CN115502671A - Machining method, guide and turbine - Google Patents
Machining method, guide and turbine Download PDFInfo
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- CN115502671A CN115502671A CN202211324059.7A CN202211324059A CN115502671A CN 115502671 A CN115502671 A CN 115502671A CN 202211324059 A CN202211324059 A CN 202211324059A CN 115502671 A CN115502671 A CN 115502671A
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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 manufacturing of aero-engines, and discloses a machining method, a guider and a turbine, wherein the machining method is used for machining the guider and comprises the following steps: s100, selecting three guide blades which surround the outer wall of the inner ring at equal intervals at the air inlet end of the guider, acquiring the highest point of the air inlet side of each guide blade, taking the plane where the highest points of the three guide blades are located as a first reference surface, selecting more than three positioning points which surround the inner wall of the outer ring at equal intervals at the air outlet end of the guider, and taking the plane where all the positioning points are located as a second reference surface; and S200, machining a first allowance part on the guide in the axial direction by taking the first reference surface as an axial machining reference, and machining a second allowance part on the guide in the radial direction by taking the second reference surface as a radial machining reference. The invention selects the positioning reference with higher precision, improves the processing precision of the guider and ensures that the guider can meet the requirement of manufacturing precision.
Description
Technical Field
The invention relates to the technical field of manufacturing of aero-engines, in particular to a machining method, a guider and a turbine.
Background
The turbine is one of main parts of an aircraft engine, is a vane machine for converting the capacity of high-temperature and high-pressure gas into kinetic energy and mechanical energy, and comprises a stator part and a rotor part, wherein the stator part is also called a guider, and the guider is an annular static blade cascade consisting of an outer ring, an inner ring and a group of guide blades. The operating conditions of the guider are very harsh, for example, the guider is in a high-temperature gas flow, the operating temperature is high, the guider is in direct contact with gas and is easily oxidized and corroded, the operating temperature fields of all parts of the guider are different, the guider is heated unevenly and has uneven thickness, so that the guider has very large thermal stress, and along with the starting, stopping, accelerating and decelerating of an aircraft engine, the guider works in a cold and hot alternating state, the guide blades are easily subjected to thermal fatigue, and fatigue cracks are easily generated at the front edges and the rear edges of the guide blades, so that the manufacturing process requirements of the guider are very harsh.
At present, a guider blank is an integral precision casting part, the blade profile of a blade, the flow passage surface of an inner ring and the flow passage surface of an outer ring are directly cast and molded, the processing parts of the guider are mainly concentrated at the positions outside the flow passage surface of the inner ring and the positions outside the flow passage surface of the outer ring, in the prior processing technology, the positioning datum of axial processing outside the end surface of a mounting edge is generally selected to process the guider, but the position of the mounting edge is mostly surplus positions, the size is large, the position of a casting head is poor in size precision and flatness, the end surface is used as the processing datum, large deviation of the processing dimension of other areas can be caused, and the form and position tolerance of the blade profile and the datum after the flow passage surface processing is out of tolerance.
Therefore, a need exists for a machining method, a guide and a turbine, which select a positioning reference with higher precision, improve the machining precision of the guide, and ensure that the guide can meet the requirement of manufacturing precision.
Disclosure of Invention
One object of the present invention is: the machining method, the guider and the turbine are provided, the positioning reference with higher precision is selected, the machining precision of the guider is improved, and the guider can meet the requirement of manufacturing precision.
In order 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 including the steps of:
s100, selecting three guide blades which surround the outer wall of an inner ring at equal intervals at the air inlet end of the guider, and obtaining the highest point of the air inlet side of each guide blade, wherein the highest point is the intersection point of an air inlet side equal-slope curve of each guide blade and a pitch circle of each guide blade, the pitch circle is determined by the distance from the middle position of each guide blade to the center of the inner ring, the plane where the highest points of the three guide blades are located is used as a first reference plane, more than three positioning points which surround the inner wall of the outer ring at equal intervals are selected at the air outlet end of the guider, and the plane where all the positioning points are located is used as a second reference plane;
and S200, machining a first allowance part on the guide in the axial direction by taking the first reference surface as an axial machining reference, and machining a second allowance part on the guide in the radial direction by taking a second reference surface as a radial machining reference.
As an optional technical solution, the step S200 includes the following steps:
s201, adopt three-jaw chuck internal stay the second reference surface, and make three-jaw chuck with the terminal surface laminating of exhaust end detects through the percentage table pitch circle 'S runout and the runout of the outer wall at the both ends of outer ring, if pitch circle' S runout and the runout of the outer wall at the both ends of outer ring all predetermines the within range, then right the inlet end the second surplus position carries out rough machining.
