a second air inlet 12 which is formed by casting and is close to one side of a rear edge are arranged at the bottom of the blade, a blade tip groove 30 with the depth of 2mm is arranged at the blade tip, an air outlet is arranged in the blade tip groove 30, the rear edge is provided with a processing surface 20 parallel to a Z axis, and a plurality of air film holes 21 communicated with the inner cavity are arranged on the processing surface 20.

The first air inlet 11, the second air inlet 12 and the air outlets in the blade tip slots 30 are directly formed during casting, and the machining surface 20 and the air film holes 21 are formed in a subsequent machining process, wherein the machining surface 20 is machined firstly, and then the air film holes 21 are formed in the machining surface 20 in an electric spark machining mode and then communicated with the inner cavity of the aircraft engine blade 100.

The aperture of the air film hole 21 is generally between phi 0.25mm and phi 0.5mm, the depth is not less than 6mm, at least one group of air film holes 21 are arranged on the processing surface 20, and the aperture and the inclination angle of each group of air film holes 21 are the same. That is, the processing surface 20 may be provided with more than one set of the film holes 21 with different hole diameters, and fig. 1e shows that the same set of the film holes 21 with the same hole diameter are provided on the processing surface 20.

As for the film holes 21, in the production and processing process of the aircraft engine blade 100, connectivity between the film holes 21 and the inner cavity can be verified through a water flow experimental mode, that is, a closable flexible joint is used to be in sealed communication with the tenon parts of the aircraft engine blade 100 (that is, with the first air inlet 11 and the second air inlet 12), and pressurized water flow is input to observe and detect whether all the film holes 21 can drain water, so as to judge whether the film holes 21 are communicated with the inner cavity or not. In addition, as described in a method for measuring the air flow of a turbine blade machine with holes provided in the chinese patent ZL2017112497983 by the inventor, the flow data of the film hole 21 can also be directly measured and obtained.

However, as shown in fig. 1d and 1e, the included angle α of the film hole 21 with respect to the X-axis and the included angle β with respect to the Z-axis of the blade measurement coordinate system also have certain design requirements, for example, the included angle α of the film hole 21 with respect to the X-axis of the blade measurement coordinate system may be designed to be 61.5 ° ± 30 ', and the included angle β of the film hole 21 with respect to the Z-axis of the blade measurement coordinate system may be designed to be 80 ° ± 30'. Because the aperture of the gas film hole 21 is too small, at present, no disclosed technical scheme can be used for directly measuring the angle of the gas film hole 21.

In the existing production process, a large hole with the diameter of 1mm is machined on the aviation engine blade 100 which is machined instead after the parameters of electric spark machining equipment are set, a standard measuring rod with the diameter of 1mm is inserted into a machined hole, the angle of the standard measuring rod is measured by a three-coordinate measuring machine, if the angle is qualified, the angle is qualified through adjusting the angle of a machine tool and/or a clamp, and a small hole with the diameter required by a drawing is reprocessed.

The prior art guarantee method has the following defects:

1. only whether the angle (namely the processing parameter) adjusted by the clamp and/or the machine tool is correct can be judged, for example, the angle is measured by processing the large hole with phi 1 and matching with a measuring rod, the angle of the small hole with the diameter phi 0.25 is qualified by default after the angle is qualified, but the actual large hole with phi 1 is not directly related to the diameter phi 0.25 (the parameter setting of the electric spark processing equipment is different), the error of the measuring method is large, and the error is usually between 1 and 1.5 degrees.

2. The inner cavity of the aero-engine blade 100 is provided with complex loops and reinforcing ribs, interference is easily generated after the measuring rod enters the inner cavity, the measuring rod is inclined to one side, and the measuring angle is inaccurate.

3. The aero-engine blade 100 is made of high-temperature alloy materials, so that the machining difficulty is high, the machining time is long, and generally, about 15 minutes is needed for machining a hole with the diameter of 1 mm.

4. The aero-engine blade 100 with the phi 1 hole machined can only be scrapped, 2-3 blades need to be scrapped during machining of each batch of blades, the price of each blade is 1 to 3 thousands, and waste is extremely large.

