阅读说明：本技术 一种用于叶片小微孔角度测量的气体循环装置的使用方法 (Use method of gas circulation device for measuring angle of small micropores of blade ) 是由 张小青 丰莉 杨秀伟 望回归 刘新见 于 2020-11-04 设计创作，主要内容包括：一种用于叶片小微孔角度测量的气体循环的使用方法,其包括如下步骤,步骤A,在一个气膜孔上装上刚性测量针,之后将叶片装夹在叶片夹座上。步骤B,分别找到并标定出叶片的Z轴与投射光线垂直和平行的位置,同时测量获得步骤A中装配的所述刚性测量针在这两个位置的测量数据,步骤C,拔出所述刚性测量针,完成样本数据的获取。步骤D,通过计算,即可获得设计数据对应的气柱在光学测量中的影像数据的范围,对于其他的叶片,测量着色气体的测量数据,然后与通过样本数据计算获得的数据范围比较。本发明所提供的一种用于叶片小微孔角度测量的气体循环的使用方法,大大提升了测量效率。(A method for using gas circulation 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 gas column corresponding to the design data in the optical measurement through calculation, measuring the measurement data of the coloring gas for other blades, and comparing the measurement data with the data range obtained through sample data calculation. The gas circulation using method for measuring the angle of the small micropores of the blade greatly improves the measuring efficiency.)

1. A use method of a gas circulation device for measuring the angle of a small micropore of a blade is characterized in that the gas circulation device is used for coloring gas by using recyclable dust on a digital horizontal projector so as to measure the gas film hole parameters of an aircraft engine blade, the device comprises a base which is arranged on a workbench of the digital horizontal projector, a first shaft rotary table for adjusting the horizontal rotation angle is fixedly arranged on the base, a second shaft rotary table for adjusting the vertical rotation angle is fixedly connected with the first shaft rotary table 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 gas recovery device in a lifting way, a powder box and a powder recovery box are arranged beside the workbench, the powder case be provided with be used for inserting compressed gas the air inlet and be used for with the blade holder passes through the air supply mouth of pipe connection, the powder recovery case be provided with be used for with the return air mouth that gas recovery device connects and be used for the air exit be connected with negative pressure device. 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, connecting the powder box with the blade holder, adjusting the position of the gas recovery device to enable the opening of the U-shaped cavity to be far away from the processing surface by at least 6mm, connecting the gas recovery device with the powder recovery box, then starting the negative pressure device to enable the gas recovery device to generate negative pressure, then connecting the powder box with a compressed air bottle, inputting compressed air with the pressure of 0.04MPa into the powder box, and when the gas film hole sprays out a gas column carrying powder, measuring data of the gas column sprayed out from the gas film hole assembled with the rigid measuring needle at the position can be measured, if the deviation is too large, the deviation is minimized while ensuring the recovery efficiency of the gas column by adjusting the negative pressure device, at this time, recording the measurement data and the parameters of the negative pressure device, then closing the compressed air bottle, lowering the gas recovery device after the gas with powder does not leak from the gas film hole, then adjusting the first axis turntable to enable the Z axis of the blade of the aircraft engine to be positioned at the other position of the positions vertical to or parallel to the projection light of the digital horizontal projector, resetting the position of the gas recovery device to enable the opening of the U-shaped cavity to be away from the processing surface by at least 6mm, then restarting the compressed air bottle to measure the measurement data of the gas column ejected from the gas film hole 21 assembled by the rigid measuring needle at the position, recording the measurement data, closing the compressed air bottle, after the gas does not leak from the gas film hole, closing the negative pressure device, and taking off the blade holder, and finishing the acquisition of the sample data.

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

2. The method according to claim 1, wherein the powder box has a barrel-shaped structure, the air inlet is arranged on one side of the top, the air outlet is arranged at the bottom of the side wall adjacent to the air inlet, a first partition is arranged in the area in the barrel between the air inlet and the air outlet, a closed powder storage area formed by a second partition is further arranged in the area in the barrel on one side of the air inlet, and a blanking port with the diameter of 2-6mm is arranged at the bottom of the powder storage area.

3. The method of claim 2, wherein the first baffle is inclined toward the second baffle, and a bottom of the first baffle is positioned above the drop opening.

4. The method of claim 2, wherein the powder previously placed in the powder storage area is chalk dust or toner.

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 coloring gas.

