CN115091210B - Machining method of power turbine guider - Google Patents
Machining method of power turbine guider Download PDFInfo
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- CN115091210B CN115091210B CN202210927899.6A CN202210927899A CN115091210B CN 115091210 B CN115091210 B CN 115091210B CN 202210927899 A CN202210927899 A CN 202210927899A CN 115091210 B CN115091210 B CN 115091210B
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- 238000003754 machining Methods 0.000 title claims abstract description 67
- 238000000034 method Methods 0.000 title claims abstract description 39
- 238000012545 processing Methods 0.000 claims abstract description 48
- 238000000227 grinding Methods 0.000 claims abstract description 35
- 238000003801 milling Methods 0.000 claims abstract description 32
- 238000005520 cutting process Methods 0.000 claims abstract description 29
- 230000008646 thermal stress Effects 0.000 claims abstract description 26
- 238000010892 electric spark Methods 0.000 claims abstract description 13
- 238000007670 refining Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 6
- 238000005516 engineering process Methods 0.000 abstract description 3
- 230000008569 process Effects 0.000 description 19
- 230000003247 decreasing effect Effects 0.000 description 8
- 238000003672 processing method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 4
- 238000012986 modification Methods 0.000 description 4
- 230000004048 modification Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000012546 transfer Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 230000006872 improvement Effects 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 230000003647 oxidation Effects 0.000 description 2
- 238000007254 oxidation reaction Methods 0.000 description 2
- 238000012797 qualification Methods 0.000 description 2
- 230000035882 stress Effects 0.000 description 2
- 239000000725 suspension Substances 0.000 description 2
- 238000009827 uniform distribution Methods 0.000 description 2
- 206010017472 Fumbling Diseases 0.000 description 1
- 229910000799 K alloy Inorganic materials 0.000 description 1
- 238000005266 casting Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 238000007514 turning Methods 0.000 description 1
Classifications
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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
- B23P23/00—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass
- B23P23/04—Machines or arrangements of machines for performing specified combinations of different metal-working operations not covered by a single other subclass for both machining and other metal-working operations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
Abstract
The application relates to the technical field of machining, and discloses a machining method of a power turbine guide, wherein the power turbine guide comprises an outer ring, an inner ring and a honeycomb structure, the outer ring and the inner ring are connected by guide blades, a plurality of bosses and a plurality of thermal stress release grooves are arranged on the inner ring, a plurality of precise bosses are arranged on the outer ring, and the machining steps are as follows: s1, machining circumferential dimensions of an outer ring and an inner ring in place, and reserving allowance for the axial dimensions of mounting edges of the inner ring; s2, machining an outer ring precise boss in place; s3, a thermal stress release groove is formed in the inner ring through linear cutting; s4, accurately grinding the axial dimension of the mounting edge of the inner ring until the mounting edge is machined in place; s5, cutting the boss line on the inner ring in place; s6, machining the honeycomb structure by electric spark grinding. The application innovates and improves the technology route, improves the milling feed scheme, optimizes the electric spark electrode and the processing parameters, and the like, does not avoid the problem of deformation of the part after the thermal stress relief groove is processed, adopts the measure of reserving the processing allowance to neutralize the size deformation, and ensures the final axial design size requirement.
Description
Technical Field
The application relates to the technical field of machining, in particular to a machining method of a power turbine guide.
Background
The turbine guider of the power of the certain type of aeroengine shown in fig. 1 belongs to a typical precise thin-wall annular part, and is made of a fatigue-resistant, oxidation-resistant, high-hardness and difficult-to-machine material K418B, and has serious cutter consumption and difficult cutting in the cold machining process. The whole part has an inner diameter of phi 608-phi 650mm, an axial width of only 82mm and a diameter-width ratio of about 8, and the inner and outer ring wall thickness of only 1.3-4 mm, and belongs to a typical large-span short-profile thin-wall structure.
