CN112797920B - Blade micro-pore angle measurement method - Google Patents
Blade micro-pore angle measurement method Download PDFInfo
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- CN112797920B CN112797920B CN201911102714.2A CN201911102714A CN112797920B CN 112797920 B CN112797920 B CN 112797920B CN 201911102714 A CN201911102714 A CN 201911102714A CN 112797920 B CN112797920 B CN 112797920B
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- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 7
- 239000000741 silica gel Substances 0.000 claims description 7
- 229910002027 silica gel Inorganic materials 0.000 claims description 7
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- 238000010892 electric spark Methods 0.000 description 4
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- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/002—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates
- G01B11/005—Measuring arrangements characterised by the use of optical techniques for measuring two or more coordinates coordinate measuring machines
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
A blade micropore angle measuring method comprises the following steps of A, preparing a measuring needle according to the diameter of a gas film hole, B, enabling the end head of an insertion part of the measuring needle prepared in the step A to be in contact with the gas film hole end opening, forming negative pressure in the inner cavity of an aeroengine blade, and accordingly sucking the insertion part into the gas film hole until an extension part is in contact with the gas film hole end opening, and completing installation of the measuring needle. And C, completing angle measurement of the air film hole by utilizing an optical measurement mode, taking out the measuring needle along the axial direction of the measuring needle after obtaining measurement data, and completing angle measurement of the air film hole. The method for measuring the angle of the small micropores of the blade can realize direct measurement of the angle of the air film hole of the blade, obtain real angle data of the air film hole, and cause no physical damage to the blade in the measuring process.
Description
Technical Field
The invention relates to the technical field of measurement, in particular to a method for measuring the true angle of a small micropore on an aero-engine blade.
Background
With the increasing of the performance of modern aeroengines, the working environment of each part, especially the blade, is more and more severe, so various technical means are needed to be used for coping with, for example, in order to ensure that the turbine blade has good mechanical properties in a high-temperature and high-pressure environment, the blade is cast into a hollow structure, and a plurality of air film holes are processed on the blade body of the blade, especially on the exhaust edge of the blade body to connect the inner cavity, so that cold air entering the inner cavity can be sprayed out from the air film holes of the blade body, a cold air protection layer is formed on the blade body while taking away the heat of a fixed blade body, 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 another view of the blade of FIG. 1 a; FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a; FIG. 1d is a schematic cross-sectional view of the blade body of the blade of FIG. 1 a; FIG. 1e is a schematic view of the schematic structure of section A-A of FIG. 1 d; wherein X, Y, Z indicated in fig. 1c, 1d and 1e is a blade measurement coordinate system, which is defined according to the standard of the aviation industry department of china, and will not be described herein. Referring to fig. 1a-1e, the aero-engine blade 100 adopts a hollow internal cooling structure, a first air inlet 11 which is formed by casting and is 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, a processing surface 20 parallel to a Z axis is arranged at the rear edge, 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 outlet in the blade tip groove 30 are all directly formed during casting, the processing surface 20 and the air film hole 21 are formed in a subsequent machining sequence, wherein the processing surface 20 is firstly processed, and then the air film hole 21 is connected with the inner cavity of the aeroengine blade 100 after the processing surface 20 is perforated and formed in an electric spark processing mode.
The aperture of the air film hole 21 is generally phi 0.25 mm-phi 0.5mm, the depth is not less than 6mm, the processing surface 20 is at least provided with one group of air film holes 21, 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 group of gas film holes 21 having different diameters, and in fig. 1e, the same group of gas film holes 21 having the same diameter are provided on the processing surface 20.
For the air film hole 21, in the production and processing process of the aeroengine blade 100, connectivity between the air film hole 21 and the inner cavity can be verified through a water flow experiment mode, that is, a closable flexible joint is used to be communicated with the tenon portion of the aeroengine blade 100 (that is, with the first air inlet 11 and the second air inlet 12), and whether all the air film holes 21 can drain water is observed and detected through inputting pressurized water flow, so that whether the air film hole 21 is communicated with the inner cavity or not is judged. In addition, as described in the method for measuring the air flow rate of the turbine blade machine with holes provided in the chinese patent ZL2017112497983 by the inventor, the flow rate data of the air film holes 21 can also be directly measured and obtained.
