CN114043183A - Turbine blade machining method and turbine blade calibration method - Google Patents
Turbine blade machining method and turbine blade calibration method Download PDFInfo
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- CN114043183A CN114043183A CN202111512244.4A CN202111512244A CN114043183A CN 114043183 A CN114043183 A CN 114043183A CN 202111512244 A CN202111512244 A CN 202111512244A CN 114043183 A CN114043183 A CN 114043183A
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Abstract
The invention discloses a processing method of a turbine blade, which comprises the steps of firstly adopting a six-point positioning method to clamp and position a precision casting blank, then adopting a high-precision sawtooth processing grinding wheel to process the precision casting blank, welding a wear-resistant coating at a sawtooth working surface welding notch of the precision casting blank, and then grinding and polishing the precision casting blank, thereby avoiding the damage to an aluminized chromium layer during welding; after the precision casting blank is subjected to the aluminizing and chromizing treatment, the to-be-machined area which is not required to be subjected to the aluminizing and chromizing treatment on the precision casting blank is prevented from being removed in the subsequent machining process, and the situation that a shielding layer of the to-be-machined area which is not required to be subjected to the aluminizing and chromizing treatment leaks due to overhigh temperature in the aluminizing and chromizing treatment process is avoided; and finally, clamping and positioning the precision casting blank by adopting a six-point positioning method, grinding the tenon tooth by adopting a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank by taking the tenon tooth as a positioning reference so as to process the rest surfaces of the precision casting blank and obtain a finished turbine blade.
Description
Technical Field
The invention relates to the technical field of manufacturing of aeroengine parts, in particular to a machining method of a turbine blade. In addition, the invention also relates to a turbine blade verification method for the machining method of the turbine blade.
Background
The aeroengine power turbine blade is usually a shrouded blade, which is located behind an engine gas turbine and is not only subjected to complex mechanical load, but also subjected to oxidation and corrosion of high-temperature and high-pressure gas, so that coating a high-performance thermal diffusion aluminide coating on the blade body and the flow passage surface is one of the main methods for preventing gas corrosion of the advanced aeroengine power turbine blade.
Meanwhile, the working surfaces of the sawteeth of the blade shroud of the power turbine blade are matched with each other, the rotating speed of the turbine blade usually reaches more than 10000r/min in the running process of the engine, and the performance and the service life of the engine are reduced due to the fact that the working surfaces of the sawteeth are easily abraded mutually in high-speed running, so that the wear-resisting performance of the blade needs to be effectively improved by welding a layer of wear-resisting material on the working surfaces of the sawteeth of the blade shroud of the power turbine blade, and the performance and the service life of the engine are improved.
Currently, the following machining methods are generally adopted for the power turbine blade of the aero-engine: the method comprises the steps of adopting a precision casting blank, processing tenon teeth through six-point positioning, processing blade shroud sawtooth surface welding gaps by taking the tenon teeth as positioning reference, welding wear-resistant materials, polishing and grinding scars after welding, and processing the welded blade shroud sawtooth surfaces and the rest parts thereof through tenon tooth positioning. And after the processing is finished, performing surface coating treatment and inspection, and shielding and protecting machined surfaces (non-aluminized areas) which do not need aluminizing, such as blade tenons and edge plates, when aluminized coatings are prepared on blade bodies of the blades. The most common shielding method at present is methods such as adhesive tape sticking, ceramic protective cover and conventional coating, the use temperature of the shielding method is limited to about 950 ℃, however, along with the improvement of the performance requirement of the surface coating, the diffusion temperature of aluminide on the blade body surface is also improved, and the temperature of aluminized chromium of the blade body is 950-1050 ℃, so that the common shielding method is difficult to effectively protect the part to be protected, and the part performance is easy to cause unqualified parts and scrap in batches. The processing method comprises the following steps: in the blank stage, the whole blade is firstly aluminized and chromized, then the tenon tooth is positioned and processed at six points, and the processing of the rest parts is finished by taking the tenon tooth as the reference.
Disclosure of Invention
The invention provides a processing method and a calibration method of a turbine blade, which aim to solve the problems that if the blank of the existing turbine blade is welded with a wear-resistant material and then subjected to aluminum and chromium infiltration treatment, the turbine blade is difficult to shield without a machining surface subjected to the aluminum and chromium infiltration treatment, and parts are easy to damage, so that the performance of the turbine blade cannot reach the standard; if the alumetized chromium is firstly treated and then the wear-resistant material is welded, the alumetized chromium layer on the flow passage surface of the welding seam accessory is easy to damage in the welding process.
According to one aspect of the present invention, there is provided a method of machining a turbine blade, comprising the steps of: a. obtaining a precision casting blank of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then machining the precision casting blank by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working surface welding gap; b. welding a wear-resistant coating at the welding notch of the sawtooth working surface of the precision casting blank; c. grinding and polishing the precision casting blank; e. carrying out aluminizing and chromizing treatment on the precision casting blank, wherein the machining allowance of a to-be-machined area which is not required to be subjected to aluminizing and chromizing treatment on the precision casting blank is not less than 0.06 mm; f. obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then processing the precision casting blank by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth; g. and clamping and positioning the precision casting blank by using the tenon tooth as a positioning reference, and then processing the precision casting blank to obtain a finished turbine blade.