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 technical problem to be solved by the present invention is to provide a gas circulation device for the angle measurement of small micropores of a blade, so as to reduce or avoid the aforementioned problems.

In order to solve the technical problem, the invention provides a use method of a gas circulation device for measuring the angle of a small micropore of a blade, which is used for coloring gas by using recyclable dust on a digital horizontal projector so as to measure the gas film hole parameter of an aircraft engine blade, the device comprises a base, a first shaft rotary table, a second connecting arm and a blade clamping seat, wherein the first shaft rotary table is used for adjusting the horizontal rotation angle and fixedly arranged on the base, the second shaft rotary table is used for adjusting the vertical rotation angle and fixedly connected with the second shaft rotary table through the first connecting arm, the second connecting arm is detachably connected with the blade clamping seat, the blade clamping seat is detachably connected with the aircraft engine blade, the base is connected with a gas recovery device in a lifting way, a powder box and a powder recovery box are arranged beside the workbench, the powder case be provided with be used for inserting compressed gas the air inlet and be used for with the blade holder passes through the air supply mouth of pipe connection, the powder recovery case be provided with be used for with the return air mouth that gas recovery device connects and be used for the air exit be connected with negative pressure device. 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, connecting the powder box with the blade holder, adjusting the position of the gas recovery device to enable the opening of the U-shaped cavity to be far away from the processing surface by at least 6mm, connecting the gas recovery device with the powder recovery box, then starting the negative pressure device to enable the gas recovery device to generate negative pressure, then connecting the powder box with a compressed air bottle, inputting compressed air with the pressure of 0.04MPa into the powder box, and when the gas film hole sprays out a gas column carrying powder, measuring data of the gas column sprayed out from the gas film hole assembled with the rigid measuring needle at the position can be measured, if the deviation is too large, the deviation is minimized while ensuring the recovery efficiency of the gas column by adjusting the negative pressure device, at this time, recording the measurement data and the parameters of the negative pressure device, then closing the compressed air bottle, lowering the gas recovery device after the gas with powder does not leak from the gas film hole, then adjusting the first axis turntable to enable the Z axis of the blade of the aircraft engine to be positioned at the other position of the positions vertical to or parallel to the projection light of the digital horizontal projector, resetting the position of the gas recovery device to enable the opening of the U-shaped cavity to be away from the processing surface by at least 6mm, then restarting the compressed air bottle to measure the measurement data of the gas column ejected from the gas film hole 21 assembled by the rigid measuring needle at the position, recording the measurement data, closing the compressed air bottle, after the gas does not leak from the gas film hole, closing the negative pressure device, and taking off the blade holder, and finishing the acquisition of the sample data.

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

Preferably, the powder box is of a barrel-shaped structure, the air inlet is arranged on one side of the top, the air supply port is arranged at the bottom of the side wall adjacent to the air inlet, a first partition plate is arranged in an area in the barrel between the air inlet and the air supply port, a closed powder storage area formed by a second partition plate is further arranged in the area in the barrel on one side of the air inlet, and a blanking port with the diameter of 2-6mm is arranged at the bottom of the powder storage area.

Preferably, the first partition plate inclines towards the second partition plate, and the bottom of the first partition plate is located above the blanking port.

Preferably, the powder previously placed in the powder storage area is chalk dust or toner.

According to the application method of the gas circulation device for measuring the angle of the small micropore of the blade, which is provided by the invention, the gas is colored by using the recyclable dust, the angle of the gas film hole of the blade is quickly and directly measured on the digital horizontal projector, the real data of the angle of the gas film hole 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 gas circulation device for measuring the angle of a small micropore of a blade in a use state according to an embodiment of the invention;

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 gas recovery device of FIG. 2;

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

FIG. 9 is a schematic diagram of a half-section structure of the gas convergence device of FIG. 7;

fig. 10 is a schematic structural view of the powder box 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 gas circulation device for measuring the angle of a small micropore of a blade in a use state according to an embodiment of the invention; 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 gas recovery device of FIG. 2; FIG. 8 is a schematic partial cross-sectional structural view of the vane cartridge of FIG. 2, and FIG. 9 is a schematic half-sectional structural view of the gas convergence device of FIG. 7; fig. 10 is a schematic structural view of the powder box of fig. 2. Wherein the dotted lines in figures 3 and 5 represent the ejected air columns, see figures 1a to 10,