However, as shown in fig. 1d and 1e, the angle α of the air film hole 21 relative to the X-axis of the blade measurement coordinate system and the angle β of the air film hole with respect to the Z-axis are also required in design, for example, the angle α of the air film hole 21 relative to the X-axis of the blade measurement coordinate system may be designed to be 61.5 ° ± 30', and the angle β of the air film hole 21 relative to the Z-axis of the blade measurement coordinate system may be designed to be 80 ° ± 30'. Because the aperture of the air film hole 21 is too small, no technical scheme is disclosed at present for directly measuring the angle of the air film hole 21.
In the existing production process, only after the parameters of the electric spark machining equipment are set, a large hole with the diameter of 1mm is machined in the aeroengine blade 100 which is machined instead, a standard measuring rod with the diameter of 1 is inserted into a machined hole, then the angle of the standard measuring rod is measured through a three-coordinate machine, and if the angle is qualified, the adjustment angle of a machine tool and/or a clamp is qualified, and then a small hole with the diameter required by a drawing is machined.
The prior art guarantee method has the following defects:
1. only the correct angle (i.e. machining parameters) of the fixture and/or the machine tool can be judged, for example, the angle is measured by matching the large hole with the measuring rod of phi 1, and the small hole with the default machining diameter phi 0.25 is qualified after the angle is qualified, but the large hole of phi 1 is not directly related to the diameter phi 0.25 (the parameter settings of the electric spark machining equipment are different), and the error of the measuring method is large, and is usually between 1 DEG and 1.5 deg.
2. The inner cavities of the aero-engine blades 100 are provided with complex loops and reinforcing ribs, and the measuring bars are easy to interfere after entering the inner cavities, so that the measuring bars incline to one side, and the measuring angles are inaccurate.
3. The aero-engine blade 100 is made of high-temperature alloy material, so that the processing difficulty is high, the processing time is long, and the processing time of a phi 1 hole usually takes about 15 minutes.
4. The aero-engine blade 100 with the phi 1 hole processed can only be scrapped, 2-3 blades are required to be scrapped for each batch of blade processing, the price of each blade is 1 ten thousand to 3 ten thousand, and the waste is extremely large.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a blade micro-pore angle measuring method so as to reduce or avoid the problems.
In order to solve the technical problems, the invention provides a blade micro-pore angle measuring method which is used for directly measuring the actual angle of a gas film hole of an aeroengine blade and comprises the following steps,
And step A, preparing a measuring needle according to the diameter of the air film hole, wherein the measuring needle comprises an insertion part and an extension part, and the diameter d1 of the insertion part is smaller than the diameter of the air film hole by 0.01mm. The diameter d2 of the extension part is 0.02mm larger than the diameter d1 of the insertion part, the length L1 of the insertion part is not smaller than 5mm, and the total length L2 of the measuring needle is not smaller than 12mm.
And B, enabling the end head of the insertion part of the measuring needle prepared in the step A to be in contact with the air film hole end opening, forming negative pressure in the inner cavity of the aeroengine blade, and sucking the insertion part into the air film hole until the extension part is in contact with the air film hole end opening, so that the installation of the measuring needle is completed.
And C, after the installation of the measuring needle is finished in the step B, the angle measurement of the air film hole is finished by utilizing an optical measurement mode, and after measurement data are obtained, the measuring needle is taken out along the axial direction of the measuring needle, so that the angle measurement of the air film hole is finished.
Preferably, in step a, the total length of the measuring needle is set to 20mm or 25mm.
Preferably, in the step a, the diameter of the air film hole is 0.25mm (0, +0.05), and the measuring needle includes a set of six measuring needles with diameters d1 of 0.24mm, 0.25mm, 0.26mm, 0.27mm, 0.28mm, and 0.29mm of the insertion portion.
Preferably, in step B, the device for assembling the measuring needle may comprise a flexible joint for detachable and closeable connection with the dovetail of the aircraft engine blade, said flexible joint being provided with an air passage joint for connection with an air extraction device, and a rigid seat for forming a clamping abutment for said flexible joint, so as to enable the air film hole to face upwards.
Preferably, in the step B, the operator clamps the outer extension part with fingers or tweezers with rubber sleeves, contacts the end of the insertion part with the air film hole port, and keeps contact as tight as possible, after the end of the insertion part contacts with the air film hole port, the clamping force on the outer extension part can be relaxed, so that the outer extension part can rest on fingers or tweezers by means of gravity and cannot fall off optimally, and then the air extractor can be started, so that negative pressure is formed in the inner cavity of the aeroengine blade, and the insertion part is sucked into the air film hole.