Further, the precision casting blank comprises a blade crown, a flange plate, a blade body and tenon teeth, wherein the side wall of the blade crown is provided with an E surface, an E ' surface, an F ' surface, a G ' surface, an H surface and an H ' surface, the two sides of the blade body are respectively provided with a blade back and a blade basin, the E surface, the F surface, the G surface and the H surface are arranged on the blade crown on one side of the blade back on the precision casting blank, the E ' surface, the F ' surface, the G ' surface and the H ' surface are arranged on the blade crown on one side of the blade basin on the precision casting blank, a sawtooth working surface welding notch on one side of the blade basin on the precision casting blank comprises the F surface and the H surface, a sawtooth working surface welding notch on one side of the blade back on the precision casting blank comprises the F ' surface and the H ' surface, the high-precision sawtooth machining grinding wheel is provided with four grinding surfaces which are arranged in one-to-one correspondence with the E surface, the F surface, the G surface and the H surface, the E ' surface are arranged in correspondence with the F surface, the G surface, the H' surface and the H surface are correspondingly arranged.
Further, the precision casting blank also comprises an X axis passing through the central point of the blade shroud and a Y axis passing through the central point of the blade shroud, wherein the X axis is respectively parallel to the E' plane and the E plane, the Y axis is vertical to the X axis, the distance between the E plane and the X axis is L1, the distance between the E plane and the F plane is L2, the included angle between the F plane and the E plane is less 1, the included angle between the H plane and the X axis is less 2, and the distance between the H plane and the M axis is L3; step a also includes the following steps: obtaining a calculation formula of the grinding amount of the high-precision sawtooth machining grinding wheel according to L1, L2, L3, angle 1 and angle 2 of the precision cast blank; the calculation formula is as follows: Δ L2 ═ Δ L1 ÷ cos × (2 × sin ×) 1, where Δ L1 is the grinding amount of the high-precision sawtooth machining grinding wheel pair E surface, Δ L2 is the grinding amount of the high-precision sawtooth machining grinding wheel pair F surface, and the grinding amount of the high-precision sawtooth machining grinding wheel is calculated according to a calculation formula.
Furthermore, the processing tolerance of the thickness of the wear-resistant coating is-0.2 mm-0, the processing tolerance of L2 is +/-0.03 mm, and the processing tolerance of L3 is +/-0.03 mm.
Further, the step a specifically comprises the following steps: 1, obtaining a precision casting blank of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then machining an E 'surface, an F' surface, a G 'surface and an H' surface of the precision casting blank by adopting four grinding surfaces of the high-precision sawtooth machining grinding wheel so as to obtain a sawtooth working surface welding notch on one side of a leaf basin; a2, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then processing the E surface, the F surface, the G surface and the H surface of the precision casting blank by adopting four grinding surfaces of a high-precision grinding wheel so as to obtain a sawtooth working surface welding notch on one side of the blade back.
Further, the six-point positioning method in step a1 specifically includes the following positioning points: a1, A2, A3, B4, B5 and C6, wherein A1 is arranged on a blade shroud on the blade back side, A2 and A3 are arranged on a flange plate on the blade back side, B4 is arranged on the blade shroud close to an air inlet edge, B5 is arranged on the flange plate close to the air inlet edge, and C6 is arranged on an inner runner surface of the flange plate.
Further, the six-point positioning method in step a2 specifically includes the following positioning points: a1 ', A2', A3 ', B4, B5 and C6, wherein A1' is arranged on the surface E ', A2' is arranged on the surface G ', A3' is arranged on the lightening groove of the edge plate on one side of the blade basin, B4 is arranged on the blade crown close to the air inlet edge, B5 is arranged on the edge plate close to the air inlet edge, and C6 is arranged on the inner runner surface of the edge plate.
Further, the six-point positioning method in step f specifically includes the following positioning points: a1 ', A2, A3, B4, B5 and C6, wherein A1 ' is arranged on a tip shroud on one side of a blade back, A2 and A3 are arranged on a flange plate on one side of the blade back, B4 is arranged on the tip shroud close to an air inlet edge, B5 is arranged on the flange plate close to the air inlet edge, C6 is arranged on an inner runner surface of the flange plate, the machining tolerance of the A1 ' is +/-0.03, and the position tolerance of a precision cast blank is +/-0.2.
Further, step a also includes the following steps: and obtaining a high-precision forming roller, and finishing the original sawtooth machining grinding wheel by adopting the high-precision forming roller to obtain the high-precision sawtooth machining grinding wheel, wherein the high-precision forming roller is provided with roller surfaces which are arranged in one-to-one correspondence with the grinding surfaces, and the profile accuracy range of the roller surfaces is 0-0.005.
According to another aspect of the invention, a turbine blade verification method is also provided, which is used for the turbine blade machining method, and comprises the following steps; obtaining a precision casting blank of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then machining the precision casting blank by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working surface welding gap; grinding and polishing the precision casting blank; carrying out aluminizing and chromizing treatment on the precision casting blank; obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank by adopting a six-point positioning method, and then processing the precision casting blank by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth; clamping and positioning the precision casting blank by using the tenon tooth as a positioning reference, and then processing the precision casting blank to obtain a turbine blade test piece; and carrying out benchmark conversion error check on the finished turbine blade product by adopting the turbine blade test piece.
