CN112797922A - Use method of measuring needle for measuring angle of small micropore of blade - Google Patents
Use method of measuring needle for measuring angle of small micropore of blade Download PDFInfo
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- CN112797922A CN112797922A CN201911103277.6A CN201911103277A CN112797922A CN 112797922 A CN112797922 A CN 112797922A CN 201911103277 A CN201911103277 A CN 201911103277A CN 112797922 A CN112797922 A CN 112797922A
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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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- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
A method for using a measuring needle for measuring the angle of a small micropore of a blade comprises an inserting part and an extending part and comprises the following steps of A, providing a device for assembling the measuring needle, B, enabling a blade air film hole to face upwards, contacting the end head of the inserting part with a port of the air film hole, starting an air exhaust device, forming negative pressure in an inner cavity of the blade of an aircraft engine, sucking the inserting part into the air film hole until the extending part is contacted with the port of the air film hole, and completing the assembly of the measuring needle. The use method of the measuring needle for measuring the angle of the small micropore of the blade provided by the invention can assemble the special measuring needle into the air film hole of the blade, thereby obtaining the real air film hole angle data through optical measurement.
Description
Technical Field
The invention relates to the technical field of measurement, in particular to a using method of a measuring needle for measuring the real angle of a small micropore on an aircraft engine blade.
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.
Disclosure of Invention
The object of the present invention is to provide a method for using a measuring tip for measuring the angle of a small aperture of a blade, which reduces or avoids the above-mentioned problems.
In order to solve the technical problem, the invention provides a use method of a measuring needle for measuring the angle of a small micropore of a blade, which is used for assembling the measuring needle into a gas film hole of an aircraft engine blade so as to directly measure the actual angle of the gas film hole, wherein the measuring needle comprises an insertion part and an extension part, and the diameter d1 of the insertion part is 0.01mm smaller than the diameter of the gas film hole. The diameter d2 of the extension being at least 0.02mm greater than the diameter d1 of the insertion, comprising the steps of:
step A, providing a device for assembling the measuring needle, wherein the device comprises a flexible joint which is detachably connected with the tenon part of the blade of the aero-engine in a sealing manner, the flexible joint is provided with an air path joint which is connected with an air exhaust device, and a rigid base which is used for clamping and supporting the flexible joint so as to enable the air film hole to be upward. After the flexible joint is sleeved at the tenon part of the blade of the aero-engine to form closed connection, the flexible joint can be arranged on the rigid base, so that the air film hole faces upwards, and then the air path joint can be connected with an air exhaust device through an air pipe.
And B, contacting the end of the insertion part with the port of the air film hole, starting the air exhaust device, forming negative pressure in the inner cavity of the blade of the aircraft engine, so that the insertion part is sucked into the air film hole until the extension part is contacted with the port of the air film hole, and finishing the assembly of the measuring needle.
Preferably, in step B, an operator clamps the extension portion with a finger or a pair of tweezers with a rubber sleeve, the tip of the insertion portion is in contact with the air film hole port and is kept in close contact as much as possible, after the tip of the insertion portion is in contact with the air film hole port, the clamping force on the extension portion can be released, so that the extension portion can be supported on the finger or the tweezers by means of gravity and cannot fall off optimally, and then the air exhaust device can be started to enable the inner cavity of the aero-engine blade to form negative pressure, so that the insertion portion is sucked into the air film hole.
Preferably, in step B, the other holes of the blade body except the air film hole to be fitted with the measurement tip are sealed with wax.
Preferably, in the step B, in the assembling process, other holes of the blade body except the air film hole to which the measurement needle needs to be assembled may be covered with a silicone sheet, and after the air-extracting device is started and the inner cavity forms negative pressure, the silicone sheet is adsorbed to the holes to form plugging.
Preferably, a flexible rope loop is bonded to one end, far away from the insertion portion, of the extension portion through an adhesive, in step a, a cantilever is arranged above the air film hole of the rigid base, in step B, the flexible rope loop is firstly sleeved on the cantilever, then an operator only needs to clamp the extension portion through fingers or tweezers with rubber sleeves to enable the end of the insertion portion to be in contact with the port of the air film hole, then the redundant portion of the flexible rope loop above the cantilever is twisted into a twist shape, or is wetted by water to be bonded together, so that the measuring needle is vertical as much as possible, then clamping of the extension portion can be released, and basic positioning and supporting of the measuring needle are carried out by using the tensile force of the flexible rope loop and the supporting force of the port of the air film hole on the end of the insertion portion.