Through experimental research and analysis, the inventor group submits three patent applications of 2019111027142 a method for measuring the angle of the small micropore of the blade, 2019111032761 a measuring needle for measuring the angle of the small micropore of the blade and 2019111032776 a method for using the measuring needle for measuring the angle of the small micropore of the blade in 2019, 11 and 13, provides a set of complete technical scheme for directly measuring the angle of the air film hole of the blade by using a rigid measuring needle, can obtain real air film hole angle data, and does not cause physical damage to the blade in the measuring process. Therefore, each blade can be detected, and the qualification rate of finished products can be greatly improved.

However, in the above-mentioned solution of performing measurement by using a rigid measurement needle, although the data accuracy is high, the measurement needle needs to be assembled in at least one of the air film holes 21 in each group of the air film holes 21 on each blade of each batch, and the assembly of the measurement needle is relatively complicated, so the labor intensity of workers is still relatively high, and the assembly time of the measurement needle is relatively long, so the overall measurement efficiency still needs to be improved.

Disclosure of Invention

The invention aims to provide a liquid supply device for measuring the angle of a small micropore of a blade, and a use method thereof, so as to reduce or avoid the problems.

In order to solve the technical problems, the invention provides a use method of a liquid supply device for measuring the angle of a small micropore of a blade, which is used for directly measuring the actual angle of a gas film hole of an aircraft engine blade, the liquid supply device comprises a base arranged on a workbench of a digital horizontal projector, a first shaft rotary table for adjusting the horizontal rotation angle is fixedly arranged on the base, the first shaft rotary table is fixedly connected with a second shaft rotary table for adjusting the vertical rotation angle through a first connecting arm, the second shaft rotary table is provided with a second connecting arm, the second connecting arm is detachably connected with a blade clamping seat, the blade clamping seat is detachably connected with the aircraft engine blade, the base is connected with a liquid recovery device in a lifting way, the liquid recovery device is connected with a solution barrel through a return pipeline, and the solution barrel is detachably connected with the blade clamping seat through a liquid supply pipeline, the liquid supply pipeline is provided with a pressure pump, coloring solution is pre-filled in the solution barrel, the liquid recovery device is provided with a U-shaped cavity, and the width of the opening of the U-shaped cavity can be slightly larger than the width of the processing surface. Which comprises the following steps of,

step A, plugging an air outlet of the blade tip groove of the aero-engine blade, then installing a rigidity measuring needle on one air film hole, then clamping the aero-engine blade on the blade clamping seat, and then plugging a clamping gap of the blade clamping seat.

And B, assembling the blade clamping seat clamping the aero-engine blade on the second connecting arm, enabling the machined surface to face downwards, adjusting the second axis rotary table to enable the machined surface to be kept horizontal, namely ensuring that the Z axis of the aero-engine blade is kept horizontal, adjusting the first axis rotary table to respectively find and calibrate the positions of the Z axis of the aero-engine blade, which are vertical and parallel to the projection light of the digital horizontal projector, and simultaneously measuring and obtaining measurement data of the rigidity measuring needle assembled in the step A at the two positions, namely an included angle alpha of the air film hole relative to the X axis of a blade measuring coordinate system and an included angle beta of the air film hole relative to the Z axis. If the measured data does not meet the design requirements, the aero-engine blade is a non-qualified product, at the moment, the aero-engine blade needs to be replaced, the step A and the step B are repeated, if the measured data meets the design requirements, the next step is carried out,

step C, keeping the Z axis of the blade of the aircraft engine at one of positions vertical or parallel to the projection light of the digital horizontal projector, pulling out the rigid measuring needle, respectively connecting the solution barrel with the blade holder and the liquid recovery device, adjusting the position of the liquid recovery device to enable the opening of the U-shaped cavity to be close to the processing surface, starting the pressure pump until the liquid supply pressure is stable, then adjusting the position of the liquid recovery device to enable the opening of the U-shaped cavity to be far away from the processing surface by at least 6mm, then measuring the measurement data of the air film hole assembled from the rigid measuring needle at the position, recording the measurement data, closing the pressure pump, lowering the liquid recovery device after the liquid does not leak from the air film hole, and then adjusting the first axis, the Z axis of the blade of the aircraft engine is located at the other position perpendicular to or parallel to the projection light of the digital horizontal projector, the position of the liquid recovery device is reset, the opening of the U-shaped cavity is made to be close to the machined surface, the pressure pump is started until the liquid supply pressure is stable, then the position of the liquid recovery device is adjusted, the opening of the U-shaped cavity is made to be far away from the machined surface by at least 6mm, then the measurement data of the air film hole assembled from the rigid measurement needle at the position can be measured, the measurement data is recorded, the pressure pump is closed, and after the air film hole does not leak liquid any more, the blade holder is taken down, and the acquisition of sample data is completed.