The invention has the following beneficial effects:
the machining method of the turbine blade comprises the steps of firstly adopting a six-point positioning method to clamp and position a precision casting blank, ensuring reliable positioning and high machining precision, machining the precision casting blank by adopting a high-precision sawtooth machining grinding wheel to machine a sawtooth working surface welding notch for welding a wear-resistant coating, ensuring the machining precision in the machining process by the high-precision sawtooth machining grinding wheel, avoiding excessive grinding allowance, welding the wear-resistant coating at the sawtooth working surface welding notch of the precision casting blank, improving the wear-resistant performance of the turbine blade, and grinding and polishing the precision casting blank to remove craters; after the refined cast blank is subjected to the process of aluminizing and chromizing, the machining allowance of the area to be machined, which is not required to be subjected to the aluminizing and chromizing treatment, on the refined cast blank is not less than 0.06mm, because the thickness of the aluminizing and chromizing layer is 0.03-0.06mm, and the machining allowance is not less than 0.06mm, the area to be machined, which is not required to be subjected to the aluminizing and chromizing treatment, on the refined cast blank is prevented from being removed in the subsequent machining process, and compared with the prior art, the risk that the turbine blade is scrapped due to the fact that a shielding layer of the area to be machined, which is not required to be subjected to the aluminizing and chromizing treatment, leaks due to overhigh temperature in the aluminizing and chromizing treatment process is avoided; finally, clamping and positioning the precision casting blank by adopting a six-point positioning method, wherein the positioning is reliable, the processing precision is high, tenon teeth are ground by adopting a tenon tooth processing grinding wheel, and then the precision casting blank is clamped and positioned by taking the tenon teeth as a positioning reference so as to process the rest surfaces of the precision casting blank to obtain a turbine blade finished product; the turbine blade's of this scheme processing adopts earlier to weld wear-resistant coating and when carrying out the processing of aluminizing chromium again, need not to ooze the processing allowance in the regional of treating that the aluminizing chromium was handled on the precision casting blank when guaranteeing to ooze the processing of aluminizing chromium not less than 0.06mm to destroy the risk of part when destroying the aluminizing chromium layer or aluminizing chromium and handling when avoiding welding, and then improved the machining capacity and the processingquality of shrouded turbine blade.
In addition to the objects, features and advantages described above, other objects, features and advantages of the present invention are also provided. The present invention will be described in further detail below with reference to the drawings.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this application, illustrate embodiments of the invention and, together with the description, serve to explain the invention and not to limit the invention. In the drawings:
FIG. 1 is a block diagram of the steps of a method of machining a turbine blade in accordance with a preferred embodiment of the present invention;
FIG. 2 is a schematic structural diagram of the turbine blade after the precision casting blank is clamped and positioned in step f of the machining method of the turbine blade according to the preferred embodiment of the invention;
FIG. 3 is a schematic structural view of a fine cast blank in the method of manufacturing a turbine blade according to the preferred embodiment of the present invention;
FIG. 4 is a schematic structural view of a fine cast blank in the method of manufacturing a turbine blade according to the preferred embodiment of the present invention;
fig. 5 is a schematic structural view of a fine cast blank in the method of manufacturing a turbine blade according to the preferred embodiment of the present invention.
Illustration of the drawings:
100. fine casting a blank; 110. a leaf shroud; 111. welding gaps on the sawtooth working surface; 120. a flange plate; 130. a leaf body; 131. leaf basin; 140. tenon tooth.
Detailed Description
The embodiments of the invention will be described in detail below with reference to the accompanying drawings, but the invention can be embodied in many different forms, which are defined and covered by the following description.
FIG. 1 is a block diagram of the steps of a method of machining a turbine blade in accordance with a preferred embodiment of the present invention; FIG. 2 is a schematic structural view of a precision cast blank in step f of the method of machining a turbine blade according to the preferred embodiment of the present invention; FIG. 3 is a schematic structural view of a turbine blade according to a preferred embodiment of the present invention after a precision cast blank is clamped and positioned; FIG. 4 is a schematic structural view of a fine cast blank in the method of manufacturing a turbine blade according to the preferred embodiment of the present invention; fig. 5 is a schematic structural view of a fine cast blank in the method of manufacturing a turbine blade according to the preferred embodiment of the present invention.