Preferably, in step a, the rigid base is a U-shaped metal block, a dovetail groove is formed at the top of the rigid base, and the cantilever is slidably connected with the rigid base through the dovetail groove.
Preferably, the cantilever is made of a resin material by injection molding.
Preferably, the flexible loop is made of cotton thread.
The use method of the measuring needle for measuring the angle of the small micropore of the blade can assemble the special measuring needle into the air film hole of the blade, so that the real air film hole angle data can be obtained through optical measurement, and the blade cannot be physically damaged in the measuring process. Therefore, each blade can be detected, and the qualification rate of finished products can be 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 measurement needle used in a method for using the measurement needle for measuring the angle of a small micropore of a blade according to an embodiment of the invention;
fig. 3 is a schematic structural view of a device for assembling the measurement tip of fig. 2;
fig. 4 is a schematic perspective view of the rigid base of fig. 3.
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.
As described in the background art, the inventor has conducted an in-depth analysis on the principle of the conventional problem that the angle of the gas film hole 21 cannot be directly measured, where the hole diameter is generally between 0.25mm and 0.5mm, and the depth is not less than 6mm, and summarized the fundamental reason that:
1. since the pore diameter of the gas film pores 21 is too small, no existing standard measuring rod can be inserted therein for pore-type angular extension measurement.
2. Because the aperture of the film hole 21 is too small, and the inner cavity of the aero-engine blade 100 is provided with a complex loop and a complex reinforcing rib, even if a small-diameter measuring needle is provided, the interference between the inserted measuring needle and the inner cavity structure is avoided.
3. Since the aperture of the gas film hole 21 is too small, even if there is a small-diameter measurement needle, in order to have enough portion exposed out of the gas film hole 21 for measurement, the length-diameter ratio thereof is inevitably large, and how to avoid the measurement result inaccuracy caused by bending of the measurement needle due to external force in the using process (i.e. the process of inserting the gas film hole 21 and taking out after measurement).
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 measurement needle used in a method for using the measurement needle for measuring the angle of a small micropore of a blade according to an embodiment of the invention; fig. 3 is a schematic structural view of a device for assembling the measurement tip of fig. 2; fig. 4 is a schematic perspective view of the rigid base of fig. 3. As shown with reference to figures 1a-4,
in view of the analysis of the inventor, the invention provides a use method of a measurement needle for measuring the angle of a small micropore of a blade, which is used for assembling the measurement needle 4 specially made by the inventor into a gas film hole 21 of an aircraft engine blade 100 so as to realize direct measurement of the actual angle of the gas film hole 21, wherein the measurement needle 4 can be prepared according to the diameter of the gas film hole 21, the measurement needle 4 comprises an insertion part 41 and an extension part 42, and the diameter d1 of the insertion part 41 is smaller than the diameter of the gas film hole 21 by 0.01 mm. The diameter d2 of the extension 42 is at least 0.02mm greater than the diameter d1 of the insertion 41, the length L1 of the insertion 41 is not less than 5mm, and the total length L2 of the measurement tip 4 is not less than 12 mm.
The inventors found, through computational analysis, that, even if the extension portion 42 is inclined and deviated due to a gap between the insertion portion 41 and the gas film hole 21, the deviation angle between the axis of the extension portion 42 and the axis of the gas film hole 21 does not exceed 12 ' on the premise that the measurement needle 4 is not bent and deformed, and this deviation value is smaller than the included angle β of the gas film hole 21 with respect to the Z axis of the blade measurement coordinate system mentioned in the background art, which may be designed to be within a tolerance range of 80 ° ± 30 ', and the deviation angle between the axis of the extension portion 42 and the axis of the gas film hole 21 is not more than 12 ' may be fully used for accurate measurement, considering that the error of the conventional measurement method mentioned in the background art is between 1 ° and 1.5 °.
Since the depth of the gas film hole 21 is not less than 6mm, when the diameter d1 of the insertion portion 41 is smaller than the diameter of the gas film hole 21 by 0.01 mm. When the diameter d2 of the extension portion 42 is 0.02mm larger than the diameter d1 of the insertion portion 41, the diameter d2 of the extension portion 42 is larger than the diameter of the film hole 21, so that the extension portion 42 can be prevented from entering the film hole 21, and the part of the measurement needle 4 entering the inner cavity of the aircraft engine blade 100 is too long, so that the measurement needle interferes with the inner cavity structure. Of course, the diameter d2 of the extension portion 42 should not be too large, which would cause the mass difference between the extension portion 42 and the insertion portion 41 to be too large, and thus would cause the axial bending to be easily caused by the self-weight or the external environment, and in a preferred embodiment, the diameter d2 of the extension portion 42 is 0.02mm larger than the diameter d1 of the insertion portion 41.
