CN115502671B - Machining method, guide and turbine - Google Patents
Machining method, guide and turbine Download PDFInfo
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- CN115502671B CN115502671B CN202211324059.7A CN202211324059A CN115502671B CN 115502671 B CN115502671 B CN 115502671B CN 202211324059 A CN202211324059 A CN 202211324059A CN 115502671 B CN115502671 B CN 115502671B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
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Abstract
The invention belongs to the technical field of aeroengine manufacturing, and discloses a machining method, a guide and a turbine, wherein the machining method is used for machining the guide and comprises the following steps of: s100, selecting three guide blades which are equidistantly and alternately surrounded on the outer wall of the inner ring at the air inlet end of the guide, acquiring the highest point of the air inlet side of each guide blade, taking the plane of the highest point of the three guide blades as a first reference plane, selecting more than three positioning points which are equidistantly and alternately surrounded on the inner wall of the outer ring at the air outlet end of the guide, and taking the planes of all the positioning points as a second reference plane; s200, taking the first datum plane as an axial machining datum, machining a first allowance part on the guide along the axial direction, and taking the second datum plane as a radial machining datum, and machining a second allowance part on the guide along the radial direction. The invention selects the positioning reference with higher precision, improves the machining precision of the guide, and ensures that the guide can meet the requirement of manufacturing precision.
Description
Technical Field
The invention relates to the technical field of aeroengine manufacturing, in particular to a processing method, a guide and a turbine.
Background
The turbine is one of the main components of an aeroengine, is an impeller machine for converting the capability of high-temperature and high-pressure fuel gas into kinetic and mechanical energy, and comprises a stator part and a rotor part, wherein the stator part is also called a director, and the director is an annular static blade grid formed by an outer ring, an inner ring and a group of guide blades. The working condition of the guide device is very harsh, for example, the guide device is in high-temperature gas flow, the working temperature is high, the guide device is in direct contact with gas, the guide device is easy to oxidize and corrode, the working temperature fields of all parts of the guide device are different, the guide device is heated unevenly and has uneven thickness, so that the guide device has great thermal stress, and along with the starting, stopping, accelerating and decelerating of an aeroengine, the guide device works in a cold-hot alternating state, the guide blade is easy to generate thermal fatigue, and fatigue cracks are easy to generate at the front edge and the rear edge of the guide blade, so the manufacturing process requirement of the guide device is very harsh.
At present, a guide blank is an integral precision casting part, the blade profile of a blade, the runner surface of an inner ring and the runner surface of an outer ring are directly cast and molded, machining parts of the guide blank are mainly concentrated at positions outside the runner surface of the inner ring and positions outside the runner surface of the outer ring, in the existing machining technology, positioning references which are axially machined outside the end surface of a mounting edge are generally selected for machining the guide, but the position of the mounting edge is mostly a allowance position, the size is large, the position is a casting head position, the size precision and the flatness are poor, the end surface is used as the machining reference, large deviation occurs in machining sizes of other areas, and the shape and position tolerance of the machined end surface of the blade and the machined reference of the runner surface are out of tolerance.
Therefore, a processing method, a guide and a turbine are needed, a positioning reference with higher precision is selected, the processing precision of the guide is improved, and the guide can meet the manufacturing precision requirement.
Disclosure of Invention
One object of the present invention is to: the machining method, the guide and the turbine are provided, the positioning reference with higher precision is selected, the machining precision of the guide is improved, and the guide can meet the manufacturing precision requirement.
To achieve the purpose, the invention adopts the following technical scheme:
in a first aspect, a machining method is provided for machining a guide, the machining method comprising the steps of:
s100, selecting three guide blades which are equidistantly arranged around the outer wall of an inner ring at the air inlet end of the guide device, and obtaining the highest point of the air inlet side of each guide blade, wherein the highest point is the intersection point of an equal-inclination curve of the air inlet side of the guide blade and a pitch circle of the guide blade, the pitch circle is determined by the distance from the middle position of the guide blade to the center of the inner ring, the plane where the highest point of the three guide blades is located is used as a first reference plane, and the air outlet end of the guide device is provided with more than three positioning points which are equidistantly arranged around the inner wall of the outer ring, and the planes where all the positioning points are located are used as second reference planes;
s200, using the first reference surface as an axial machining reference, machining a first allowance part on the guide in the axial direction, and using a second reference surface as a radial machining reference, and machining a second allowance part on the guide in the radial direction.