And D, after the sample data acquisition is completed, calculating to obtain the range of the image data of the liquid column corresponding to the design data in the optical measurement, so that for other aviation engine blades, the measurement data of the coloring solution can be measured according to the operation of the step C, and then compared with the data range obtained by calculating the sample data, the design requirement is met in the range, otherwise, the product is an unqualified product.

Preferably, in step a, the air outlet of the blade tip groove of the aircraft engine blade is blocked by using yellow wax.

Preferably, in step C, the liquid supply pressure is regulated to be stable at 0.065MPa or 0.08 MPa.

Preferably, the solution tank holds 50 liters of coloring solution.

Preferably, the coloring solution is a copper sulfate solution or a mixture of a commercially available ink and water.

Preferably, a stirring blade is arranged in the solution barrel.

Preferably, a filter screen is further arranged at the interface of the liquid supply pipeline in the solution barrel.

The use method of the liquid supply device for measuring the angle of the small micropore of the blade provided by the invention can be used for quickly and visually and directly measuring the angle of the air film hole of the blade on a digital horizontal projector by utilizing self-circulation coloring liquid, so that real air film hole angle data is obtained, and the measurement efficiency is greatly improved.

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 an aircraft engine blade;

FIG. 1b is a schematic perspective view of the blade of FIG. 1a from another perspective;

FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a;

FIG. 1d is a schematic cross-sectional structural view of the blade body of the blade of FIG. 1 a;

FIG. 1e is a schematic diagram of the cross-sectional structure A-A of FIG. 1 d;

FIG. 2 is a schematic structural diagram of a liquid supply device for measuring the angle of a small pore of a blade according to an embodiment of the present invention in a use state;

FIG. 3 is a schematic diagram of a screen display effect of the projection imaging of FIG. 2;

FIG. 4 is a schematic view of the apparatus of FIG. 2 in another use state;

FIG. 5 is a diagram illustrating a screen display effect of the projection imaging of FIG. 4;

FIG. 6 is a schematic perspective view of the second connecting arm of FIG. 2;

FIG. 7 is a schematic perspective view of the liquid recovery apparatus of FIG. 2;

FIG. 8 is a schematic partial cross-sectional structural view of the blade cartridge of FIG. 2.

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 an aircraft engine blade; FIG. 1b is a schematic perspective view of the blade of FIG. 1a from another perspective; FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a; FIG. 1d is a schematic cross-sectional structural view of the blade body of the blade of FIG. 1 a; FIG. 1e is a schematic diagram of the cross-sectional structure A-A of FIG. 1 d; FIG. 2 is a schematic structural diagram of a liquid supply device for measuring the angle of a small pore of a blade according to an embodiment of the present invention in a use state; FIG. 3 is a schematic diagram of a screen display effect of the projection imaging of FIG. 2; FIG. 4 is a schematic view of the apparatus of FIG. 2 in another use state; FIG. 5 is a diagram illustrating a screen display effect of the projection imaging of FIG. 4; FIG. 6 is a schematic perspective view of the second connecting arm of FIG. 2; FIG. 7 is a schematic perspective view of the liquid recovery apparatus of FIG. 2; FIG. 8 is a schematic partial cross-sectional structural view of the blade cartridge of FIG. 2. Wherein the dotted lines in figures 3 and 5 represent the ejected liquid column, see figures 1a to 8,

as described in the background art, aiming at the problem that the angle of the air film hole 21 cannot be directly measured due to the fact that the existing aperture is generally between phi 0.25mm and phi 0.5mm, and the depth is not less than 6mm, the inventor conducts deep analysis on the principle of the air film hole, provides a set of complete technical scheme for directly measuring the angle of the air film hole of the blade by using a rigid measuring needle, can obtain real air film hole angle data, and cannot cause physical damage to the blade in the measuring process. Therefore, each blade can be detected, and the qualification rate of finished products can be greatly improved. Although the scheme of using the rigid measurement needle for measurement has high data accuracy, more than one group of the air film holes 21 may be formed in a single blade, and for each blade of each batch, the measurement needle needs to be assembled on at least one air film hole 21 in each group of the air film holes 21, and the assembly of the measurement needle is complicated, so the labor intensity of workers is high, and the assembly time of the measurement needle is long, so the overall measurement efficiency still needs to be improved.