Preferably, in step B, the other holes of the blade body than the film holes to be fitted with the measuring needle are plugged with wax.
Preferably, in the step B, in the assembling process, other holes of the blade body except for the air film hole to be assembled with the measuring needle may be covered with a silica gel sheet, and after the air extractor is started and the cavity forms negative pressure, the silica gel sheet is adsorbed to the holes to form a plug.
Preferably, in the step B, a flexible rope loop may be adhered to the end of the extension portion away from the insertion portion through an adhesive, and a cantilever may be disposed above the air film hole on the rigid base, so that the flexible rope loop may be sleeved on the cantilever, then an operator only needs to clamp the extension portion with a finger or tweezers with rubber sleeves, so that after the end of the insertion portion contacts with the air film hole end, an unnecessary portion of the flexible rope loop above the cantilever is twisted into a twisted shape, or is wetted with water to be adhered together, so that the measuring needle is as vertical as possible, and then the clamping of the extension portion may be released, and the measuring needle is basically positioned and supported by using the tension of the flexible rope loop and the supporting force of the air film hole end on the end of the insertion portion.
Preferably, in step B, the flexible loop is made of cotton thread.
Preferably, in the step B, when the measuring needle includes a group of measuring needles having different diameters of the insertion portions, the measuring needle is used in such a manner that the diameter of the insertion portion is from large to small, so that a difference between the insertion portion having the maximum diameter that can be used and the actual aperture of the gas film hole is about 0.1 mm.
The method for measuring the angle of the small micropores of the blade can realize direct measurement of the angle of the air film hole of the blade, obtain real angle data of the air film hole, and cause no physical damage to the blade in the measuring process. Therefore, each blade can be detected, and the qualification rate of the finished product can be greatly improved.
Drawings
The following drawings are only for purposes of illustration and explanation of the present invention and are not intended to limit the scope of the invention. Wherein,
FIG. 1a is a schematic perspective view of an aircraft engine blade;
FIG. 1b is a schematic perspective view of another view of the blade of FIG. 1 a;
FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a;
FIG. 1d is a schematic cross-sectional view of the blade body of the blade of FIG. 1 a;
FIG. 1e is a schematic view of the schematic structure of section A-A of FIG. 1 d;
FIG. 2 is a schematic view of the structure of a measuring needle used in a method for measuring the angle of small micro-holes of a blade according to an embodiment of the present invention;
fig. 3 is a schematic view of the construction of a device for assembling the measuring needle of fig. 2.
Detailed Description
For a clearer understanding of technical features, objects, and effects of the present invention, a specific embodiment of the present invention will be described with reference to the accompanying drawings. Wherein like parts are designated by like reference numerals.
As described in the background art, aiming at the problem that the angle of the air film hole 21 with the existing aperture generally ranging from phi 0.25mm to phi 0.5mm and the depth not smaller than 6mm cannot be directly measured, the inventor has conducted in-depth analysis on the principle thereof, and summarized the root cause as follows:
1. because the diameter of the air film hole 21 is too small, no existing standard measuring rod can be inserted into the air film hole 21 for hole type angle extension measurement.
2. Because the diameter of the air film hole 21 is too small, and the inner cavity of the aeroengine blade 100 is provided with a complex loop and a reinforcing rib, even if a measuring needle with a small diameter is provided, interference with the inner cavity structure after insertion is avoided.
3. Because the aperture of the air film hole 21 is too small, even if there is a measuring needle with a small diameter, in order to have enough exposed portions of the air film hole 21 for measurement, the length-diameter ratio of the air film hole must be very large, so as to avoid inaccurate measurement results caused by bending of the measuring needle due to external force in the use process (i.e., the process of inserting the air film hole 21 and taking out after the measurement).