A total length L2 of the measurement tip 4 of not less than 12mm ensures that the extension 42 can have a length of at least 10 mm, wherein 5mm close to the film hole 21 can be used for accurate measurement and the distal portion can be used for handling (e.g. for clamping) the measurement tip 4, although the measurement tip 4 cannot be too long, usually not more than 50mm, so as to avoid that the measurement accuracy is affected by the bending of the axis due to its own weight or external environmental influences after the extension 42 is too long. In a preferred embodiment, the total length of the measurement tip 4 is set to 20mm or 25 mm.
The measurement tip 4 can be prepared by the following method:
first, a blank is manufactured having a length which is greater than the total length of the measurement tip 4, a diameter which is equal to the diameter d1 of the insertion portion 41,
then, a portion for molding the extension portion 42 is formed on the blank by means of metal plating (e.g., copper plating) or painting or spraying a resin material (e.g., resin silicone),
finally, cutting is carried out according to the design 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 the cutting process, and the length of the protrusion is usually not more than 0.05mm, so although it 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 measurement tip 4 defined in the present invention do not include the process protrusion structure.
In a specific embodiment, when the diameter of the air film hole 21 is 0.25mm, the diameter d1 of the insertion part 41 of the measurement tip 4 is 0.24mm, and the diameter d2 of the extension part 42 is 0.26 mm. In production, the gas film holes 21 are given a tolerance range, for example, the hole diameter of the gas film holes 21 is 0.25mm (0, +0.05), that is, the hole diameter of the gas film holes 21 can be up to 0.30mm at the maximum, in this case, a plurality of measurement needles 4 of different diameters may be prepared according to the tolerance range of the gas film hole 21 at intervals of 0.01mm from each other, as six measurement needles 4 having diameters d1 of 0.24mm, 0.25mm, 0.26mm, 0.27mm, 0.28mm, 0.29mm of the insertion part 41 can be prepared, and then used in such a manner that the diameter d1 of the insertion part 41 is increased to be decreased, this ensures that the difference between the actual diameter of the insertion portion 41 and the actual diameter of the gas film hole 21 is about 0.1mm, thereby avoiding excessive differences that would result in excessive possible angles of deviation of the axis of the extension 42 from the axis of the film hole 21.
The invention discloses a use method of a measuring needle for measuring the angle of a small micropore of a blade, which comprises the following steps:
step a, providing a device 5 for assembling the measuring needle 4, as shown in fig. 3 and 4, wherein the device 5 comprises a flexible joint 51 for detachably and sealably connecting with a tenon of the aircraft engine blade 100, the flexible joint 51 is provided with an air passage joint 52 for connecting with an air extraction device (not shown in the figure), and a rigid base 53 for forming a clamping support for the flexible joint 51 so as to enable the air film hole 21 to be upward. After the flexible joint 51 is sleeved on the tenon portion of the aircraft engine blade 100 to form a closed connection, the flexible joint 51 may be placed on the rigid base 53, so that the film hole 21 faces upward, and then the air path joint 52 may be connected to an air extractor through an air tube (not shown).
The device 5 for creating negative pressure according to the present invention may be modified from the device for verifying the connectivity between the film hole 21 and the cavity described in the background of the invention, and may also include a flexible joint for sealing connection with the tenon of the blade 100 of the aircraft engine, except that the water supply line connected to the flexible joint is replaced by a gas pipe connected to a gas extraction device.
And step B, contacting the end of the insertion part 41 of the measuring needle 4 with the port of the air film hole 21, forming negative pressure in the inner cavity of the aircraft engine blade 100, so that the insertion part 41 is sucked into the air film hole 21 until the extension part 42 is contacted with the port of the air film hole 21, and finishing the assembly of the measuring needle 4.
The aspect ratio of the measurement tip 4 is large and the diameter is too small, and if the insertion portion 41 is pressed into the gas film hole 21 from the outside to the inside by using an axial force alone, the distortion is easily generated between the extension portion 42 and the insertion portion 41, and an accurate measurement result cannot be obtained.
In the present invention, negative pressure is formed in the inner cavity of the aircraft engine blade 100, and the insert portion 41 is sucked into the film hole 21 by using the pressure difference of air, in this case, the external force is not required to be too large to drive or clamp the extension portion 42, so that the distortion between the extension portion 42 and the insert portion 41 can be effectively avoided.