As an optional technical solution, after the step S201, the method further includes the following steps:
s202, adopt the fixed block internal stay the outer loop is located the inner wall of inlet end and adopts the three-jaw chuck presss from both sides tightly the outer loop is located the outer wall of inlet end, and make the three-jaw chuck with the terminal surface laminating of inlet end, through the percentage table detects the inner ring is located the runout of the outer wall of exhaust end, if the inner ring is located the runout of the outer wall of exhaust end is in predetermineeing the within range, then right the exhaust end first surplus position carries out rough machining.
As an optional technical solution, after the step S202, the method further includes the following steps:
s203, the fixed block is adopted to support the inner wall of the outer ring at the exhaust end and the three-jaw chuck is adopted to clamp the outer wall of the outer ring at the exhaust end, the three-jaw chuck is attached to the end face of the exhaust end, and the second allowance part of the air inlet end is subjected to finish machining, 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, the fixed block is adopted to prop up the inner wall of the outer ring at the air inlet end and the three-jaw chuck is adopted to clamp the outer wall of the outer ring at the air inlet end, the three-jaw chuck is attached to the end face of the air inlet end, the first allowance part of the exhaust end is subjected to finish machining, and the distance from the end face of the outer ring at the exhaust end to the first reference surface is h2.
As an optional technical solution, after the step S200, the method further includes the following steps:
s300, machining a stress groove of the guider 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, removing burrs of the guider and cleaning pollutants on the surface of the guider.
As an optional technical solution, after the step S400, the method further includes the following steps:
s500, visually inspecting the surface quality of the guider, detecting the size and the surface roughness of the guider, and detecting the surface defects of the guider.
In a second aspect, a guide is provided, made using the method of processing 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 guider and a turbine, wherein the guider is manufactured by the processing method, the turbine comprises the guider, when the guider is processed, three guide blades which surround the outer wall of an inner ring at equal intervals are selected at the air inlet end of the guider, the highest point of the air inlet side of each guide blade is obtained, wherein the highest point is the intersection point of an equal-slope curve of the air inlet side of each guide blade and a pitch circle of each guide blade, the pitch circle is determined by the distance from the middle position of each guide blade to the center of the inner ring, the plane where the highest points of the three guide blades are located is used as a first reference plane, more than three positioning points which surround the inner wall of the outer ring at equal intervals are selected at the air outlet end of the guider, and the plane where all the positioning points are located is used as a second reference plane; and then, the first reference surface is used as an axial machining reference, the first allowance part on the guide is machined along the axial direction, the second reference surface is used as a radial machining reference, and the second allowance part on the guide is machined along the radial direction. According to the invention, two surfaces related to important dimensions are set as references, namely a first reference surface and a second reference surface with higher precision are selected as references, so that the machining precision of the guider is improved, and areas with high dimensional precision are considered, so that dimensional tolerance and form and position tolerance of each position after machining can be fully ensured to meet requirements, the reference position is convenient to obtain, and dimensional deviation caused by a complex structure in the casting process of the whole guider can be compensated.
Drawings
The invention is explained in further detail below with reference to the figures and examples;
FIG. 1 is a flow chart of a process 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 unprocessed guide according to an embodiment;
FIG. 4 is a partial cross-sectional view of the guide according to the exemplary embodiment after machining;
FIG. 5 is a schematic structural 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 structural view of another view angle 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. the highest point; 22. an air inlet edge equal inclination curve;
3. and (4) an outer ring.
Detailed Description
In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description herein, it is to be understood that the terms "upper," "lower," "left," "right," and the like are based on the orientation or positional relationship shown in the drawings for convenience in description and simplicity of operation, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the present invention. Furthermore, the terms "first" and "second" are used merely for descriptive purposes and are not intended to have any special meaning.
In the description herein, references to "an embodiment," "an example" or the like are intended to mean 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, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example.
The technical scheme of the invention is further explained by the specific implementation mode in combination with the attached drawings.
As shown in fig. 1 and 2, the present embodiment provides a machining method for machining the guide 100, the machining method including the steps of:
s100, selecting three guide blades 2 which surround the outer wall of the inner ring 1 at equal intervals at the air inlet end 101 of the guide device 100, and obtaining the highest point 21 on the air inlet side of each guide blade 2, wherein the highest point 21 is the intersection point of an air inlet side equal-slope curve 22 of each guide blade 2 and a pitch circle 200 of each guide blade 2, the pitch circle 200 is determined by the distance from the middle position of each guide blade 2 to the center of the inner ring 1, the plane where the highest points 21 of the three guide blades 2 are located is taken as a first reference plane, more than three positioning points which surround the inner wall of the outer ring 3 at equal intervals are selected at the air outlet end 102 of the guide device 100, and the plane where all the positioning points are located is taken as a second reference plane.
S200, the first margin portion 103 on the guide 100 is machined in the axial direction with the first reference surface as the axial machining reference, and the second margin portion 104 on the guide 100 is machined in the radial direction with the second reference surface as the radial machining reference.