FIG. 1a is a schematic perspective view of an aircraft engine blade; FIG. 1b is a schematic perspective view of another view of the blade of FIG. 1 a; FIG. 1c is a schematic cross-sectional structural view of the blade of FIG. 1 a; FIG. 1d is a schematic cross-sectional view of the blade body of the blade of FIG. 1 a; FIG. 1e is a schematic view of the schematic structure of section A-A of FIG. 1 d; FIG. 2 is a schematic view of the structure of a measuring needle used in a method for measuring the angle of small micro-holes of a blade according to an embodiment of the present invention; fig. 3 is a schematic view of the construction of a device for assembling the measuring needle of fig. 2. As can be seen in figures 1a-3,
In view of the above-described inventor's analysis, the present invention provides a blade micro-hole angle measurement method for directly measuring the actual angle of the film hole 21 of the aircraft engine blade 100, which includes the steps of,
And step A, preparing a measuring needle 4 according to the diameter of the air film hole 21, wherein the measuring needle 4 comprises an insertion part 41 and an extension part 42, and the diameter d1 of the insertion part 41 is 0.01mm smaller than the diameter of the air film hole 21. The diameter d2 of the extension 42 is 0.02mm larger than the diameter d1 of the insertion 41, the length L1 of the insertion 41 is not smaller than 5mm, and the total length L2 of the measuring needle 4 is not smaller than 12mm.
The inventor finds through calculation analysis that, on the premise that the measuring needle 4 does not bend and deform, as long as the depth of the insertion portion 41 inserted into the air film hole 21 is ensured to be not less than 5mm (including 5 mm), even if the outer extension portion 42 is inclined and deviated due to a gap between the insertion portion 41 and the air film hole 21, the deviation angle of the axis of the outer extension portion 42 from the axis of the air film hole 21 is not more than 12', and the deviation value is smaller than the included angle beta of the air film hole 21 relative to the Z axis of the blade measuring coordinate system, which is mentioned in the background art, can be designed to be within a tolerance range of 80 DEG + -30 ', and the deviation angle of the axis of the outer extension portion 42 from the axis of the air film hole 21 is not more than 12', which is fully applicable to accurate measurement in consideration of the existing measuring method errors mentioned in the background art, which are between 1 DEG and 1.5 deg.
Since the depth of the film hole 21 is not less than 6mm, the diameter d1 of the insertion portion 41 is 0.01mm smaller than the diameter of the film hole 21. When the diameter d2 of the extension 42 is 0.02mm greater than the diameter d1 of the insertion portion 41, this means that the diameter d2 of the extension 42 is greater than the diameter of the air film hole 21, so that the extension 42 is prevented from entering the air film hole 21, and the portion of the measuring needle 4 entering the inner cavity of the aero-engine blade 100 is prevented from being too long, so that interference with the inner cavity structure occurs.
The total length L2 of the measuring needle 4 is not less than 12mm, which ensures that the extension 42 has a length of at least 10mm, wherein 5mm near the air film hole 21 is used for accurate measurement, and a distal portion is used for handling the measuring needle 4 (for example, for clamping), and of course, the measuring needle 4 cannot be too long, usually not more than 50mm, so that it is avoided that after the extension 42 is too long, the axis is bent due to its own weight or external environmental influence, thereby affecting the measurement accuracy. In a preferred embodiment, the total length of the measuring needle 4 is set to 20mm or 25mm.
The measuring needle 4 can be prepared by the following method:
Firstly, a blank having a length greater than the total length of the measuring needle 4 and a diameter equal to the diameter d1 of the insertion portion 41 is manufactured,
Thereafter, a portion for molding the extension 42 is formed on the blank by means of a metal plating film (e.g., copper plating) or painting or spraying a resin material (e.g., resin silicone),
Finally, cutting is carried out according to the designed size on the basis of the blank, and the preparation of the measuring needle 4 is completed.
In fig. 2, the end of the insertion portion 41 has a protrusion, which is a process structure formed during cutting, and although the protrusion is shown in fig. 2, the length of the protrusion is not considered in the present invention, that is, the length L1 of the insertion portion 41 and the total length L2 of the measuring needle 4 defined in the present invention do not include the process protrusion structure, because the length of the protrusion is generally not greater than 0.05 mm.