The inner ring and the outer ring of the guide are connected through the slender guide blades, a plurality of fracture thermal stress release grooves are uniformly distributed at the inner ring, so that the rigidity of the guide is insufficient and the deformation of the axial feeding processing cutter is serious under the condition that the small boss of the inner lace and four guide blades connected with the small boss are fixedly positioned only by the outer ring in the axial direction, the relevant dimensions of the inner ring and the outer ring are processed in place at first, and then the thermal stress release grooves of the inner ring are processed. However, the axial precise dimension of the inner ring of the part is qualified in the previous turning process, but the inner mounting edge is out of constraint to generate stress deformation after the subsequent inner ring lace boss linear cutting and the thermal stress relief groove processing, and the axial precise dimension of the part is deformed out of tolerance.
The patent application number CN2014106040680 discloses a machining method of a power turbine guide, and although the patent is the same as the application, the machining method is mainly aimed at determining an axial initial machining reference of the power turbine guide so as to improve the qualification rate of a casting channel surface of the turbine guide and guide blades to the form and position tolerance of the subsequent machining reference, and does not mention the problem of axial precise dimensional deformation of an inner ring of the guide.
Furthermore, according to the process route of fig. 2, there is a need to solve the following problems in the guide processing: 1) The axial positions of a plurality of precise bosses uniformly distributed on the outer ring of the guide are deeper, so that the cutter is longer in suspension length, the phi 2 milling cutter is weak in rigidity, and the cutter is machined by up to 40 suspension lengths, so that the cutter is seriously left, and the part is not milled. The radial precision size of the honeycomb structure of the part reaches phi 636.7 (+ 0.05, 0) mm, the axial width is 10, and the large-size honeycomb is subjected to electric spark grinding, so that the production efficiency is low; 2) The process scheme of the precise boss of the outer ring is vertical milling and precise linear cutting, the processing efficiency is low, the arc milling at the bottom of the side edge is not in place, and the processing quality of the precise dimension linear cutting of the width of the boss is unstable; 3) The electric spark grinding machining efficiency of the precise honeycomb size at the two parts of the large end of the part is low, and the efficiency is needed to be improved.
Disclosure of Invention
The application aims to overcome the defects of the prior art, and provides a processing method of a power turbine guider, which can overcome the problem of deformation of the axial precise dimension of an inner ring, can avoid the problem of out-of-tolerance deformation of the axial precise dimension of the inner ring, can ensure that the outer ring is processed to be qualified in precise boss width dimension and the like, and can obviously improve the machining efficiency of honeycomb electric spark grinding.
The application aims at realizing the following technical scheme:
the power turbine guide comprises an outer ring, an inner ring and a honeycomb structure, wherein the outer ring and the inner ring are connected by guide blades, a plurality of bosses and a plurality of thermal stress release grooves are arranged on the inner ring, a plurality of precise bosses are arranged on the outer ring, the axial dimension of an inner ring mounting edge is reserved for allowance, and after the thermal stress release grooves on the inner ring are processed, the axial dimension of the inner ring mounting edge is finished in place.
Further, the power turbine guide is processed by the following steps:
s1, machining circumferential dimensions of an outer ring and an inner ring in place, and reserving allowance for the axial dimensions of mounting edges of the inner ring;
s2, machining an outer ring precise boss in place;
s3, a thermal stress release groove is formed in the inner ring through linear cutting;
s4, accurately grinding the axial dimension of the mounting edge of the inner ring until the mounting edge is machined in place;
s5, cutting the boss line on the inner ring in place;
s6, machining the honeycomb structure by electric spark grinding.
Further, the reserved allowance of the axial dimension of the inner ring installation edge in the S1 is 0.2-0.5 mm.
Still further, measures are taken to increase the power turbine guide stiffness for the inner ring thermal stress relief grooves and blade areas prior to S4 refining.
Still further, the measure is wax filling, and the wax removal is required after the finish grinding of the size is in place at S4.
Furthermore, the machining mode of the outer ring precise boss in the step S2 is milling, the allowance of the precise boss is removed, and then the width dimension of the precise boss is finished, so that the transfer arc is ensured, and the tool joint mark is removed.
Still further, the apparatus employed in S2 is a five axis vertical and horizontal milling apparatus.
Further, when the cutting mark is removed, the milling cutter is fed in a direction perpendicular to the position of the cutting mark.