As an optional solution, the step S200 includes the following steps:
s201, adopting a three-jaw chuck to internally support the second reference surface, enabling the three-jaw chuck to be attached to the end surface of the exhaust end, detecting radial runout of the pitch circle and radial runout of outer walls at two ends of the outer ring through a dial indicator, and if the radial runout of the pitch circle and the radial runout of the outer walls at two ends of the outer ring are within preset ranges, carrying out rough machining on the second allowance part of the air inlet end.
As an optional technical solution, after the step S201, the method further includes the following steps:
s202, adopting a fixed block to internally support the outer ring to be positioned on the inner wall of the air inlet end and adopting the three-jaw chuck to clamp the outer ring to be positioned on the outer wall of the air inlet end, enabling the three-jaw chuck to be attached to the end face of the air inlet end, detecting radial runout of the inner ring positioned on the outer wall of the air outlet end through the dial indicator, and if the radial runout of the inner ring positioned on the outer wall of the air outlet end is in a preset range, carrying out rough machining on the first allowance part of the air outlet end.
As an optional technical solution, after the step S202, the method further includes the following steps:
s203, supporting the inner wall of the outer ring at the exhaust end by adopting the fixing block, clamping the outer ring at the outer wall of the exhaust end by adopting the three-jaw chuck, attaching the three-jaw chuck to the end face of the exhaust end, and carrying out finish machining on the second allowance part of the air inlet end, so that the distance from the end face of the outer ring at the air inlet end to the first reference surface is h1.
As an optional technical solution, after the step S203, the method further includes the following steps:
s204, supporting the inner wall of the outer ring at the air inlet end by adopting the fixing block, clamping the outer wall of the outer ring at the air inlet end by adopting the three-jaw chuck, attaching the three-jaw chuck to the end face of the air inlet end, and carrying out finish machining on the first allowance part of the air outlet end so that the distance from the end face of the outer ring at the air outlet end to the first reference surface is h2.
As an optional technical solution, after the step S200, the method further includes the following steps:
and S300, processing the stress groove of the guide by taking the exhaust end as a positioning end.
As an optional technical solution, after the step S300, the method further includes the following steps:
s400, deburring the guide and cleaning pollutants on the surface of the guide.
As an optional technical solution, after the step S400, the method further includes the following steps:
s500, visually inspecting the surface quality of the guide, detecting the size and the surface roughness of the guide, and detecting the surface defect of the guide.
In a second aspect, there is provided a guide made by the process described above.
In a third aspect, there is provided a turbine comprising a guide as described above.
The invention has the beneficial effects that:
the invention provides a processing method, a guide and a turbine, wherein the guide is manufactured by the processing method, the turbine comprises the guide, when the guide is processed, three guide blades which are equidistantly and alternately surrounded on the outer wall of an inner ring are selected at the air inlet end of the guide, the highest point of the air inlet side of each guide blade is obtained, wherein the highest point is the intersection point of an air inlet side equal inclination curve of the guide blade and a pitch circle of the guide blade, the pitch circle is determined by the distance from the middle position of the guide blade to the center of the inner ring, the plane where the highest point of the three guide blades is located is taken as a first reference plane, more than three locating points which are equidistantly and alternately surrounded on the inner wall of the outer ring are selected at the air outlet end of the guide, and the planes where all locating points are located are taken as a second reference plane; and then the first datum plane is used as an axial machining datum, the first allowance part on the guide is machined along the axial direction, the second datum plane is used as a radial machining datum, and the second allowance part on the guide is machined along the radial direction. According to the invention, two important dimension-related surfaces are set as the references, namely the first reference surface and the second reference surface with higher precision are selected as the references, the machining precision of the guide is improved, meanwhile, the region with high dimensional precision is considered, the dimensional tolerance and the form and position tolerance of each position after machining can be fully ensured to meet the requirements, the reference position is convenient to acquire, and the dimensional deviation caused by the complex structure in the whole guide casting process can be also compensated.
Drawings
The invention is described in further detail below with reference to the drawings and examples;
FIG. 1 is a flow chart of a processing method according to an embodiment;
FIG. 2 is another flow chart of the processing method according to the embodiment;
FIG. 3 is a partial cross-sectional view of an embodiment of a guide without machining;
FIG. 4 is a partial cross-sectional view of the guide according to the embodiment after machining;
FIG. 5 is a schematic view of a guide vane according to an embodiment;
FIG. 6 is a front view of a guide according to an embodiment;
fig. 7 is a schematic view of another view of the guide according to the embodiment.
In the figure:
100. a guide; 101. an air inlet end; 102. an exhaust end; 103. a first margin portion; 104. a second margin portion; 200. a pitch circle;
1. an inner ring;
2. a guide vane; 21. a highest point; 22. an air inlet side equal-inclination curve;
3. and an outer ring.