In a specific embodiment, when the aperture of the gas film hole 21 is 0.25mm, the diameter d1 of the insertion portion 41 of the measuring pin 4 is 0.24mm, and the diameter d2 of the extension portion 42 is 0.26mm. In production, the gas film hole 21 may be given a tolerance range, for example, the diameter of the gas film hole 21 is 0.25mm (0, +0.05), that is, the maximum diameter of the gas film hole 21 may be up to 0.30mm, in which case, a set of a plurality of measuring pins 4 with different diameters may be prepared according to the tolerance range of the gas film hole 21, for example, six measuring pins 4 with diameters d1 of 0.24mm, 0.25mm, 0.26mm, 0.27mm, 0.28mm, 0.29mm may be prepared according to the tolerance range of the gas film hole 21, and then the difference between the actual diameters of the maximum diameter of the insert 41 and the gas film hole 21 may be ensured to be about 0.1mm, so that the possible deviation angle between the axis of the extension portion 42 and the axis of the gas film hole 21 may be excessively large due to excessively large difference.
And B, enabling the end of the insertion part 41 of the measuring needle 4 prepared in the step A to be in contact with the port of the air film hole 21, forming negative pressure in the inner cavity of the aeroengine blade 100, and sucking the insertion part 41 into the air film hole 21 until the extension part 42 is in contact with the port of the air film hole 21, so as to finish the installation of the measuring needle 4.
The length-diameter ratio of the measuring pin 4 is large and the diameter is too small, and if the insertion portion 41 is simply pressed into the gas film hole 21 from outside to inside by using an axial force, the outer extension portion 42 and the insertion portion 41 are easily distorted, and thus an accurate measurement result cannot be obtained.
In the present invention, the insert 41 is sucked into the air film hole 21 by the negative pressure formed in the inner cavity of the aero-engine blade 100 by the pressure difference of air, and in this case, the external force is not required to drive or clamp the extension 42, so that the twisting between the extension 42 and the insert 41 can be effectively prevented.
The device for creating the negative pressure may be modified on the basis of the device for verifying the connectivity between the air film hole 21 and the inner cavity described in the background art, and may also comprise a flexible joint for the sealing connection with the tenon portion of the aeroengine blade 100, only by replacing the water supply line connected with the flexible joint with an air pipe connected with an air extraction device.
Fig. 3 is a schematic view of the construction of a device for assembling the measuring needle of fig. 2. Referring to fig. 3, the device 5 for assembling the measuring needle 4 may comprise a flexible joint 51 for detachable and closeable connection to the dovetail of the aircraft engine blade 100, said flexible joint 51 being provided with an air passage joint 52 for connection to an air extraction device (not shown), and a rigid base 53 for forming a clamping abutment for the flexible joint 51, so as to enable the air film hole 21 to face upwards.
After the flexible joint 51 is sleeved on the tenon portion of the aero-engine blade 100 to form a closed connection, the flexible joint 51 may be placed on the rigid base 53, so that the processing surface 20 where the air film hole 21 is located faces upwards, and then the air passage joint 52 may be connected with an air extraction device through an air pipe (not shown in the figure).
Then, the operator holds the extension portion 42 with fingers or tweezers with rubber sleeves, the end of the insertion portion 41 contacts with the port of the air film hole 21, the contact is kept as tight as possible, after the end of the insertion portion 41 contacts with the port of the air film hole 21, the holding force on the extension portion 42 can be relaxed, so that the extension portion 42 can rest on the fingers or tweezers by means of gravity to be optimal, and then the air extractor can be started, so that negative pressure is formed in the inner cavity of the aeroengine blade 100, and the insertion portion 41 is sucked into the air film hole 21.
As described in the background art, the air film holes 21 are machined by electric spark machining, so that the aperture and the inclination angle of each group of air film holes 21 are the same, which means that, for each group of air film holes 21, only one air film hole 21 needs to be measured, in order to reduce the influence of other holes on the blade body on the cavity pressure, other holes of the blade body except for the air film holes 21 needing to be assembled with the measuring needle 4 can be sealed in the assembling process, the sealing mode can be that wax is used for sealing, or a silica gel piece is used for covering, and the sealing effect of sealing with wax is good, but the subsequent heating and the wax removal are needed, the silica gel piece needs to be started by the air extractor, and after the cavity forms negative pressure, the silica gel piece can be adsorbed on the hole to form the covering, so that the air extraction pressure needs to be regulated and controlled.
The manner in which the operator grips the extension 42 with his fingers or forceps with rubber sleeves requires a high level of skill in the operator's operation. The inventors have found through practice that the assembly of the measuring needle 4 can be assisted by means of a flexible connection with an auxiliary suspension.