As shown in fig. 1 to 5, the method for machining a turbine blade of the present embodiment includes the following steps: a. obtaining a precision casting blank 100 of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then machining the precision casting blank 100 by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working face welding notch 111; b. welding a wear-resistant coating at a welding notch 111 of the sawtooth working surface of the precision casting blank 100; c. grinding and polishing the precision casting blank 100; e. carrying out aluminizing and chromizing treatment on the precision casting blank 100, wherein the machining allowance of a to-be-machined area which is not required to be subjected to the aluminizing and chromizing treatment on the precision casting blank 100 is not less than 0.06 mm; f. obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then processing the precision casting blank 100 by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth 140; g. and clamping and positioning the precision casting blank 100 by taking the tenon teeth 140 as a positioning reference, and then processing the precision casting blank 100 to obtain a finished turbine blade. Specifically, the processing method of the turbine blade of the invention, adopt six-point positioning method to clamp and position the precision casting blank 100 at first, the location is reliable, the machining precision is high, adopt the high-accuracy sawtooth to process the precision casting blank 100 and process the grinding wheel of the high-accuracy sawtooth, in order to process the sawtooth working face welding gap 111 used for welding the wear-resisting coating, the high-accuracy sawtooth processes the grinding wheel and guarantees the machining precision in the course of processing, avoid grinding the excessive machining allowance, weld the wear-resisting coating in the sawtooth working face welding gap 111 of the precision casting blank 100, improve the wear-resisting property of the turbine blade, polish and polish the precision casting blank 100, in order to remove the weld scar, compared with prior art, finish the welding of the wear-resisting coating before the chromizing, has avoided the destruction to the chromizing while welding; after the refined cast blank 100 is subjected to the process of alumetizing and chromizing, the machining allowance of the to-be-machined area which is not required to be subjected to alumetizing and chromizing on the refined cast blank 100 is not less than 0.06mm, because the thickness of the alumetizing chromium layer is 0.03-0.06mm and the machining allowance is not less than 0.06mm, the to-be-machined area which is not required to be subjected to alumetizing and chromizing on the refined cast blank 100 is prevented from being removed in the subsequent machining process, and compared with the prior art, the risk that the turbine blade is scrapped due to the fact that a shielding layer of the to-be-machined area which is not required to be subjected to alumetizing and chromizing is leaked due to overhigh temperature in the alumetizing and chromizing process is avoided; finally, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, the positioning is reliable, the processing precision is high, the tenon tooth 140 is ground by adopting a tenon tooth processing grinding wheel, and then the precision casting blank 100 is clamped and positioned by taking the tenon tooth 140 as a positioning reference so as to process the rest surfaces of the precision casting blank 100 and obtain a turbine blade finished product; the turbine blade's of this scheme processing adopts earlier to weld wear-resistant coating and when carrying out the processing of aluminizing chromium again, need not to ooze the processing allowance in the regional of treating that the aluminizing chromium was handled on the precision casting blank 100 when guaranteeing to ooze the processing of aluminizing chromium not less than 0.06mm to destroy the risk of part when destroying the aluminizing chromium layer or aluminizing chromium and handling when avoiding welding, and then improved shrouded turbine blade's throughput and processingquality. It should be understood that a high precision serrated grinding wheel is generally understood to have a grinding face profile of less than 0.005 to also ensure the relative positional relationship of the machined faces of the precision cast blank when machining the precision cast blank.
As shown in fig. 3, in the present embodiment, the fine cast blank 100 includes a tip shroud 110, a rim plate 120, a blade body 130, and a tenon 140, an E face, an E 'face, an F' face, a G 'face, an H face, and an H' face are provided on a side wall of the tip shroud 110, a blade back and a blade basin 131 are respectively provided on both sides of the blade body 130, the E face, the F face, the G face, and the H face are provided on the tip shroud 110 on the blade back side of the fine cast blank 100, the E 'face, the F' face, the G 'face, and the H' face are provided on the tip shroud 110 on the blade basin 131 side of the fine cast blank 100, a serration working face welding notch 111 on the blade basin 131 side of the fine cast blank 100 includes an F face and an H face, the serration working face welding notch 111 on the blade back side of the fine cast blank 100 includes an F 'face and an H' face, the high precision serration grinding wheel is provided with four grinding faces provided corresponding to the E face, the F face, the G face, and the H face one-to one, the F ' surface and the F surface are correspondingly arranged, the G ' surface and the G surface are correspondingly arranged, and the H ' surface and the H surface are correspondingly arranged. Specifically, the E surface, the F surface, the G surface and the H surface of the sawtooth on the blade crown 110 are processed at one time through four grinding surfaces of the high-precision sawtooth machining grinding wheel, or the E 'surface, the F' surface, the G 'surface and the H' surface of the sawtooth on the blade crown 110 are processed at one time, the relative position relation of the four grinding surfaces of the high-precision sawtooth machining grinding wheel is determined, so that the relative position relation between the surfaces of the sawtooth on the blade crown 110 is ensured, the machining precision is improved, meanwhile, the measurement and the inspection of the machined size are facilitated, and the product qualification rate is ensured. It should be understood that, since the serration working face welding notch 111 on the side of the vane basin 131 of the fine cast blank 100 includes the F-face and the H-face and the serration working face welding notch 111 on the side of the vane back of the fine cast blank 100 includes the F ' -face and the H ' -face, the position and depth of the serration working face welding notch 111 on the side of the vane basin 131 are controlled by the grinding amount of the F-face, and the position and depth of the serration working face welding notch 111 on the side of the vane back are controlled by the grinding amount of the F ' -face.