The inventor provides a method for measuring parameters of the air film holes 21 by supplying liquid (such as water) with constant pressure to the aero-engine blade 100 so as to utilize the characteristic that liquid columns sprayed out of the air film holes 21 keep axial linearity in an invention patent application 'a method for measuring the angle of small micropores of the blade by using liquid', wherein the method is submitted on the same day as the application and the invention patent application is tested, verified and optimized. However, this application is primarily based on the principle of describing the process of implementation, and although the requirements for the parts for holding the aircraft engine blade 100 and the parts for recovering the liquid flow are clear, the existing optical measuring devices include digital measuring projectors or non-contact three-coordinate measuring machines. The digital measurement projector is further specifically divided into a digital vertical projector (the optical axis of the objective lens is vertical to the working table) according to the structural form; and digital horizontal projectors (objective optic axis parallel to the work surface). Therefore, no further detailed definition of the means applied to a particular optical measuring device of a certain type is given in this application. In addition, in practice, when the existing cooling water pipeline of a factory building is used for supplying water, the pipeline of the factory building needs to be modified, and in measurement, the fact that the multi-purpose reclaimed water of the factory is used as cooling industrial water, and the reclaimed water is colorless is found, so that when the liquid column is measured, the edge of the liquid column can be blurred, and an experienced worker needs to take special care when the focal length of the optical projection device is adjusted, and a good measurement effect can be obtained. Therefore, the method still has certain requirements on the operation proficiency of workers.

In the present application, for the commonly used digital horizontal projector, the inventor provides a more detailed technical scheme of the device which can realize the liquid method by using self-circulation coloring liquid,

specifically, the invention provides a liquid supply device for measuring the angle of a small micropore of a blade, which is used for measuring the parameters of a gas film hole 21 of an aircraft engine blade 100 on a digital horizontal projector through self-circulation coloring liquid flow, wherein the aircraft engine blade 100 adopts a hollow inner-cooling structure, the bottom of the blade is provided with a first air inlet 11 which is formed by casting and communicated with an inner cavity and is close to one side of a front edge and a second air inlet 12 which is formed by casting and is close to one side of a rear edge, the blade tip is provided with a blade tip groove 30 with the depth of 2mm, the blade tip groove 30 is provided with an air outlet, the rear edge is provided with a processing surface 20 with a Z axis in parallel, and the processing surface 20 is provided with a plurality of gas film holes 21 communicated with the inner cavity. Which comprises the steps of preparing a mixture of a plurality of raw materials,

be used for installing base 4 on digital horizontal projector's the workstation, fixed mounting has the primary shaft revolving stage 5 that is used for adjusting horizontal rotation angle on the base 4, primary shaft revolving stage 5 is used for adjusting vertical rotation angle's second shaft revolving stage 6 through first linking arm 51 fixedly connected with, second linking arm 7 is installed to second shaft revolving stage 6, second linking arm 7 can be dismantled and is connected with blade holder 8, blade holder 8 can be dismantled and is connected with aeroengine blade 100, base 4 liftable is connected with liquid recovery unit 9, liquid recovery unit 9 is connected with solution barrel 300 through backflow pipeline, solution barrel 300 through the liquid supply pipeline with blade holder 8 can be dismantled and be connected, be provided with force pump 301 on the liquid supply pipeline, the pre-installation has coloring solution in solution barrel 300.