Further, the size of the spark-ground honeycomb electrode in S6 is close to the honeycomb diameter size.
Further, the grinding processing in the step S6 adopts a mode of decreasing feed and optimizing layering parameters.
Compared with the prior art, the application has the following beneficial effects:
the application innovates and improves the technology route, improves the milling feed scheme, optimizes the electric spark electrode and the processing parameters, and the like, does not avoid the problem of deformation of the part after the thermal stress relief groove is processed, adopts the measure of reserving the processing allowance to neutralize the size deformation, and ensures the final axial design size requirement;
the machining mode of combining traditional vertical milling rough machining and linear cutting finish machining is abandoned, numerical control milling is adopted in the whole process, numerical control effect improvement is achieved, meanwhile, the relevant size of the precise boss can be ensured, in addition, a milling machining path of a milling cutter for feeding in the direction perpendicular to the position direction of the cutter mark is additionally arranged, and the cutter mark can be effectively removed;
the honeycomb machining process improves the machining efficiency by increasing the size of the honeycomb electrode and improving the single cutting amount of the electrode, the grinding process is carried out in a mode of decreasing feed and optimizing layering parameters, which is equivalent to dividing honeycomb machining into rough machining, semi-finishing and finishing, decreasing axial radial allowance and optimizing parameters such as corresponding current pulse width, and the like, is beneficial to improving the machining quality of the honeycomb surface, can improve the machining precision of the size, can grind large allowance of rough machining, can reduce the machining time and greatly improve the overall machining efficiency.
Drawings
FIG. 1 is a process flow of a power turbine pilot as described in example 2;
FIG. 2 is a schematic view of removing the outer ring precision boss tool mark in example 2;
FIG. 3 is a schematic view of a honeycomb electrode processing honeycomb structure of example 2;
FIG. 4 is a schematic illustration of a power turbine pilot;
FIG. 5 is a conventional process flow of a power turbine pilot;
FIG. 6 is a schematic view of a honeycomb electrode machining honeycomb structure commonly used in power turbine guides.
Detailed Description
The present application will be further described with reference to the following specific embodiments, and in order to clearly explain the technical features of the present application, the present application will be described in detail with reference to the following specific embodiments and the accompanying drawings.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present application, however, the present application may be practiced in other ways than those described herein, and therefore the scope of the present application is not limited to the specific embodiments disclosed below.
In addition, in the description of the present application, it should be understood that the terms "center", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more such feature. In the description of the present application, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the present application, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; the device can be mechanically connected, electrically connected and communicated; 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 application can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present application, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," 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 present application. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.
Example 1
In order to avoid serious deformation caused by insufficient rigidity of the inner ring and the parts connected with the inner ring after the processing of the fracture groove is finished, the method selects to reserve allowance for the axial dimension of the mounting edge of the inner ring before the processing of the fracture groove, and then finish-processes the inner ring to remove the allowance after the fracture groove on the inner ring is processed. The processing method does not avoid the problem of integral deformation of the part after the part fracture groove is processed, and the size of the final part can be ensured to meet the design size requirement by reserving the processing allowance to neutralize the size deformation.
Example 2
The turbine guider of the power of the aeroengine shown in fig. 4 belongs to a typical precise thin-wall annular part, is made of a fatigue-resistant, oxidation-resistant, high-hardness and difficult-to-process material K418B, belongs to a high-aspect-ratio weak-rigidity K alloy guider, has serious cutter consumption in the cold working process, and is not easy to cut. The power turbine guide comprises an outer ring, an inner ring and a honeycomb structure, wherein the outer ring and the inner ring are connected by guide blades, a plurality of bosses and a plurality of thermal stress release grooves are arranged on the inner ring, and a plurality of precise bosses are arranged on the outer ring. The conventional process route is shown in fig. 5, before the thermal stress relief groove structure is machined and formed, the numerical control vertical lathe has machined the circular hole size of the inner ring and the relative axial precise size of the inner mounting edge in place, and in the processes of front and back process size chain and tolerance control or subsequent linear cutting machining of the inner ring thermal stress relief groove and uniform distribution boss, effective measures are not taken to control machining stress deformation, and finally, the axial precise size of the inner ring mounting edge is out of tolerance.