As shown in fig. 3, in this embodiment, the fine cast blank 100 further includes an X axis passing through a central point of the blade shroud 110 and a Y axis passing through a central point of the blade shroud 110, the X axis is respectively parallel to the E' plane and the E plane, the Y axis is perpendicular to the X axis, a distance between the E plane and the X axis is L1, a distance between the E plane and the F plane is L2, an included angle between the F plane and the E plane is less 1, an included angle between the H plane and the X axis is less 2, and a distance between the H plane and the M axis is L3; step a also includes the following steps: obtaining a calculation formula of the grinding amount of the high-precision sawtooth machining grinding wheel according to L1, L2, L3, angle 1 and angle 2 of the precision cast blank 100; the calculation formula is as follows: Δ L2 ═ Δ L1 ÷ cos × (2 × sin ×) 1, where Δ L1 is the grinding amount of the high-precision sawtooth machining grinding wheel pair E surface, Δ L2 is the grinding amount of the high-precision sawtooth machining grinding wheel pair F surface, and the grinding amount of the high-precision sawtooth machining grinding wheel is calculated according to a calculation formula. Specifically, Δ L2 affects the position and depth of the machined sawtooth working face welding notch 111, and needs to be controlled during high-precision sawtooth machining of the grinding wheel, and since the distance between the E face and the F face is affected by the circular arc at the bottom of the sawtooth notch, the measurement is inconvenient, and as can be known from the relative position relationship between each face and the shaft on the precision cast blank 100, Δ L2 ═ Δ L1 ÷ cos 2 × sin ═ 1, that is, Δ L2 can be converted from Δ L1, and Δ L1 measurement is convenient (for example, measurement is performed by three-coordinate six-point fitting or a special measuring tool), therefore, the precision cast blank 100 is subjected to high-precision sawtooth machining of the grinding wheel to ensure the relative position relationship between each face and the shaft on the precision cast blank 100, and Δ L2 which is difficult to measure is converted into Δ L1 which is convenient to measure, thereby realizing the control of the depth and the position of the sawtooth working face welding notch 111. It should be understood that when the high-precision sawtooth machining grinding wheel grinds, enough machining allowance is reserved on each surface of the sawtooth, so that enough machining allowance is reserved after the wear-resistant coating is welded, and the risk of damaging parts during aluminizing and chromizing is avoided.
In the present embodiment, as shown in fig. 3-4, the machining tolerance of the wear-resistant coating thickness is-0.2 mm-0, the machining tolerance of L2 is ± 0.03mm, and the machining tolerance of L3 is ± 0.03 mm. Specifically, when the fine casting blank 100 is processed by welding the notch 111 on the working face of the sawtooth, the positioning datum is six positioning points on the fine casting blank 100 in the step a, and each working face of the sawtooth is subjected to aluminizing and chromizing treatment in the step f and needs to be ground and removed, at this time, the positioning datum is the tenon tooth 140, and the sawtooth generates datum transformation in the two processing processes, so that enough datum transformation error is reserved for the datum transformation of the sawtooth by ensuring that the processing tolerance of the thickness of the wear-resistant coating is-0.2 mm-0, the processing tolerance of the L2 is +/-0.03 mm, and the processing tolerance of the L3 is +/-0.03 mm, so that the processing precision after the sawtooth processing is ensured, and the datum transformation error control of the sawtooth in the two processing processes is realized.
As shown in fig. 3, in this embodiment, step a specifically includes the following steps: a1, obtaining a precision casting blank 100 of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then machining an E 'surface, an F' surface, a G 'surface and an H' surface of the precision casting blank 100 by adopting four grinding surfaces of the high-precision sawtooth machining grinding wheel so as to obtain a sawtooth working surface welding notch 111 on one side of the blade basin 131; a2, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then processing the E surface, the F surface, the G surface and the H surface of the precision casting blank 100 by adopting four grinding surfaces of a high-precision grinding wheel so as to obtain a sawtooth working surface welding notch 111 on one side of the blade back. Specifically, in the step a1, firstly, a six-point positioning method is adopted to clamp and position the precision casting blank 100, then four grinding surfaces of the high-precision sawtooth machining grinding wheel are adopted to machine the E 'surface, the F' surface, the G 'surface and the H' surface of the precision casting blank 100, so that the machining precision is improved, the machining quality is ensured, meanwhile, the relative position relation among the surfaces on one side of the sawtooth blade basin 131 on the blade crown 110 is ensured, the control on the position and the depth of the sawtooth working surface welding notch 111 on one side of the blade basin 131 is realized, and the part is ensured to be qualified; in the step a2, the precision casting blank 100 is clamped and positioned by a six-point positioning method, and then the E surface, the F surface, the G surface and the H surface of the precision casting blank 100 are machined by four grinding surfaces of the high-precision sawtooth machining grinding wheel, so that the machining precision is improved, the machining quality is ensured, and meanwhile, the relative position relation between the surfaces of the sawtooth blade basin 131 on the blade crown 110 is ensured, so that the control of the position and the depth of the sawtooth working surface welding notch 111 on the blade basin 131 side is realized, and the part is qualified. It should be understood that in other embodiments, the serrated face weld notch 111 on the blade basin 131 side of the blade shroud 110 may be machined first, and then the serrated face weld notch 111 on the blade back side of the blade shroud 110 may be machined.