The coloring solution in the solution tank 300 may be a copper sulfate solution or a mixture of commercially available ink and water, as long as it has a distinct color, thereby facilitating optical projection. The inventor team finds through practice that the requirement of measuring at least 100 aero-engine blades 100 can be met by keeping about 50 liters of coloring solution in the solution barrel 300, and in addition, in order to avoid the coloring solution from precipitating, a stirring blade (not shown in the figure) can be arranged in the solution barrel 300, so that the stirring can be carried out for at least 20 minutes before the solution barrel is used, and large particles are not in the solution, and in addition, a filter screen (not shown in the figure) can be arranged at the joint of the liquid supply pipeline in the solution barrel 300, so that the large particles are further prevented from entering the pipeline.

The device provided by the invention needs to supply coloring solution to the aero-engine blade 100 in the using process of the digital horizontal projector, and needs to be collected, recovered and recycled, so that the influence on optical equipment caused by splashing and scattering of liquid can be avoided, the transformation of the existing plant pipeline can be avoided, and the measuring effect can be effectively improved. Therefore, the invention is specially designed for the connection structure of the two-axis turntable.

Referring to fig. 2, 4 and 6, the first connecting arm 51 may be an L-shaped connecting arm sleeved on the rotating shaft of the first shaft turntable 5, so that the axis of the second shaft turntable 6 and the axis of the first shaft turntable 5 have a certain distance in the horizontal direction.

The main structure of the second connecting arm 7 can be a Z-shaped structure, so that after the blade holder 8 is installed, the Z-axis of the aircraft engine blade 100 can have a certain distance with the axis of the second axis turntable 6, and therefore, the light projection area can not be affected by the structure of the two axis turntable during measurement. Specifically, the second connecting arm 7 may include a first connecting portion 71, a first extending portion 72 and a second extending portion 73, which are connected in sequence, the first connecting portion 71 is used for connecting a rotating shaft of the second shaft rotating platform 6, the first extending portion 72 is not coaxial with the first connecting portion 71, for example, an axis of the first extending portion 72 may be perpendicular to an axis of the first connecting portion 71, an axis of the second extending portion 73 may be arranged parallel to an axis of the first connecting portion 71, an end portion of the second extending portion 73 is provided with a mounting portion 74, and the mounting portion 74 may be provided with a mounting hole 75 with a clamping spring sheet, so that the blade holder 8 which completes the assembly of the aero-engine blade 100 at the outside can be conveniently and quickly clamped and assembled in the mounting hole 75.

In the production process of the aircraft engine blade 100, the securing of the machining coordinate system and the measuring coordinate system is accomplished by clamping the dovetail section of the aircraft engine blade 100. As described in the prior application "2019111027142 a method for measuring the angle of a small micropore of a blade" of the inventor team, there are various ways for clamping the aero-engine blade 100 equipped with a rigidity measuring probe, and it can be seen that several prior application patent documents of the inventor team, such as 201610873006.9, 201811495958.7, etc., describe the existing blade clamping ways and technical solutions.

In order to measure by using liquid, the inventor group is reformed on the basis of the existing clamping structure, and the key point of the invention is how to reform the existing clamping structure and ensure the sealing performance and the size minimization on the premise of ensuring the repeated precision of a clamping coordinate system. As shown in fig. 8, the core of the modification is to provide a sealable buffer chamber 82 at the dovetail mounting structure to which an inlet connector 81 is connected, so that a constant pressure liquid can be supplied to the aircraft engine blade 100 during the measurement. Specifically, the blade holder 8 provided by the present invention may include a mounting post 83 connected to the mounting hole 75, and the main structure of the blade holder 8 may be modified based on the existing elastic tenon tooth holder, as shown in fig. 1a, the edge of the machined surface 20 near one side of the platform of the aero-engine blade 100 may effectively prevent the influence of the holding structure on the area where light is projected as long as the size of the structure for holding the tenon portion of the aero-engine blade 100 can be controlled to be small enough, and the existing high strength alloy material may be selected to meet the requirement of the connection strength and rigidity under the condition of the minimum wall thickness of 1-2 mm. Therefore, the tenon tooth clamping structure portion of the blade holder 8 can be made of a high-strength alloy material, and is prepared according to the peripheral dimension of the flange plate, and the length of the flange plate in the length direction, that is, the length of the aero-engine blade 100 in the X-axis direction of the measurement coordinate system, can be slightly longer, so that after the aero-engine blade 100 is clamped into the main body structure of the blade holder 8 in the X-axis direction, the exposed portion in the X-axis direction can be closed by using yellow wax or a rubber block, and thus the sealing performance of the buffer cavity 43 can be ensured. The parts of the existing tenon tooth clamping structure, such as the fastening screw, are not shown in fig. 8, and it should be understood by those skilled in the art that these fastening structures for ensuring stable and accurate clamping of the aero-engine blade 100 can be implemented by various existing technologies, and therefore will not be described in detail herein,