The embodiment provides a method for machining a power turbine guide, as shown in fig. 1, in a numerical control vertical lathe stage, the axial dimension of an inner ring mounting edge is reserved for a margin, then an outer ring precise boss is machined, then a thermal stress relief groove is machined, and after the thermal stress relief groove on the inner ring is machined, the axial dimension of the inner ring mounting edge is finished in place.
Specifically, the power turbine pilot is processed as follows:
s1, machining circumferential dimensions of an outer ring and an inner ring in place, and reserving allowance of 0.2 in the axial dimension of a mounting edge of the inner ring;
s2, machining the outer ring precise boss in place;
s3, linearly cutting a thermal stress release groove on the inner ring and processing the thermal stress release groove in place;
s4, precisely grinding the axial precise dimension of the mounting edge of the inner ring until the mounting edge is machined in place;
s5, cutting the boss on the inner ring in place;
s6, machining the honeycomb structure by electric spark grinding.
Wherein, in order to further increase the rigidity of the power turbine guide in the processing process, measures can be taken between the steps S3 and S4 for the inner ring thermal stress relief groove and the blade area to enhance the rigidity of the power turbine guide so as to avoid the processing deformation to the maximum extent. The method of this embodiment adopts the steps of wax filling, the fine grinding process in S4 is performed under the condition that the thermal stress relief grooves of the inner ring of the turbine guide and the blade area are waxed, and the wax removal operation is required to be performed on the turbine guide after the fine grinding in S4 is in place.
As described above, the processing route of the processing method does not avoid the problem of deformation of the part after the thermal stress relief groove is processed, the processing allowance is reserved to neutralize the size deformation, and measures are taken for improving the rigidity of the part aiming at the weak rigidity structure of the inner ring in the axial size grinding process so as to ensure the final axial design size requirement.
Aiming at the problems that machining efficiency is low and machining quality of circular arcs at the bottom of side edges and precise width dimensions is unstable when a plurality of precise bosses on the outer ring of the power turbine guide are machined in a combined mode of vertical milling rough machining and wire cutting finish machining according to a traditional technological scheme, the machining mode of the precise bosses on the outer ring in the S2 is designed to be milling machining, specifically, five-axis vertical and horizontal type milling equipment is adopted, the allowance of the precise bosses is removed through vertical machining, the width dimensions of the precise bosses are machined through horizontal type finish machining, and switching circular arcs R and cutter marks of the outer ring are guaranteed.
In the above new process scheme for processing the outer ring precise boss, the technical difficulty is that the problem of removing the cutting marks at the side of the boss transfer R is solved, as shown in fig. 2, the dash-dot line is the outline of a horizontal common process scheme milling cutter, and the common milling scheme is to perform horizontal milling along two sides of the boss, so that the width dimension and the bottom arc R are ensured. It can be seen from fig. 2 that after milling using this common process scheme there will be a tool receiving table as shown in the oval on the right. In order to solve the technical problem, the machining method selects a new milling path, wherein the milling cutter is positioned at the new milling cutter position as shown by a solid line in fig. 2, the milling cutter does not use two sides of the boss as paths for machining, and feeds in a direction perpendicular to the position of the internal cutting mark in the elliptical ring to remove the cutting mark. Therefore, compared with the conventional milling scheme, the novel vertical and horizontal milling process scheme has the advantages that numerical control is improved, the problem of cutter mark connection is solved, and the machining quality of the arc R at the bottom of the side edge and the width dimension of the boss is ensured.
In the S6 electric spark grinding process, the diameter size of the part honeycomb reaches phi 636.7, the part honeycomb belongs to a large-span size, 13 hours are needed for processing one circle of honeycomb by the traditional honeycomb, and the power turbine guide is divided into two circles of honeycomb at the upper stage and the lower stage, the total processing time reaches 3.5 shifts (8 hours/shift), and the processing efficiency is low. In this embodiment, the process is optimized to improve the machining efficiency by improving the honeycomb electrode as the cut-in point.