Detailed Description
In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved more clear, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.
In the description of the present invention, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description herein, it should be understood that the terms "upper," "lower," "left," "right," and the like are based on the orientation or positional relationship shown in the drawings, and are merely for convenience of description and to simplify the operation, rather than to indicate or imply that the apparatus or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for providing a special meaning.
In the description herein, reference to the term "one embodiment," "an example," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, schematic representations of the above terms do not necessarily refer to the same embodiments or examples.
The technical scheme of the invention is further described below by the specific embodiments with reference to the accompanying drawings.
As shown in fig. 1 and 2, the present embodiment provides a processing method for processing a guide 100, the processing method including the steps of:
s100, selecting three guide blades 2 which are equidistantly and alternately surrounded on the outer wall of the inner ring 1 at the air inlet end 101 of the guide device 100, and obtaining the highest point 21 of the air inlet side of each guide blade 2, wherein the highest point 21 is the intersection point of the equal-inclination curve 22 of the air inlet side of each guide blade 2 and the pitch circle 200 of the guide blade 2, the pitch circle 200 is determined by the distance from the middle position of the guide blade 2 to the center of the inner ring 1, the plane where the highest point 21 of the three guide blades 2 is located is used as a first reference plane, and the plane where more than three anchor points which are equidistantly and alternately surrounded on the inner wall of the outer ring 3 are selected at the air outlet end 102 of the guide device 100, and the planes where all the anchor points are located are used as second reference planes.
S200, using the first reference surface as an axial machining reference, machining the first allowance part 103 on the guide 100 along the axial direction, and using the second reference surface as a radial machining reference, machining the second allowance part 104 on the guide 100 along the radial direction.
Specifically, the equal-pitch curve 22 of the air inlet edge on the guide vane 2 is a curve of the guide vane 2 closest to the air inlet end 101, and each point on the curve may be selected as the highest point 21, that is, the air outlet end 102 of the guide 100 is regarded as the bottom end, the air inlet end 101 of the guide 100 is regarded as the top end, and the highest point 21 is located at the highest position of the guide vane 2.
Specifically, as shown in fig. 3 to 7, the guide 100 includes an inner ring 1, an outer ring 3 and a plurality of guide blades 2, the outer ring 3 is disposed at the outer periphery of the inner ring 1, the outer wall of the inner ring 1 is connected with the inner wall of the outer ring 3 by a connecting plate, a plurality of guide blades 2 are disposed on the outer wall of the inner ring 1 close to the air inlet end 101, and the plurality of guide blades 2 are all located on the same cross section, the embodiment obtains the highest point 21 of each of the three guide blades 2, a machining reference surface with higher precision, namely, a first reference surface, can be obtained, when the first allowance part 103 on the axial machining guide 100 is obtained, the cutting amount can be effectively controlled to ensure that the machining dimension along the axial direction meets the requirement, and when the first reference surface is taken as the axial machining reference, the outer wall of the air inlet end 101 is clamped by the three-jaw chuck, the guide 100 is ensured not to move along the axial direction, namely, the guide 100 is prevented from moving along the axial direction, the axial machining precision is ensured, six positioning points are obtained on the inner wall of the outer ring 3 close to the air outlet end 102, the plane, namely, the second allowance part 104 on the radial direction is ensured to move along the radial direction is ensured, and the radial machining precision is ensured, when the radial allowance part 104 on the radial direction is not moved along the radial reference surface is ensured, and the radial direction is ensured, the radial machining reference surface is ensured, and the radial machining precision is ensured. According to the embodiment, by setting two important dimension-related surfaces as the reference, namely, selecting a first reference surface and a second reference surface with higher precision as the reference, the machining precision of the guide 100 is improved, meanwhile, the region with high dimensional precision is considered, the dimensional tolerance and the form and position tolerance of each position after machining can be fully ensured to meet the requirements, the reference position is convenient to obtain, and the dimensional deviation caused by the complex structure in the casting process of the whole guide 100 can be also compensated.
Optionally, step S200 includes the steps of:
s201, a third-jaw chuck is adopted to internally support a second reference surface, the third-jaw chuck is attached to the end surface of the exhaust end 102, radial runout of the pitch circle 200 and radial runout of outer walls at two ends of the outer ring 3 are detected through a dial indicator, and if the radial runout of the pitch circle 200 and the radial runout of the outer walls at two ends of the outer ring 3 are within preset ranges, rough machining is conducted on the second allowance part 104 of the air inlet end 101. The three-jaw chuck is attached to the end face of the exhaust end 102, so that the three-jaw chuck can grasp the guide 100, and deflection of the guide 100 during rough machining is avoided; by rough machining the second remainder 104 of the air inlet end 101, most of the remainder material can be removed in a short time, surface defects can be removed, and a precise positioning reference can be provided for subsequent finish machining.