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 gas film holes 21 by supplying coloring gas with certain pressure to the aero-engine blade 100 so as to utilize the characteristic that gas columns sprayed out of the gas film holes 21 keep axial linearity in the invention patent application 'a method for measuring the angle of small micropores of the blade by using gas', which is filed on the same day as the application through testing, verification and optimization. The application is principally formulated for the process of implementation, however, since the existing optical measuring devices comprise digital measuring projectors or non-contact three-coordinate measuring machines, although the requirements for the parts for holding the aircraft engine blade 100 and the method of generating the coloring gas, which is experimentally obtained by the team of the inventors, are made clear. 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, the means applied to a certain type of specific optical measuring device and the means for generating a certain type of coloring gas are not further defined in detail in this application.

In the application, for a common digital horizontal projector, under the condition of adopting dust for gas coloring, the inventor provides a more detailed technical scheme of a device for realizing the gaseous method by coloring gas with recyclable dust,

specifically, the invention provides a gas circulation device for measuring the angle of a small micropore of a blade, which is used for coloring gas by using recyclable and recyclable dust on a digital horizontal projector so as to measure the parameters of a gas film hole 21 of an aircraft engine blade 100, wherein the aircraft engine blade 100 adopts a hollow internal cooling structure, the bottom of the blade is provided with a first gas 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 gas 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 a gas 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. Which comprises the steps of preparing a mixture of a plurality of raw materials,

a base 4 for installing on the workbench of the digital horizontal projector, a first axis turntable 5 for adjusting the horizontal rotation angle is fixedly installed on the base 4, the first axis turntable 5 is fixedly connected with a second axis turntable 6 used for adjusting the vertical rotation angle through a first connecting arm 51, the second shaft rotary table 6 is provided with a second connecting arm 7, the second connecting arm 7 is detachably connected with a blade clamping seat 8, the blade holder 8 is detachably connected with the aero-engine blade 100, the base 4 is connected with a gas recovery device 9 in a lifting way, a powder box 300 and a powder recovery box 400 are arranged beside the workbench, the powder box 300 is provided with an air inlet for connecting compressed air and an air outlet for connecting the blade holder 8 through a pipeline, the powder recovery box 400 is provided with a return air port for connecting with the gas recovery device 9 and an air outlet for connecting with the negative pressure device 500.

Referring to fig. 10, the powder box 300 has a barrel-shaped structure, the air inlet is disposed at one side of the top, the air outlet is disposed at the bottom of the side wall adjacent to the air inlet, a first partition is disposed in an area in the barrel between the air inlet and the air outlet, a closed powder storage area formed by a second partition is further disposed in the area in the barrel at one side of the air inlet, and a discharging opening with a diameter of 2-6mm is disposed at the bottom of the powder storage area. The first partition plate inclines towards the second partition plate, and the bottom of the first partition plate is located above the blanking port. The powder that the powder storage area was placed in advance can be chalk dust or powdered ink, and it is out of work, under the action of gravity, the powder can be followed the blanking mouth slowly drops, but drops and piles up to certain degree, just can not drop again, and in operation, compressed air (for example 0.04Mpa) that has certain pressure gets into from the air inlet powder case 300, behind via the blanking mouth, can carry the powder of piling up and mix the back and get into the region that the air feed inlet is located, and one part of it is followed the air feed inlet via the pipeline is carried to aeroengine blade 100 is used for optical measurement, and another part continues to form the torrent in the bucket thereby promotes mixing efficiency.

The powder recovery box 400 is mainly used for adsorbing the powder in the recovered coloring gas, and therefore, the structure thereof can be selected from various existing dust collector structures, for example, the structure described in the existing patent document such as "201220201007.6 a pulse bag dust collector ash storage cylinder" or "201220217474.8 a filter bag dust collector" can be selected, and will not be described again here. When the powder recovered in the powder recovery box 400 reaches a certain amount (for example, one third or one half of the preset amount of powder in the powder box 300), the powder recovered in the powder recovery box 400 can be transferred to the powder box 300 at a use interval, so that the recycling of the powder is realized.

The negative pressure device 500 may be an exhaust fan or an exhaust fan, as long as a negative pressure with a certain pressure can be formed in the gas recovery device 9.