since the blade holder 8 is based on the tenon of the aircraft engine blade 100 as a clamping reference, the blade holder 8 may be marked with a certain mark in advance on the X-Y axis, the mounting hole 75 may be provided with a positioning groove (not shown), and correspondingly, the mounting post 83 may be provided with a positioning tooth (not shown), so that when the blade holder 8 is located behind the second connecting arm 7, the X-Y axis of the aircraft engine blade 100 may be visually perceived to a certain extent. Thereby facilitating subsequent adjustment at the digital horizontal projector.

The first shaft turntable 5 and the second shaft turntable 6 can be provided with accurate scales, so that repeated precise positioning can be facilitated.

Referring to fig. 2-4, since the apparatus of the present invention is used in the liquid method, in order to minimize the influence of gravity on the liquid column during the measurement, the apparatus is optimally used such that the processing surface 20 is located at a horizontal plane, thereby ensuring that the liquid column is ejected downward.

In order to ensure that the liquid column sprayed out from the gas film hole 21 can not be scattered by sputtering and can be recycled, the invention is particularly provided with a liquid recovery device 9, and as shown in figures 2, 4 and 7, the liquid recovery device 9 is provided with a U-shaped cavity body, the sectional area of the U-shaped cavity may be gradually increased, the width of the opening 91 of the U-shaped cavity may be slightly larger than the width of the processing surface 20, before liquid supply, the opening 91 of the U-shaped cavity can be close to the processing surface 20, after the liquid supply pressure is stable, the opening 91 of the U-shaped cavity is far away from the processing surface 20 by at least 6mm, thus, all the liquid columns ejected from the air film holes 21 can enter the U-shaped cavity body and are converged, so that the solution can be collected to the solution tank 300 through a return line by a return joint (not shown) provided at the bottom of the liquid recovery device 9. The opening of the U-shaped cavity is far away from the processing surface by 20 mm at least 6mm, so that the measurement of the optical measurement equipment on the liquid column within the range of 5mm close to the air film hole 21 is not influenced. The liquid recovery device 9 can be detachably connected to the base 4 through a lifting device 92, so that the position of the liquid recovery device 9 can be conveniently adjusted according to the position of the aircraft engine blade 100.

When the aero-engine blades 100 are measured in batches, only one of the film holes 21 in each group of the film holes 21 may be measured according to the records of "2019111027142 a method for measuring the angle of the small blade micropores", "2019111032761 a measuring needle for measuring the angle of the small blade micropores" and "2019111032776 a method for using the measuring needle for measuring the angle of the small blade micropores" filed on 11/13.2019 by the inventor team, and the other film holes 21 may be blocked during measurement, or all the film holes 21 may be measured after analyzing the data range of the liquid flow measurement according to the records of the inventor team in the invention patent application "a method for measuring the angle of the small blade micropores using liquid" filed on the same day as the present application. The specific method of use may be selected according to the capabilities of the digital flat projector being used.

The method for using the liquid supply device for measuring the angle of the small micropore of the blade provided by the invention can comprise the following steps,

step A, plugging the air outlet of the blade tip groove 30 of the aero-engine blade 100, then installing a rigidity measuring needle on one air film hole 21, then clamping the aero-engine blade 100 on the blade holder 8, and then plugging the clamping gap of the blade holder 8.

The air outlet of the tip slot 30 of the aircraft engine blade 100 is blocked by using yellow wax, as described in a method for measuring the flow rate of air flowing through a hole of a turbine blade machine provided by the inventor in chinese patent ZL2017112497983,

the rigidity measuring needle and the assembling method thereof can be referred to the records of three patent applications of '2019111027142 a method for measuring the angle of the small micropore of the blade', '2019111032761 a measuring needle for measuring the angle of the small micropore of the blade' and '2019111032776 a method for using the measuring needle for measuring the angle of the small micropore of the blade', which are filed by an inventor team on 11, 13.2019.