Specifically, the pitch circle 200 is the trajectory of the node of the guide vane 2 on the motion plane, and the node of the guide vane 2 and the highest point 21 are located on the same air inlet side equal pitch curve 22.
Optionally, after step S201, the method further includes the following steps:
s202, the inner wall of the air inlet end 101 is provided with the inner supporting outer ring 3 of the fixed block, the outer wall of the air inlet end 101 is provided with the three-jaw chuck, the three-jaw chuck is attached to the end face of the air inlet end 101, radial runout of the outer wall of the air outlet end 102 of the inner ring 1 is detected through the dial indicator, and if the radial runout of the outer wall of the air outlet end 102 of the inner ring 1 is within a preset range, rough machining is performed on the first allowance part 103 of the air outlet end 102. The three-jaw chuck is attached to the end face of the air inlet end 101, so that the three-jaw chuck can grasp the guide 100, and deflection of the guide 100 during rough machining is avoided; through rough machining is carried out to the first allowance part 103 of the exhaust end 102, most of allowance materials can be removed in a short time, surface defects are removed, and meanwhile a precise positioning reference is provided for subsequent fine machining.
After finishing the rough machining twice, a more accurate positioning reference is obtained, and then a subsequent finish machining step is carried out on the basis of the positioning reference.
Optionally, after step S202, the following steps are further included:
s203, supporting the inner wall of the outer ring 3 at the exhaust end 102 by adopting a fixed block, clamping the outer wall of the outer ring 3 at the exhaust end 102 by adopting a three-jaw chuck, enabling the three-jaw chuck to be attached to the end face of the exhaust end 102, and carrying out finish machining on the second allowance part 104 of the air inlet end 101 so as to enable the distance from the end face of the outer ring 3 at the air inlet end 101 to the first reference surface to be h1.
Optionally, after step S203, the method further includes the following steps:
s204, supporting the inner wall of the outer ring 3 at the air inlet end 101 by adopting a fixed block, clamping the outer ring 3 at the outer wall of the air inlet end 101 by adopting a three-jaw chuck, attaching the three-jaw chuck to the end face of the air inlet end 101, and finishing the first allowance part 103 of the air outlet end 102 to ensure that the distance from the end face of the outer ring 3 at the air outlet end 102 to the first reference surface is h2.
Optionally, after step S200, the following steps are further included:
s300, the stress groove of the guide 100 is machined by taking the exhaust end 102 as a positioning end.
Optionally, after step S300, the following steps are further included:
s400, deburring the guide 100 and cleaning contaminants located on the surface of the guide 100.
Optionally, after step S400, the following steps are further included:
s500, visually inspecting the surface quality of the guide 100, detecting the size and the surface roughness of the guide 100, and detecting the surface defect of the guide 100.
By the machining method, machining precision can be guaranteed while machining references are rapidly positioned, and the air inlet end 101 and the air outlet end 102 of the guide 100 are machined only twice, namely, the first machining is rough machining, the second machining is finish machining, so that deformation caused by clamping of a three-jaw chuck is reduced, and dimensional deviations such as deformation existing in the casting process of the guide 100 with the integral front end are compensated; and few special fixtures are used in the machining process, so that the fixture design, machining and verification cost is saved, and the machining efficiency of the guide 100 is improved.
The present embodiment also provides a guide 100, wherein the guide 100 is manufactured by the above processing method, and the guide 100 is manufactured by high-temperature alloy materials.
The present embodiment also provides a turbine comprising a guide 100 as above.
Furthermore, the foregoing description of the preferred embodiments and the principles of the invention is provided herein. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, while the invention has been described in connection with the above embodiments, the invention is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the invention, which is set forth in the following claims.