After aeroengine blade 100 is clamped, operating personnel can with the finger or have the tweezers centre gripping of rubber sleeve epitaxial portion 42, will the tip of inserted part 41 with the contact of gas film hole 21 port to keep the contact as far as possible inseparable, the tip of inserted part 41 with after the contact of gas film hole 21 port, can relax right the clamping-force of epitaxial portion 42, with epitaxial portion 42 can rely on gravity to lean on finger or tweezers not to fall for the best, later can start air exhaust device, make aeroengine blade 100's inner chamber forms the negative pressure, thereby will inserted part 41 inhales gas film hole 21.
As described in the background art, the air film holes 21 are processed by an electrical discharge machining method, so that the aperture and the inclination angle of each group of the air film holes 21 are the same, which means that only one of the air film holes 21 needs to be measured for each group of the air film holes 21, in order to reduce the influence of other holes on the leaf body on the pressure of the inner cavity, the other holes of the leaf body except the air film holes 21 on which the measuring needles 4 need to be assembled can be sealed in the assembling process, the sealing method can be sealing with wax, or covering with silicon film, the sealing effect of wax is good, but the wax needs to be removed by heating, the silicon film covering needs to be started by the air extractor, the silicon film can be adsorbed on the holes to form the covering after the inner cavity forms negative pressure, and therefore the air extraction pressure needs to be adjusted and controlled.
The operator has a high requirement on the operating skill level of the operator in a manner that the operator clamps the extension portion 42 with a finger or a pair of tweezers with a rubber sleeve. The inventors have found in practice that the assembly of the measurement tip 4 can be assisted by means of a flexible connection plus an auxiliary suspension.
As shown in fig. 2-4, the extension 42 may be glued at its end remote from the insertion portion 41 with a flexible loop 43, the rigid base 53 may be provided with a cantilever 54 above the film hole 21, such that the flexible loop 43 may be first looped over the cantilever 54, then the operator only needs to hold the extension part 42 with fingers or tweezers with rubber sleeves to make the end of the insertion part 41 contact with the port of the air film hole 21, then the surplus part of the flexible rope loop 43 above the cantilever 54 is twisted into a twist shape, or the measuring needle 4 is wetted by water to be adhered together, so that the measuring needle 4 is as vertical as possible, then the clamping of the extending part 42 is released, and the measuring needle 4 is basically positioned and supported by the tensile force of the flexible rope 43 and the supporting force of the end of the inserting part 41 by the port of the air film hole 21.
When negative pressure is formed in the inner cavity of the aircraft engine blade 100, the pressure difference of air is much greater 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 does not cause obstruction in the process of inserting the insertion part 41 into the film hole 21.
The flexible string loop 43 may be a cotton thread, a plastic filament similar to a fishing line, or an elastic thin rubber band.
When the measuring tip 4 is assembled, the flexible loop 43 may be directly removed from the cantilever 54 if the length is long, or may be pushed forward to remove the flexible loop 43 from the cantilever 54 if the length is short, or the cantilever 54 may be made into a telescopic structure (e.g. a structure similar to an old radio antenna) and released from contact with the flexible loop 43 by retracting.
As shown in fig. 4, the rigid base 53 may be a U-shaped metal block, which facilitates the placement of the flexible joint 51. The top of the rigid base 53 may be provided with a dovetail groove 531, the cantilever 54 may be made of resin material by injection molding, and the cantilever 54 may be slidably connected to the rigid base 53 through the dovetail groove 531, so as to adjust the position of the cantilever 54, thereby facilitating the measurement tip 4 to be as vertical as possible. The assembly of the measuring tip 4 is completed.
After the installation of the measurement needle 4 is completed in step B, the angle measurement of the air film hole 21 can be completed by using an optical measurement mode, and after measurement data is obtained, the measurement needle 4 is taken out along the axial direction of the measurement needle 4.
The conventional optical measurement method, including using a digital measurement projector or a non-contact three-dimensional measuring machine, can achieve a high measurement accuracy, for example, the angle accuracy of the measurement projector produced by wang precision instruments ltd in Dongguan, which is commercially available, can reach 8', so that the angle data of the measurement needle 4 can be obtained by these commercially available devices by measuring the image of the extension portion 42 which is about 5mm outside the port of the air film hole 21, that is, the angle data of the air film hole 21 can be obtained by a direct measurement method.
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. Therefore, how to guarantee the clamping of the aero-engine blade 100 in the measurement process is not the focus of the present invention, and particularly if the clamping of the blade is guaranteed to be stable, reference may be made to the existing blade clamping methods and technical solutions described in several prior patent applications of the inventor, such as 201610873006.9 and 201811495958.7.