Fig. 6 is a schematic diagram of machining a honeycomb by spark grinding before modification, fig. 3 is a schematic diagram of machining a honeycomb by spark grinding after modification, and a black hatched area 1 is a honeycomb electrode cutting area. According to the graph, the larger the size of the honeycomb electrode 2, the more the honeycomb electrode is cut, the larger the honeycomb allowance is removed, namely the larger the honeycomb processing area in the graph is; and the larger the size R of the honeycomb electrode 2, the shorter the circumference L [ l=2pi (R-R) ] of the honeycomb electrode center around the honeycomb, the less time-consuming. In summary, by increasing the size of the honeycomb electrode to a size close to the diameter of the honeycomb, the single cutting amount of the honeycomb electrode can be increased, and thus the processing efficiency can be improved, and in this embodiment, the honeycomb electrode size is preferably phi 600.
Example 3
The embodiment provides a processing method of a power turbine guide, which comprises the following steps:
s1, machining circumferential dimensions of an outer ring and an inner ring in place, and reserving allowance of 0.5 in the axial dimension of a mounting edge of the inner ring;
s2, machining the outer ring precise boss in place, wherein the outer ring precise boss is machined in a milling mode, the allowance of the precise boss is removed firstly, then the width dimension of the precise boss is finely machined, the transfer arc is ensured, and the tool mark is removed;
s3, a thermal stress release groove is formed in the inner ring through linear cutting;
s4, taking measures on the inner ring thermal stress release groove and the blade area to enhance the rigidity of the power turbine guide, wherein the measures are wax filling;
s5, accurately grinding the axial dimension of the mounting edge of the inner ring until the mounting edge is machined in place;
s6, removing wax;
s7, cutting the boss line on the inner ring in place;
s8, machining the honeycomb structure by electric spark grinding.
Wherein, the equipment adopted in the S2 is five-axis vertical and horizontal milling equipment; when the cutting mark is removed, the milling cutter is fed in a direction perpendicular to the position of the cutting mark.
The size of the spark-ground honeycomb electrode in S8 is close to the honeycomb diameter size.
This embodiment differs from embodiment 2 in that: and S8, performing electric spark grinding processing in a mode of decreasing feed and optimizing layering parameters.
The honeycomb of the power turbine guide may alternatively be performed on a FORM E600 (GF) precision forming spark machine using a universal honeycomb electrode. The traditional technological scheme uses only one set of technological parameters to carry out multi-layer uniformly distributed grinding, and the processing parameters are shown in the table one:
surface-to-surface multi-layer uniformly distributed same-group parameter grinding
In order to ensure the size precision and the surface quality of the honeycomb, the machining allowance and the machining parameters selected by the final finish machining are all relatively conservative, namely the time required by the final grinding is relatively long. The allowance and the processing parameters of each layer of the grinding mode in the first table are consistent with the final finish processing parameters, and relatively conservative data are adopted, so that the time consumption of original rough processing with low requirements is the same as that of finish processing with high requirements, the whole processing time is overlong, and the grinding processing efficiency is low.
Different from the multi-layer uniform distribution same-group parameter grinding processing method, in the embodiment, grinding processing is performed in a step S8 by adopting a mode of decreasing feed and layering parameter optimization. As shown in table two below:
surface two-layer decreasing type parameter optimizing grinding
The grinding mode of decreasing type feeding and layering parameter optimization is equivalent to dividing honeycomb processing into rough processing, semi-finishing and finishing, decreasing the axial and radial allowance and optimizing parameters such as corresponding current pulse width, and the like, thereby being beneficial to improving the processing quality of the honeycomb surface, improving the processing precision of the dimension, reducing the processing time of rough processing and greatly improving the overall processing efficiency.
The application innovates and improves the technology route, improves the milling feed scheme, optimizes the electric spark electrode and the processing parameters, and the like, ensures that the axial design precision size of the power turbine guide, the width of the outer ring precision boss and the processing qualification of the switching R size are ensured, the processing time of the guide precision boss width and the switching arc R procedure is reduced from the original 24H to 18H, and the procedure processing efficiency is improved by 25%; aiming at the spark grinding of the honeycomb, specific innovation is carried out from the aspects of improved design and parameter fumbling of the honeycomb electrode, 13H is needed for processing a circle of honeycomb in the traditional honeycomb, only 6H is needed for processing a circle of honeycomb at present, and the spark grinding efficiency of the honeycomb is improved by 53%.