For the clamping gap after the aero-engine blade 100 is clamped on the blade clamping seat 8, if a mode of clamping along the X-axis direction is adopted, a corresponding rubber structure can be arranged according to the clamping structure, and the blade can be blocked by clamping force or by using yellow wax. Even if a gap is reserved between the blade flange plate and the blade clamping seat 8, the blade flange plate can be blocked by using yellow wax.

As described above, since the blade holder 8 is attached and fixed based on the dovetail portion of the aircraft engine blade 100, the X-Y axis position of the aircraft engine blade 100 can be previously calibrated on the blade holder 8,

step B, assembling the blade holder 8, to which the aero-engine blade 100 is clamped, on the second connecting arm 7, and allowing the machined surface 20 to face downward, then adjusting the second axis turntable 6, so that the machined surface 20 is kept horizontal, that is, so that the Z axis of the aero-engine blade 100 is kept horizontal, then adjusting the first axis turntable 5, respectively finding and calibrating the position where the Z axis of the aero-engine blade 100 is perpendicular to and parallel to the projection light of the digital horizontal projector, that is, finding the position shown in fig. 2 and 4, and simultaneously measuring and obtaining measurement data of the two positions of the rigidity measuring needle assembled in step a, that is, an included angle α between the air film hole 21 and the X axis of the blade measuring coordinate system and an included angle β between the air film hole and the Z axis. If the measured data do not meet the design requirements, the aero-engine blade 100 is a non-qualified product, at this time, the aero-engine blade 100 needs to be replaced, the step A and the step B are repeated, if the measured data meet the design requirements, the next step is carried out,

step C, keeping the Z axis of the aero-engine blade 100 at one of positions vertical or parallel to the projection light of the digital horizontal projector, pulling out the rigid measurement needle, connecting the solution barrel 300 with the blade holder 8 and the liquid recovery device 9 respectively, adjusting the position of the liquid recovery device 9 to enable the opening 91 of the U-shaped cavity to be close to the processing surface 20, starting the pressure pump 301 until the liquid supply pressure is stabilized at 0.065MPa or 0.08MPa, adjusting the position of the liquid recovery device 9 to enable the opening 91 of the U-shaped cavity to be far away from the processing surface 20 by at least 6mm, so that the measurement is not influenced, then measuring the measurement data of the air film hole 21 assembled from the rigid measurement needle at the position, recording the measurement data, closing the pressure pump 301, and stopping when the air film hole 21 does not leak liquid, lowering the liquid recovery device 9, then adjusting the first axis turntable 5 to enable the Z axis of the aircraft engine blade 100 to be located at the other position perpendicular to or parallel to the projection light of the digital horizontal projector, resetting the position of the liquid recovery device 9 to enable the opening 91 of the U-shaped cavity to be close to the processing surface 20, starting the pressure pump 301 until the liquid supply pressure is stabilized at 0.065Mpa or 0.08Mpa, then adjusting the position of the liquid recovery device 9 to enable the opening 91 of the U-shaped cavity to be away from the processing surface 20 by at least 6mm, then measuring the measurement data of the gas film hole 21 assembled from the rigid measurement needle at the position, recording the measurement data, closing the pressure pump 301, and taking down the blade holder 8 after the liquid does not leak from the gas film hole 21, thereby completing the acquisition of sample data.

And D, after the sample data acquisition is completed, calculating to obtain the range of the image data of the liquid column corresponding to the design data in the optical measurement, so that for other aviation engine blades 100, the measurement data of the coloring solution can be measured according to the operation of the step C, and then compared with the data range obtained by calculating the sample data, the design requirement is met in the range, otherwise, the product is an unqualified product.

The use method of the liquid supply device for measuring the angle of the small micropore of the blade provided by the invention can be used for quickly and visually and directly measuring the angle of the air film hole of the blade on a digital horizontal projector to obtain real air film hole angle data, and the measurement efficiency is greatly improved.