As shown in fig. 5, in the present embodiment, the six-point positioning method in step a1 specifically includes the following positioning points: a1, A2, A3, B4, B5 and C6, wherein A1 is arranged on the blade shroud 110 on the blade back side, A2 and A3 are arranged on the edge plate 120 on the blade back side, B4 is arranged on the blade shroud 110 close to the air inlet edge, B5 is arranged on the edge plate 120 close to the air inlet edge, and C6 is arranged on the inner runner surface of the edge plate 120. Specifically, a1, a2 and A3 are uniformly distributed on one side of the blade back to form a same plane, so that partial limiting of the precision-cast blank 100 is realized, and the complete limiting of the precision-cast blank 100 is realized through B4, B5 and C6, so that the processing precision is improved, and the processing quality is ensured.
As shown in fig. 5, in the present embodiment, the six-point positioning method in step a2 specifically includes the following positioning points: a1 ', a 2', A3 ', B4, B5 and C6, wherein a 1' is arranged on the E 'surface, a 2' is arranged on the G 'surface, A3' is arranged on the lightening groove of the flange 120 at one side of the blade basin 131, B4 is arranged on the shroud 110 close to the air inlet edge, B5 is arranged on the flange 120 close to the air inlet edge, and C6 is arranged on the inner runner surface of the flange 120. It should be understood that, when the welding notch 111 of the sawtooth working face on the side of the blade basin 131 on the blade shroud 110 is machined in step a2, a1, a2 and A3 in step a1 are located on the same side of the blade as the face to be machined, which results in difficulty in positioning and clamping the blade, and easily interferes with the machining position, which results in failure of machining, therefore, 3 positioning accuracies such as a1, a2 and A3 are no longer applicable, and need to perform reference transformation to reselect the positioning points, while the E ' face and the G ' face in step a1 have been primarily machined to form a more accurate machining face, a1 ' can be arranged on the E ' face, a2 ' can be arranged on the G ' face to ensure the machining accuracy, and if A3 ' adopts a point near the blade shroud 110 as the positioning point, the influence of machining tolerance of the cast blank 100 is fertilized, the influence on the welding notch 111 of the sawtooth working face is great, and in order to reduce the influence of the machining tolerance of the cast blank 100 on the machining, the A3 'is arranged on the lightening groove of the flange plate 120 on one side of the blade basin 131, where the distance to be processed is L4 (48 mm in the embodiment), and the processing tolerance (plus or minus 0.15mm in the embodiment) of the fine cast blank 100 is much smaller than L4, and tan α is T/L (T is the processing tolerance of the fine cast blank 100) obtained from the position relation of the fine cast blank 100, and the influence of the A3' positioning point on the blade clamping swing angle is calculated to be about 0.006 °, so as to ensure that the reference conversion error is controllable, and the processing precision is high.
As shown in fig. 5, in this embodiment, the six-point positioning method in step f specifically includes the following positioning points: a1 ', A2, A3, B4, B5 and C6, wherein A1 ' is arranged on the blade shroud 110 at the blade back side, A2 and A3 are arranged on the edge plate 120 at the blade back side, B4 is arranged on the blade shroud 110 close to the air inlet edge, B5 is arranged on the edge plate 120 close to the air inlet edge, C6 is arranged on the inner runner surface of the edge plate 120, the machining tolerance of the A1 ' is +/-0.03, and the position tolerance of the precision cast blank 100 is +/-0.2.
In this embodiment, step a further includes, before step a: and obtaining a high-precision forming roller, and finishing the original sawtooth machining grinding wheel by adopting the high-precision forming roller to obtain the high-precision sawtooth machining grinding wheel, wherein the high-precision forming roller is provided with roller surfaces which are arranged in one-to-one correspondence with the grinding surfaces, and the profile accuracy range of the roller surfaces is 0-0.005. Specifically, the original sawtooth machining grinding wheel is dressed through the high-precision forming roller, so that the high-precision sawtooth machining grinding wheel is obtained, the profile precision range of the roller surface of the high-precision forming roller is 0-0.005, the machining precision of the high-precision sawtooth machining grinding wheel is further ensured, and the relative position relation of each surface on the precision casting blank 100 is further ensured.
The turbine blade verification method of the embodiment is used for the turbine blade machining method and comprises the following steps; obtaining a precision casting blank 100 of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then machining the precision casting blank 100 by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working face welding notch 111; grinding and polishing the precision casting blank 100; carrying out aluminum and chromium infiltration treatment on the precision casting blank 100; obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank 100 by adopting a six-point positioning method, and then processing the precision casting blank 100 by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth 140; clamping and positioning the precision casting blank 100 by using the tenon teeth 140 as a positioning reference, and then processing the precision casting blank 100 to obtain a turbine blade test piece; and carrying out benchmark conversion error check on the finished turbine blade product by adopting the turbine blade test piece. Specifically, the turbine blade test piece is obtained first, and since the turbine blade test piece is not welded with the wear-resistant coating, the sawtooth working face welding notch 111 can be enlarged and measured by using a measuring tool (such as a microscope), and then compared with the finished turbine blade product to obtain the thickness of the L1 and the wear-resistant coating, and further the sawtooth reference conversion error is verified, so that the product is determined to be qualified.