In the measuring process, only one clamp can be arranged to ensure that the Z axis is vertical to the horizontal plane when the clamp is clamped, 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 acquired, the other clamp is arranged to ensure that the X axis is horizontal when the blade body is horizontally placed when the clamp is clamped, and the measuring needle 4 does not fall off when the measuring needle is in an upward posture, 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 acquired. The two clamps are different from the existing clamp only in that after the aero-engine blade 100 is clamped, the blade body is in a different position, or a corresponding XY position relationship needs to be marked on the clamp in advance according to the spatial position of the tenon part in the clamped state (the placing position of the clamp is convenient to adjust and measure on an optical measurement device), and the clamping of the tenon part can be completely realized by adopting the prior art, so in the file of the invention, the structure of the clamp is not repeated.
The use method of the measuring needle for measuring the angle of the small micropore of the blade can assemble the special measuring needle into the air film hole of the blade, so that the real air film hole angle data can be obtained through optical measurement, and the blade cannot be physically damaged in the measuring process. Therefore, each blade can be detected, and the qualification rate of finished products can be 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 (8)
1. Use of a measurement needle for the angular measurement of small pores of a blade, characterized in that it is used for fitting a measurement needle into a film hole of an aircraft engine blade, thereby enabling direct measurement of the actual angle of the film hole, the measurement needle comprising an insertion portion and an extension portion, the diameter d1 of the insertion portion being 0.01mm smaller than the diameter of the film hole. The diameter d2 of the extension being at least 0.02mm greater than the diameter d1 of the insertion, comprising the steps of:
step A, providing a device for assembling the measuring needle, wherein the device comprises a flexible joint which is detachably connected with the tenon part of the blade of the aero-engine in a sealing manner, the flexible joint is provided with an air path joint which is connected with an air exhaust device, and a rigid base which is used for clamping and supporting the flexible joint so as to enable the air film hole to be upward. After the flexible joint is sleeved at the tenon part of the blade of the aero-engine to form closed connection, the flexible joint can be arranged on the rigid base, so that the air film hole faces upwards, and then the air path joint can be connected with an air exhaust device through an air pipe.
And B, contacting the end of the insertion part with the port of the air film hole, starting the air exhaust device, forming negative pressure in the inner cavity of the blade of the aircraft engine, so that the insertion part is sucked into the air film hole until the extension part is contacted with the port of the air film hole, and finishing the assembly of the measuring needle.
2. The method according to claim 1, wherein in step B, an operator holds the extension portion with a finger or a pincette with a rubber sleeve, brings the tip of the insertion portion into contact with the port of the film hole and keeps the contact as close as possible, and after the tip of the insertion portion is brought into contact with the port of the film hole, the holding force on the extension portion can be released, so that the extension portion can be supported against the finger or the pincette by gravity optimally, and then the suction device is activated to form a negative pressure in the cavity of the aero-engine blade, thereby sucking the insertion portion into the film hole.
3. Method according to claim 1, characterized in that in step B the other cavities of the blade body except the air film hole where the measurement tip needs to be fitted are plugged with wax.
4. The method according to claim 1, wherein in step B, during the assembly process, the holes of the blade body other than the air film hole for assembling the measuring needle are covered with a silicone sheet, and after the suction device is started and the inner cavity is pressurized, the silicone sheet is adsorbed on the holes to form a plug.
5. A method according to claim 1, wherein the extension portion is adhesively bonded at an end remote from the insertion portion with a flexible loop of thread, in step a, the rigid base 53 may be provided with a cantilever 54 above the film hole 21, in the step B, the flexible rope loop is sleeved on the cantilever, then an operator only needs to clamp the extension part by fingers or tweezers with rubber sleeves to enable the end of the insertion part to be contacted with the port of the air film hole, and then the redundant part of the flexible rope loop above the cantilever is twisted into a twist shape, or wetting the flexible rope ring with water to enable the flexible rope ring to be adhered together, so that the measuring needle is vertical as much as possible, then releasing the clamping of the extending part, and performing basic positioning and leaning on the measuring needle by utilizing the tensile force of the flexible rope ring and the supporting force of the end of the inserting part on the port of the air film hole.
6. The method according to claim 5, wherein in step A, the rigid base is a U-shaped metal block, a dovetail groove is formed on the top of the rigid base, and the cantilever is slidably connected with the rigid base through the dovetail groove.
7. The method of claim 6, wherein the cantilever is injection molded from a resin material.
8. The method of claim 5, wherein the flexible loop is made of cotton thread.
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| CN113859764A (en) * | 2021-09-29 | 2021-12-31 | 中国航发动力股份有限公司 | Protection device for guide blade cavity of turbine guide assembly and preparation method |
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