Referring to fig. 2 and 3, a flexible rope ring 43 may be adhered to the end of the extension portion 42 away from the insertion portion 41 through adhesive, the rigid base 53 may be provided with a cantilever 54 above the air film hole 21, so that the flexible rope ring 43 may be sleeved on the cantilever 54, then an operator only needs to clamp the extension portion 42 with fingers or tweezers with rubber sleeves, after the end of the insertion portion 41 contacts with the end of the air film hole 21, the redundant portion of the flexible rope ring 43 above the cantilever 54 is twisted into a twisted shape, or is wetted with water to adhere the flexible rope ring 43 together, so that the measuring needle 4 is as vertical as possible, and then the clamping of the extension portion 42 may be released, and the measuring needle 4 is basically positioned and supported by using the tensile force of the flexible rope ring 43 and the supporting force of the end of the air film hole 21 to the end of the insertion portion 41.
When the inner cavity of the aero-engine blade 100 forms a negative pressure, the pressure difference of air is much larger than the bonding force between the redundant parts of the flexible rope loop 43 above the cantilever 54, so that the flexible rope loop 43 is ensured not to be blocked in the process of inserting the insertion part 41 into the air film hole 21.
The flexible cord 43 may be cotton or a plastic thread like a fishing line or a thin elastic band.
When the measuring needle 4 is assembled, the flexible loop 43 may be directly removed from the cantilever 54 if the length is long, and the flexible joint 51 may be pushed forward if the length is short, so that the flexible loop 43 may be removed from the cantilever 54, and the cantilever 54 may be made into a telescopic structure, and may be separated from contact with the flexible loop 43 by retraction.
And C, after the installation of the measuring needle 4 is completed in the step B, the angle measurement of the air film hole 21 is completed by utilizing an optical measurement mode, after measurement data are obtained, the measuring needle 4 is taken out along the axial direction of the measuring needle 4, and the angle measurement of the air film hole 21 is completed.
The existing optical measurement method includes using a digital measurement projector or a non-contact three-coordinate measuring machine to achieve higher measurement accuracy, for example, the angle accuracy can reach 8' by using a measurement projector manufactured by the company of Shandong precision instruments, inc. in Dongguan, which is commercially available, so that the angle data of the measuring needle 4 can be obtained by using the image measurement of the extension 42 about 5mm outside the port of the air film hole 21 by using these commercially available devices, that is, the angle data of the air film hole 21 is obtained by a direct measurement method.
In the production process of the aero-engine blade 100, the guarantee of the machining coordinate system and the measuring coordinate system is completed through clamping the tenon part of the aero-engine blade 100. Therefore, how to ensure the clamping of the aero-engine blade 100 during the measurement process is not an important aspect of the present invention, and particularly if the clamping stability of the blade is ensured, reference may be made to the prior blade clamping methods and technical solutions described in several prior application patent documents of the inventor, such as 201610873006.9, 201811495958.7, etc.
In the measuring process of the invention, only one clamp can be arranged to ensure that the Z axis is vertical to the horizontal plane during clamping, so that the data of the included angle beta of the air film hole 21 relative to the Z axis of the blade measuring coordinate system can be conveniently obtained, the X axis is horizontal during the horizontal placement of the blade body during the clamping of the other clamp, and the measuring needle 4 is in an upward posture and cannot fall off, so that the data of the included angle alpha of the air film hole 21 relative to the X axis of the blade measuring coordinate system can be conveniently obtained. The difference between the two clamps and the existing clamps is that after the aeroengine blade 100 is clamped, the positions of the blade bodies are different, or the corresponding XY position relationship (which is convenient for adjusting the placing position of the clamps on the optical measurement device) needs to be marked on the clamps in advance according to the space positions of the tenon portions in the clamping state, and the clamping of the tenon portions can be completely realized by adopting the prior art, so that the structure of the clamps is not repeated in the document of the invention.
The method for measuring the angle of the small micropores of the blade can realize direct measurement of the angle of the air film hole of the blade, obtain real angle data of the air film hole, and cause no physical damage to the blade in the measuring process. Therefore, each blade can be detected, and the qualification rate of the finished product can be greatly improved.
It should be understood by those skilled in the art that while the present invention has been described in terms of several embodiments, not every embodiment contains only one independent technical solution. The description is given for clearness of understanding only, and those skilled in the art will understand the description as a whole and will recognize that the technical solutions described in the various embodiments may be combined with one another to understand the scope of the present invention.