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

1. A use method of a liquid supply device for measuring the angle of a small micropore of a blade is characterized in that the liquid supply device is used for directly measuring the actual angle of a gas film hole of an aircraft engine blade, the liquid supply device comprises a base arranged on a workbench of a digital horizontal projector, a first shaft rotary table for adjusting the horizontal rotation angle is fixedly arranged on the base, the first shaft rotary table is fixedly connected with a second shaft rotary table for adjusting the vertical rotation angle through a first connecting arm, a second connecting arm is arranged on the second shaft rotary table, a blade clamping seat is detachably connected with the second connecting arm, the blade clamping seat is detachably connected with the aircraft engine blade, the base is connected with a liquid recovery device in a lifting manner, the liquid recovery device is connected with a solution barrel through a backflow pipeline, the solution barrel is detachably connected with the blade clamping seat through a liquid supply pipeline, the liquid supply pipeline is provided with a pressure pump, the solution barrel is pre-filled with coloring solution, the liquid recovery device is provided with a U-shaped cavity, the width of the opening of the U-shaped cavity is slightly larger than the width of the processing surface, the method comprises the following steps,

step A, plugging an air outlet of a blade tip groove of the blade of the aero-engine, then installing a rigidity measuring needle on one air film hole, then clamping the blade of the aero-engine on the blade clamping seat, and then plugging a clamping gap of the blade clamping seat,

step B, assembling the blade holder with the aero-engine blade clamped on the second connecting arm, enabling the machined surface to face downwards, adjusting the second axis turntable to enable the machined surface to be kept horizontal, namely ensuring that the Z axis of the aero-engine blade is kept horizontal, then adjusting the first axis turntable to respectively find and calibrate the positions of the Z axis of the aero-engine blade, which are vertical and parallel to the projection light of the digital horizontal projector, and simultaneously measuring and obtaining the measurement data of the rigidity measurement needle assembled in the step A at the two positions, namely the included angle alpha of the air film hole relative to the X axis of a blade measurement coordinate system and the included angle beta of the air film hole relative to the Z axis, if the measurement data do not meet the design requirements, the aero-engine blade is an unqualified product, and at the moment, the aero-engine blade needs to be replaced and the steps A and B need to be repeated, if the measured data meets the design requirements, the next step is carried out,

step C, keeping the Z axis of the blade of the aircraft engine to be in a position vertical or parallel to the projection light of the digital horizontal projector, pulling out the rigid measuring needle, respectively connecting the solution barrel with the blade holder and the liquid recovery device, adjusting the position of the liquid recovery device to enable the opening of the U-shaped cavity to be close to the processing surface, starting the pressure pump until the liquid supply pressure is stable, then adjusting the position of the liquid recovery device to enable the opening of the U-shaped cavity to be far away from the processing surface by at least 6mm, then measuring the measurement data of the air film hole assembled from the rigid measuring needle at the position, recording the measurement data, closing the pressure pump, lowering the liquid recovery device after the air film hole does not leak liquid any more, and then adjusting the first axis, the Z axis of the blade of the aircraft engine is positioned at the other position which is vertical or parallel to the projection light of the digital horizontal projector, the position of the liquid recovery device is reset, the opening of the U-shaped cavity is close to the processing surface, the pressure pump is started until the liquid supply pressure is stable, then the position of the liquid recovery device is adjusted, the opening of the U-shaped cavity is far away from the processing surface by at least 6mm, then the measurement data of the air film hole assembled from the rigid measurement needle at the position is measured, the measurement data is recorded, the pressure pump is closed, after the air film hole does not leak liquid any more, the blade holder is taken down, and the acquisition of sample data is completed,

2. The method according to claim 1, wherein in step A, the air outlet of the blade tip groove of the aircraft engine blade is blocked by using yellow wax.

3. The method of claim 1, wherein in step C, the liquid supply pressure is regulated to be stable at 0.065Mpa or 0.08 Mpa.

4. The method of claim 1, wherein the vat holds 50 liters of coloring solution.

5. The method of claim 1, wherein the coloring solution is a copper sulfate solution or a mixture of ink and water.

6. The method of claim 1, wherein a stirring blade is disposed within the solution tank.

7. The method of claim 6, wherein a strainer is further disposed at an interface of the liquid supply line within the solution barrel.