The device provided by the invention needs to supply coloring gas 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 of gas sputtering and scattering on the measuring environment and workers can be avoided, and therefore, the device is specially designed for the connecting 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 gas, an inventor team 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 air inlet connector 81 is connected, so that a constant pressure of air 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 a gaseous process, in order to minimize the effect of gravity on the gas column during the measurement, the apparatus is preferably used in such a way that the processing surface 20 is located at a horizontal plane, thereby ensuring that the gas column is ejected downward.

In order to ensure that the gas column ejected from the gas film hole 21 is not scattered by sputtering and the powder can be recycled, the gas recovery device 9 is particularly arranged, as shown in fig. 2, 4, 7 and 9, the gas recovery device 9 is provided with a U-shaped cavity body, the cross section area of the U-shaped cavity body can be gradually increased, the width of an opening 91 of the U-shaped cavity body can be slightly larger than the width of the processing surface 20, and in a half cross section, the size of an included angle β 1 between the opening 91 and the bottom side can be not smaller than half of the size of an included angle β between the gas film hole 21 and the Z axis, so that the gas column can be reflected towards the tail part of the U-shaped cavity body to the greatest extent possible after being injected into the U-shaped cavity body. The tail of the U-shaped cavity is provided with an exhaust port 93, and the exhaust port 93 is connected with the powder recovery box 400 through a pipeline.

When the aero-engine blades 100 are measured in batches, according to the descriptions of the schemes such as "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 by the inventor on 11/13 of 2019, only one of the gas film holes 21 in each group of the gas film holes 21 is measured, and the other gas film holes 21 are blocked during measurement, or according to the descriptions of the inventor in the invention patent application "a method for measuring the angle of the small blade micropores using gas" filed on the same day as the present application, all the gas film holes 21 are measured after analyzing the data range of gas flow measurement. The specific method of use may be selected according to the capabilities of the digital flat projector being used.

The method for using the gas circulation device for measuring the angle of the small micropores 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 the positions vertical or parallel to the projection light of the digital horizontal projector, pulling out the rigid measurement needle, connecting the powder box 300 with the blade holder 8, adjusting the position of the gas 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 can be unaffected, connecting the gas recovery device 9 with the powder recovery box 400, then starting the negative pressure device 500 to enable the gas recovery device 9 to generate negative pressure, then connecting the powder box 300 with a compressed air bottle, inputting compressed air with the pressure of 0.04MPa into the powder box 300, and when the gas film hole 21 ejects a gas column carrying powder, measuring the measurement data of the gas column ejected from the gas film hole 21 assembled by the rigid measurement needle at the position, if the deviation is too large, which may be caused by the excessive negative pressure, the deviation can be minimized while ensuring the efficiency of gas column recovery by adjusting the negative pressure device 500, at this time, the measurement data and the parameters of the negative pressure device 500 are recorded, then the compressed air bottle is closed, the gas recovery device 9 is lowered after the gas with powder no longer leaks from the gas film hole 21, then the first axis rotating table 5 is adjusted so that the Z axis of the aircraft engine blade 100 is located at the other position perpendicular or parallel to the projection light of the digital horizontal projector, the position of the gas recovery device 9 is reset so that the opening 91 of the U-shaped cavity is at least 6mm away from the processing surface 20, and then the compressed air bottle can be restarted to measure the measurement data of the gas column ejected from the gas film hole 21 of the rigid measurement needle assembly at this position, recording the measurement data, closing the compressed air bottle, closing the negative pressure device 500 after the gas film hole 21 does not leak gas any more, and taking down the blade holder 8 to finish the acquisition of sample data.

And D, after sample data acquisition is completed, calculating to obtain the range of the image data of the gas column corresponding to the design data in the optical measurement, so that for other aviation engine blades 100, the operation can be repeated according to the parameters recorded in the step C to measure the measurement data of the coloring gas, and then the measurement data is compared with the data range obtained through sample data calculation, the design requirements are met in the range, otherwise, the product is an unqualified product.

According to the gas circulating device for measuring the angle of the small micropore of the blade, which is provided by the invention, gas is colored by using recyclable dust, the angle of the gas film hole of the blade is quickly and directly measured on a digital horizontal projector, real gas film hole angle data is obtained, and the measuring 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.