The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention, and various modifications and changes may be made by those skilled in the art. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A method of machining a turbine blade, comprising the steps of:
a. obtaining a precision casting blank (100) of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then machining the precision casting blank (100) by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working face welding notch (111);
b. welding a wear-resistant coating at a welding notch (111) of a sawtooth working surface of the precision casting blank (100);
c. grinding and polishing the precision casting blank (100);
e. carrying out aluminizing and chromizing treatment on the precision casting blank (100), wherein the machining allowance of a to-be-machined area which is not required to be subjected to the aluminizing and chromizing treatment on the precision casting blank (100) is not less than 0.06 mm;
f. obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then processing the precision casting blank (100) by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth (140);
g. and clamping and positioning the precision casting blank (100) by taking the tenon tooth (140) as a positioning reference, and then processing the precision casting blank (100) to obtain a finished turbine blade.
2. The method for machining a turbine blade as claimed in claim 1, wherein the precisely cast blank (100) comprises a tip shroud (110), a flange plate (120), a blade body (130) and a tenon tooth (140), the side wall of the tip shroud (110) is provided with an E surface, an E ' surface, an F ' surface, a G ' surface, an H surface and an H ' surface, two sides of the blade body (130) are respectively provided with a blade back and a blade basin (131), the E surface, the F surface, the G surface and the H surface are arranged on the tip shroud (110) on the blade back side of the precisely cast blank (100), the E ' surface, the F ' surface, the G ' surface and the H ' surface are arranged on the tip shroud (110) on the blade basin (131) side of the precisely cast blank (100), the sawtooth working surface welding notch (111) on the blade basin (131) side of the precisely cast blank (100) comprises the F surface and the H surface, the sawtooth working surface welding notch (111) on the blade back side of the precisely cast blank (100) comprises the F ' surface and the H surface, the high-precision sawtooth machining grinding wheel is provided with four grinding surfaces which are arranged in one-to-one correspondence with an E surface, an F surface, a G surface and an H surface, wherein the E 'surface is arranged corresponding to the E surface, the F' surface is arranged corresponding to the F surface, the G 'surface is arranged corresponding to the G surface, and the H' surface is arranged corresponding to the H surface.
3. The machining method of the turbine blade as claimed in claim 2, characterized in that the fine cast blank (100) further comprises an X axis passing through the center point of the blade shroud (110) and a Y axis passing through the center point of the blade shroud (110), wherein the X axis is respectively parallel to the E' plane and the E plane, the Y axis is perpendicular to the X axis, the distance between the E plane and the X axis is L1, the distance between the E plane and the F plane is L2, the included angle between the F plane and the E plane is ^ 1, the included angle between the H plane and the X axis is ^ 2, and the distance between the H plane and the M axis is L3;
step a also includes the following steps: obtaining a calculation formula of the grinding amount of the high-precision sawtooth machining grinding wheel according to L1, L2, L3, angle 1 and angle 2 of a precision cast blank (100);
the calculation formula is as follows: Δ L2 ═ Δ L1 ÷ cos × (2 × sin ×) 1, where Δ L1 is the grinding amount of the high-precision sawtooth machining grinding wheel pair E surface, Δ L2 is the grinding amount of the high-precision sawtooth machining grinding wheel pair F surface, and the grinding amount of the high-precision sawtooth machining grinding wheel is calculated according to a calculation formula.
4. The method for machining a turbine blade as claimed in claim 3, wherein the machining tolerance of the wear resistant coating thickness is-0.2 mm-0, the machining tolerance of L2 is ± 0.03mm, and the machining tolerance of L3 is ± 0.03 mm.
5. The method for machining a turbine blade as claimed in claim 2, wherein the step a comprises the steps of:
a1, obtaining a high-precision sawtooth machining grinding wheel and a precision casting blank (100) of a turbine blade, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then machining an E 'surface, an F' surface, a G 'surface and an H' surface of the precision casting blank (100) by adopting four grinding surfaces of the high-precision sawtooth machining grinding wheel so as to obtain a sawtooth working surface welding notch (111) on one side of a blade basin (131);
a2, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then processing the E surface, the F surface, the G surface and the H surface of the precision casting blank (100) by adopting four grinding surfaces of a high-precision grinding wheel so as to obtain a sawtooth working surface welding notch (111) on one side of the blade back.
6. The method for machining a turbine blade as claimed in claim 5, wherein the six-point positioning method in the step a1 specifically comprises the following positioning points: a1, A2, A3, B4, B5 and C6, wherein A1 is arranged on a blade shroud (110) on the blade back side, A2 and A3 are arranged on a flange plate (120) on the blade back side, B4 is arranged on the blade shroud (110) close to an air inlet edge, B5 is arranged on the flange plate (120) close to the air inlet edge, and C6 is arranged on an inner runner surface of the flange plate (120).
7. The method for machining a turbine blade as claimed in claim 5, wherein the six-point positioning method in the step a2 specifically comprises the following positioning points: a1 ', A2', A3 ', B4, B5 and C6, wherein A1' is arranged on the surface E ', A2' is arranged on the surface G ', A3' is arranged on the lightening groove of the edge plate (120) on one side of the blade basin (131), B4 is arranged on the blade crown (110) close to the air inlet edge, B5 is arranged on the edge plate (120) close to the air inlet edge, and C6 is arranged on the inner runner surface of the edge plate (120).