It is apparent that the above examples are only examples for clearly illustrating the technical solution of the present application, and are not limiting of the embodiments of the present application. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. Any modification, equivalent replacement, improvement, etc. which come within the spirit and principles of the application are desired to be protected by the following claims.
Claims (7)
1. The power turbine guide comprises an outer ring, an inner ring and a honeycomb structure, wherein the outer ring and the inner ring are connected by guide blades, a plurality of bosses and a plurality of thermal stress release grooves are arranged on the inner ring, and a plurality of precise bosses are arranged on the outer ring;
the processing steps are as follows:
s1, machining circumferential dimensions of an outer ring and an inner ring in place, and reserving allowance for the axial dimensions of mounting edges of the inner ring;
s2, machining an outer ring precise boss in place;
s3, a thermal stress release groove is formed in the inner ring through linear cutting;
s4, accurately grinding the axial dimension of the mounting edge of the inner ring until the mounting edge is machined in place;
s5, cutting the boss line on the inner ring in place;
s6, machining the honeycomb structure by electric spark grinding.
2. The method of claim 1, wherein the axial dimension of the inner ring mounting edge in S1 is reserved by 0.2 to 0.5mm.
3. The method of claim 1, wherein the inner ring thermal stress relief grooves and blade areas are treated to enhance power turbine guide stiffness prior to S4 refining.
4. A method of machining a power turbine guide according to claim 3, wherein the measure is wax filling, and the removal of wax is required after S4 finish grinding is in place.
5. The method of claim 1, wherein the machining of the outer ring precise boss in S2 is milling, removing the allowance of the precise boss, and then finishing the width of the precise boss, ensuring the switching arc, and removing the tool mark.
6. The method of machining a power turbine guide according to claim 5, wherein the equipment used in S2 is a five axis vertical and horizontal milling equipment.
7. The method of claim 5 or 6, wherein the milling cutter is fed in a direction perpendicular to the position of the cutting mark when the cutting mark is removed.
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| CN201818331U (en) * | 2009-12-28 | 2011-05-04 | 中国燃气涡轮研究院 | Partitioned high-pressure turbine guider |
| CN103464989A (en) * | 2013-09-16 | 2013-12-25 | 苏州大学 | Processing technique of precision turbine parts |
| CN103586651A (en) * | 2013-11-29 | 2014-02-19 | 重庆清平机械厂 | Method for machining toothed arc |
| CN106141590A (en) * | 2016-08-08 | 2016-11-23 | 成都四威高科技产业园有限公司 | A kind of aspect is than thin-walled filter cavity body processing technology |
| CN107175475A (en) * | 2017-07-03 | 2017-09-19 | 沈阳透平机械股份有限公司 | A kind of processing method of long Thin-wall cylindrical part |
| CN109955039A (en) * | 2018-12-28 | 2019-07-02 | 天津航天长征火箭制造有限公司 | A kind of major diameter clip processing method with precision slot |
| CN110193610A (en) * | 2019-06-20 | 2019-09-03 | 苏州真懿精密器械有限公司 | Long line footpath is than turning thin-walled parts processing method |
| CN110253234A (en) * | 2019-07-22 | 2019-09-20 | 湖南南方通用航空发动机有限公司 | A kind of processing method of aero-engine low-pressure turbine guider outer cover |
| CN113059242A (en) * | 2021-03-25 | 2021-07-02 | 中国航发南方工业有限公司 | Method for machining multilayer honeycomb sealing ring by electric spark |
| CN113319613A (en) * | 2021-06-08 | 2021-08-31 | 南昌沪航工业有限公司 | Efficient machining method for large aircraft seat slide rail parts |
| CN114589461A (en) * | 2022-03-02 | 2022-06-07 | 贵州新安航空机械有限责任公司 | Numerical control machining process for parts of ventilation window frame |
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