The foregoing is illustrative of the present invention and is not to be construed as limiting the scope of the invention. Any equivalent alterations, modifications and combinations thereof will be effected by those skilled in the art without departing from the spirit and principles of this invention, and it is intended to be within the scope of the invention.
Claims (10)
1. A blade micro-pore angle measuring method is characterized in that the method is used for directly measuring the actual angle of a gas film hole of an aeroengine blade and comprises the following steps,
A step A of preparing a measuring needle according to the diameter of the air film hole, wherein the measuring needle comprises an insertion part and an extension part, the diameter d1 of the insertion part is 0.01mm smaller than the diameter of the air film hole, the diameter d2 of the extension part is 0.02mm larger than the diameter d1 of the insertion part, the length L1 of the insertion part is not smaller than 5mm, the total length L2 of the measuring needle is not smaller than 12mm,
B, enabling the end head of the insertion part of the measuring needle prepared in the step A to be in contact with the air film hole end opening, forming negative pressure in the inner cavity of the aeroengine blade, sucking the insertion part into the air film hole until the extension part is in contact with the air film hole end opening, completing the installation of the measuring needle,
And C, after the installation of the measuring needle is finished in the step B, the angle measurement of the air film hole is finished by utilizing an optical measurement mode, and after measurement data are obtained, the measuring needle is taken out along the axial direction of the measuring needle, so that the angle measurement of the air film hole is finished.
2. Method according to claim 1, characterized in that in step a the total length of the measuring needle is set to 20mm or 25mm.
3. The method according to claim 1, wherein in step a, the diameter of the gas film holes is 0.25mm (0, +0.05), and the measuring needle includes a set of six measuring needles having a diameter d1 of the insertion portion of 0.24mm, 0.25mm, 0.26mm, 0.27mm, 0.28mm, 0.29 mm.
4. A method according to claim 1, characterized in that in step B the means for assembling the measuring pin comprise a flexible joint for detachable and closeable connection with the dovetail of the aircraft engine blade, said flexible joint being provided with an air passage joint for connection with an air extraction device, and a rigid seat for forming a clamping abutment for the flexible joint, so as to enable the air film hole to face upwards.
5. The method according to claim 4, wherein in step B, the operator holds the outer extension part with a finger or a pair of tweezers with rubber sleeves, contacts the tip of the insertion part with the port of the air film hole and keeps the contact as tight as possible, and after the tip of the insertion part contacts the port of the air film hole, the holding force on the outer extension part is released, so that the outer extension part can rest on the finger or the tweezers by gravity to be optimal, and then the air suction device can be started, so that the inner cavity of the blade of the aeroengine forms negative pressure, and the insertion part is sucked into the air film hole.
6. The method according to claim 1, characterized in that in step B, the other holes of the blade body than the film holes to be fitted with the measuring needle are plugged with wax.
7. The method according to claim 5, wherein during the assembly process, other holes of the blade body except for the air film hole to be assembled with the measuring needle are covered by a silica gel sheet, and after the air suction device is started and the cavity forms negative pressure, the silica gel sheet is adsorbed to the holes to form a plug.
8. The method according to claim 4, wherein in the step B, a flexible rope loop is adhered to the extension portion at the end far from the insertion portion through adhesive, the rigid base is provided with a cantilever above the air film hole, so that the flexible rope loop is sleeved on the cantilever, then an operator only needs to clamp the extension portion with fingers or tweezers with rubber sleeves, after the end of the insertion portion is contacted with the air film hole end opening, the redundant part of the flexible rope loop above the cantilever is twisted into a twist shape, or is wetted with water to be adhered together, so that the measuring needle is vertical as much as possible, and then the clamping of the extension portion can be released, and the measuring needle is basically positioned and supported by the tension of the flexible rope loop and the supporting force of the air film hole end opening to the end of the insertion portion.
9. The method of claim 8, wherein in step B, the flexible loop is made of cotton thread.
10. The method according to claim 1, characterized in that in step B, when the measuring needle comprises a set of measuring needles having different diameters of the insertion portions, the use is made in such a way that the diameter of the insertion portions is from large to small, so that the difference between the actual aperture of the insertion portion (41) of the maximum diameter used and the air film hole (21) is about 0.1 mm.
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