Specifically, the intake edge constant slope curve 22 on the guide vane 2 is a curve of the guide vane 2 closest to the intake end 101, and each point on the curve may be selected as the highest point 21, that is, the exhaust end 102 of the guide vane 100 is regarded as the bottom end, the intake end 101 of the guide vane 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 on the periphery of the inner ring 1, the outer wall of the inner ring 1 is connected to the inner wall of the outer ring 3 through a connecting plate, the outer wall of the inner ring 1 close to the air inlet 101 is provided with the plurality of guide blades 2, and the plurality of guide blades 2 are all located on the same cross section, in this embodiment, the respective highest points 21 of the three guide blades 2 are obtained, so that a machining reference surface with higher precision, that is, a first reference surface, can be obtained, when a first allowance portion 103 on the guide 100 is machined in the axial direction, the cutting amount can be effectively controlled, so that the machining dimension along the axial direction meets the requirement, and when the first reference surface is used as the axial machining reference, the three-jaw chuck clamps the outer wall of the air inlet 101, so that when axial machining is performed, the guide 100 is not moved in the axial direction, that the axial machining accuracy is ensured, and when the inner wall of the guide 100 is moved in the axial direction, the inner wall of the guide 100 is obtained, six positioning points are used as a second reference surface, when radial machining plane, the inner wall is moved in the radial direction, so that when the guide chuck is moved, the radial machining accuracy is ensured, and when the inner wall of the guide chuck is moved in the radial direction, and when the inner wall of the guide chuck 100 is moved, the radial direction, the guide chuck, the radial machining accuracy is ensured, and the guide chuck, and when the radial machining accuracy is not moved, the inner wall is ensured, and when the inner wall is moved in the radial machining accuracy is controlled, and when the guide chuck, the radial machining accuracy is ensured. In the embodiment, two surfaces related to important dimensions are set as the reference, namely, the first reference surface and the second reference surface with higher precision are selected as the reference, so that the machining precision of the guider 100 is improved, the area with high dimensional precision is considered, dimensional tolerance and 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 dimensional deviation caused by a complex structure in the casting process of the whole guider 100 can be compensated.
Optionally, step S200 includes the following steps:
s201, a second reference surface is internally supported by the three-jaw chuck, the three-jaw chuck is attached to the end face of the exhaust end 102, radial runout of the pitch circle 200 and radial runout of outer walls of 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 of two ends of the outer ring 3 are within a preset range, rough machining is performed on a 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 tightly grasp the guider 100, and the deviation of the guider 100 during rough machining is avoided; by roughly machining the second allowance part 104 of the air inlet 101, most of allowance materials can be removed in a short time, surface defects can be removed, and meanwhile, a more accurate positioning reference is provided for subsequent finish machining.
Specifically, the pitch circle 200 is a trajectory of a node of the guide vane 2 on a motion plane, and the node of the guide vane 2 and the highest point 21 are located on the same air inlet edge equal-slope curve 22.
Optionally, after step S201, the method further includes the following steps:
s202, adopting a fixing block inner support outer ring 3 to be located on the inner wall of the air inlet end 101 and adopting a three-jaw chuck to clamp the outer ring 3 to be located 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 outer wall of the inner ring 1 located on the exhaust end 102 through a dial indicator, and if the radial runout of the outer wall of the inner ring 1 located on the exhaust end 102 is within a preset range, roughly machining a first allowance part 103 of the exhaust 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 tightly grasp the guider 100, and the deviation of the guider 100 during rough machining is avoided; by rough machining the first allowance part 103 of the exhaust end 102, most of allowance materials can be removed in a short time, surface defects can be removed, and meanwhile, a more accurate positioning reference is provided for subsequent finish machining.
After two times of rough machining, a more accurate positioning reference is obtained, and then a subsequent finishing step is carried out on the basis of the more accurate positioning reference.
Optionally, after step S202, the method further includes the following steps:
s203, supporting the inner wall of the outer ring 3 at the exhaust end 102 by using a fixing block, clamping the outer wall of the outer ring 3 at the exhaust end 102 by using a three-jaw chuck, enabling the three-jaw chuck to be attached to the end face of the exhaust end 102, and performing finish machining on the second allowance part 104 of the air inlet end 101, so that the distance from the end face of the outer ring 3 at the air inlet end 101 to the first reference surface is h1.
Optionally, after step S203, the method further includes the following steps:
and S204, supporting the inner wall of the outer ring 3 at the air inlet end 101 by using a fixing block, clamping the outer wall of the outer ring 3 at the air inlet end 101 by using a three-jaw chuck, attaching the three-jaw chuck to the end surface of the air inlet end 101, and finishing the first allowance part 103 of the exhaust end 102, so that the distance from the end surface of the outer ring 3 at the exhaust end 102 to the first reference surface is h2.