Claims (6)
1. Machining method for a machining guide (100), characterized in that it comprises the steps of:
s100, selecting three guide blades (2) which are equidistantly spaced and encircling the outer wall of an inner ring (1) at the air inlet end (101) of the guide device (100), and acquiring the highest point (21) of the air inlet side of each guide blade (2), wherein the highest point (21) is the intersection point of an air inlet side equal-inclination curve (22) of the guide blade (2) and a pitch circle (200) of the guide blade (2), the pitch circle (200) is determined by the distance from the middle position of the guide blade (2) to the center of the inner ring (1), a plane where the highest point (21) of the three guide blades (2) is located is used as a first reference plane, and more than three locating points which are equidistantly spaced and encircling the inner wall of the outer ring (3) are selected at the air outlet end (102) of the guide device (100), and all planes where the locating points are located are used as second reference planes;
s200, using the first reference surface as an axial machining reference, machining a first allowance part (103) on the guide (100) along the axial direction, and using a second reference surface as a radial machining reference, and machining a second allowance part (104) on the guide (100) along the radial direction;
the step S200 includes the steps of:
s201, adopting a three-jaw chuck to internally support the second reference surface, enabling the three-jaw chuck to be attached to the end surface of the exhaust end (102), detecting radial runout of the pitch circle (200) and radial runout of outer walls at two ends of the outer ring (3) through a dial indicator, and if the radial runout of the pitch circle (200) and the radial runout of the outer walls at two ends of the outer ring (3) are within preset ranges, performing rough machining on the second allowance part (104) of the air inlet end (101);
the pitch circle (200) is a track of a node of the guide blade (2) on a motion plane, and the node of the guide blade (2) and the highest point (21) are positioned on the same air inlet side equal-inclination curve (22);
after said step S201, the method further comprises the steps of:
s202, adopting a fixed block to internally support the outer ring (3) to be positioned on the inner wall of the air inlet end (101) and adopting the three-jaw chuck to clamp the outer ring (3) to be positioned on the outer wall of the air inlet end (101), enabling the three-jaw chuck to be attached to the end face of the air inlet end (101), detecting radial runout of the inner ring (1) positioned on the outer wall of the air outlet end (102) through the dial indicator, and if the radial runout of the inner ring (1) positioned on the outer wall of the air outlet end (102) is within a preset range, performing rough machining on the first allowance part (103) of the air outlet end (102);
after the step S202, the method further includes the steps of:
s203, supporting the inner wall of the outer ring (3) positioned at the exhaust end (102) by adopting the fixed block, clamping the outer ring (3) positioned at the outer wall of the exhaust end (102) by adopting the three-jaw chuck, enabling the three-jaw chuck to be attached to the end face of the exhaust end (102), and carrying out finish machining on the second allowance part (104) of the air inlet end (101) so as to enable the distance from the end face of the outer ring (3) positioned at the air inlet end (101) to the first reference surface to be h1;
after said step S203, the method further comprises the steps of:
s204, the fixing block is adopted to prop up the outer ring (3) to be located on the inner wall of the air inlet end (101) and the three-jaw chuck is adopted to clamp the outer ring (3) to be located on the outer wall of the air inlet end (101), the three-jaw chuck is enabled to be attached to the end face of the air inlet end (101), and the first allowance part (103) of the air outlet end (102) is subjected to finish machining, so that the distance from the end face of the outer ring (3) to the first reference surface, which is located on the air outlet end (102), is h2.
2. The processing method according to claim 1, further comprising, after the step S200, the steps of:
s300, processing the stress groove of the guide (100) by taking the exhaust end (102) as a positioning end.
3. The processing method according to claim 2, further comprising, after said step S300, the steps of:
s400, deburring the guide (100) and cleaning pollutants on the surface of the guide (100).
4. A method according to claim 3, further comprising, after said step S400, the steps of:
s500, visually inspecting the surface quality of the guide (100), detecting the size and the surface roughness of the guide (100), and detecting the surface defect of the guide (100).
5. A guide manufactured by the processing method according to any one of claims 1 to 4.
6. Turbine, characterized by comprising a guide (100) according to claim 5.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211324059.7A CN115502671B (en) | 2022-10-27 | 2022-10-27 | Machining method, guide and turbine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211324059.7A CN115502671B (en) | 2022-10-27 | 2022-10-27 | Machining method, guide and turbine |
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| CN115502671A CN115502671A (en) | 2022-12-23 |
| CN115502671B true CN115502671B (en) | 2023-07-21 |
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| CN104454027B (en) * | 2014-10-31 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | The processing method of power turbine guider |
| CN106514149B (en) * | 2016-11-29 | 2018-08-10 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of processing method of monoblock type guider |
| US11339680B2 (en) * | 2018-02-28 | 2022-05-24 | Mitsubishi Heavy Industries Engine & Turbocharger, Ltd. | Radial inflow turbine and turbocharger |
| CN115091210B (en) * | 2022-08-03 | 2023-12-01 | 中国航发南方工业有限公司 | Machining method of power turbine guider |
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