8. The method for machining a turbine blade as claimed in any one of claims 1 to 7, wherein the six-point positioning method in step f specifically comprises the following positioning points: a1 ', A2, A3, B4, B5 and C6, wherein A1 ' is arranged on a blade shroud (110) on the blade back side, A2 and A3 are arranged on a flange plate (120) on the blade back side, B4 is arranged on the blade shroud (110) close to an air inlet edge, B5 is arranged on the flange plate (120) close to the air inlet edge, C6 is arranged on an inner runner surface of the flange plate (120), the machining tolerance of the A1 ' is +/-0.03, and the position tolerance of the precision casting blank (100) is +/-0.2.
9. The method for machining a turbine blade as claimed in any one of claims 1 to 7, wherein step a is preceded by the step of: and obtaining a high-precision forming roller, and finishing the original sawtooth machining grinding wheel by adopting the high-precision forming roller to obtain the high-precision sawtooth machining grinding wheel, wherein the high-precision forming roller is provided with roller surfaces which are arranged in one-to-one correspondence with the grinding surfaces, and the profile accuracy range of the roller surfaces is 0-0.005.
10. A turbine blade verification method, which is used in the turbine blade machining method according to any one of claims 1 to 9, comprising the steps of;
obtaining a precision casting blank (100) of a high-precision sawtooth machining grinding wheel and a turbine blade, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then machining the precision casting blank (100) by adopting the high-precision sawtooth machining grinding wheel to obtain a sawtooth working face welding notch (111);
grinding and polishing the precision casting blank (100);
carrying out aluminizing and chromizing treatment on the precision casting blank (100);
obtaining a tenon tooth processing grinding wheel, clamping and positioning the precision casting blank (100) by adopting a six-point positioning method, and then processing the precision casting blank (100) by adopting the tenon tooth processing grinding wheel to obtain a tenon tooth (140);
clamping and positioning the precision casting blank (100) by using the tenon tooth (140) as a positioning reference, and then processing the precision casting blank (100) to obtain a turbine blade test piece;
and carrying out benchmark conversion error check on the finished turbine blade product by adopting the turbine blade test piece.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB664614A (en) * | 1949-03-28 | 1952-01-09 | Bristol Aeroplane Co Ltd | Improvements in or relating to a method of fabricating hollow blades for turbines, compressors or the like |
| US4176433A (en) * | 1978-06-29 | 1979-12-04 | United Technologies Corporation | Method of remanufacturing turbine vane clusters for gas turbine engines |
| US4185369A (en) * | 1978-03-22 | 1980-01-29 | General Electric Company | Method of manufacture of cooled turbine or compressor buckets |
| CN102107314A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for overlaying wear-resistant layer of blade shroud of turbine working blade |
| CN104439617A (en) * | 2014-10-27 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Turbine blade sawtooth shroud wear-proof layer preparation method |
| US20150322804A1 (en) * | 2012-05-09 | 2015-11-12 | Siemens Aktiengesellschaft | Airfoil arrangement with ptal bond coating and thermal barrier coating, and corresponding manufacturing method |
| CN105436839A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Manufacturing method of titanium alloy wide-chord hollow fan blade of aeroengine |
| CN110551970A (en) * | 2019-09-29 | 2019-12-10 | 中国人民解放军空军工程大学 | Compressor blade partition protective coating and preparation method thereof |
| CN113005417A (en) * | 2021-03-10 | 2021-06-22 | 广东省科学院新材料研究所 | Turbine moving blade of aircraft engine, method for prolonging service life of turbine moving blade and application of turbine moving blade |
-
2021
- 2021-12-08 CN CN202111512244.4A patent/CN114043183B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB664614A (en) * | 1949-03-28 | 1952-01-09 | Bristol Aeroplane Co Ltd | Improvements in or relating to a method of fabricating hollow blades for turbines, compressors or the like |
| US4185369A (en) * | 1978-03-22 | 1980-01-29 | General Electric Company | Method of manufacture of cooled turbine or compressor buckets |
| US4176433A (en) * | 1978-06-29 | 1979-12-04 | United Technologies Corporation | Method of remanufacturing turbine vane clusters for gas turbine engines |
| CN102107314A (en) * | 2009-12-23 | 2011-06-29 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for overlaying wear-resistant layer of blade shroud of turbine working blade |
| US20150322804A1 (en) * | 2012-05-09 | 2015-11-12 | Siemens Aktiengesellschaft | Airfoil arrangement with ptal bond coating and thermal barrier coating, and corresponding manufacturing method |
| CN104439617A (en) * | 2014-10-27 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Turbine blade sawtooth shroud wear-proof layer preparation method |
| CN105436839A (en) * | 2015-12-16 | 2016-03-30 | 西北工业大学 | Manufacturing method of titanium alloy wide-chord hollow fan blade of aeroengine |
| CN110551970A (en) * | 2019-09-29 | 2019-12-10 | 中国人民解放军空军工程大学 | Compressor blade partition protective coating and preparation method thereof |
| CN113005417A (en) * | 2021-03-10 | 2021-06-22 | 广东省科学院新材料研究所 | Turbine moving blade of aircraft engine, method for prolonging service life of turbine moving blade and application of turbine moving blade |
Non-Patent Citations (1)
| Title |
|---|
| 张杰等: "先进的燃气轮机叶片粉末冶金修复技术", 《材料导报》 * |
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