Optionally, after step S200, the method further includes the following steps:
and S300, machining the stress groove of the guide 100 by taking the exhaust end 102 as a positioning end.
Optionally, after step S300, the method further includes the following steps:
s400, deburring the guide 100, and cleaning contaminants on the surface of the guide 100.
Optionally, after step S400, the method further includes the following steps:
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 defects of the guide 100.
By the aid of the machining method, machining accuracy can be guaranteed while machining references are quickly positioned, and the air inlet end 101 and the air outlet end 102 of the guider 100 are machined twice, namely the first machining is rough machining, the second machining is fine machining, deformation caused by clamping of a three-jaw chuck is reduced, and dimensional deviations such as deformation in the casting process of the guider 100 with the integral front end are compensated; and a special fixture is rarely used in the machining process, so that the design, machining and verification costs of the fixture are saved, and the machining efficiency of the guider 100 is improved.
The present embodiment further provides a guide 100, wherein the guide 100 is manufactured by the above-mentioned processing method, and the guide 100 is made of a high-temperature alloy material.
The present embodiment also provides a turbine comprising the above-described guide 100.
In addition, the foregoing is only the preferred embodiment of the present invention and the technical principles applied. 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, although the present invention has been described in greater detail by the above embodiments, the present invention is not limited to the above embodiments, and may include other equivalent embodiments without departing from the spirit of the present invention, and the scope of the present invention is determined by the scope of the appended claims.
Claims (10)
1. Machining method for machining a guide (100), characterized in that it comprises the following steps:
s100, selecting three guide blades (2) which surround the outer wall of an inner ring (1) at equal intervals at an air inlet end (101) of the guider (100), and obtaining a 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-slope curve (22) of each guide blade (2) and a pitch circle (200) of each guide blade (2), the pitch circle (200) is determined by the distance from the middle position of each guide blade (2) to the center of the inner ring (1), a plane where the highest points (21) of the three guide blades (2) are located is taken as a first reference plane, more than three positioning points which surround the inner wall of the outer ring (3) at equal intervals are selected at an air outlet end (102) of the guider (100), and a plane where all the positioning points are located is taken as a second reference plane;
and S200, machining a first allowance part (103) on the guide (100) in the axial direction by taking the first reference surface as an axial machining reference, and machining a second allowance part (104) on the guide (100) in the radial direction by taking a second reference surface as a radial machining reference.
2. The machining method according to claim 1, wherein the step S200 includes the steps of:
s201, a three-jaw chuck is adopted to internally support the second reference surface, the three-jaw chuck is attached to the end face of the exhaust end (102), the radial runout of the pitch circle (200) and the radial runout of the outer walls of the 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 of the two ends of the outer ring (3) are within a preset range, the second allowance part (104) of the air inlet end (101) is subjected to rough machining.
3. The processing method according to claim 2, further comprising, after the step S201, the steps of:
s202, a fixing block is adopted to internally support the outer ring (3) which is located on the inner wall of the air inlet end (101) and the three-jaw chuck is adopted to clamp the outer ring (3) which is located on the outer wall of the air inlet end (101), the three-jaw chuck is attached to the end face of the air inlet end (101), the radial runout of the outer wall of the exhaust end (102) of the inner ring (1) is detected through the dial indicator, and if the radial runout of the outer wall of the exhaust end (102) of the inner ring (1) is within a preset range, the first allowance part (103) of the exhaust end (102) is subjected to rough machining.
4. The machining method according to claim 3, further comprising, after the step S202, the steps of:
s203, the inner wall of the outer ring (3) located at the exhaust end (102) is supported by the fixing block, the outer wall of the outer ring (3) located at the exhaust end (102) is clamped by the three-jaw chuck, the three-jaw chuck is attached to the end face of the exhaust end (102), the second allowance part (104) of the air inlet end (101) is subjected to finish machining, and the distance from the end face of the outer ring (3) located at the air inlet end (101) to the first reference surface is h1.
5. The machining method according to claim 4, characterized by further comprising, after the step S203, the steps of:
s204, the fixed block is adopted to support the inner wall of the outer ring (3) located at the air inlet end (101) and clamp the outer wall of the outer ring (3) located at the air inlet end (101) through the three-jaw chuck, the three-jaw chuck is made to be attached to the end face of the air inlet end (101), the first allowance part (103) of the exhaust end (102) is subjected to finish machining, and the distance from the end face of the outer ring (3) located at the exhaust end (102) to the first reference surface is h2.
6. The processing method according to claim 1, further comprising, after the step S200, the steps of:
s300, machining a stress groove of the guide device (100) by taking the exhaust end (102) as a positioning end.
7. The machining method according to claim 6, further comprising, after the step S300, the steps of:
s400, removing burrs of the guider (100) and cleaning pollutants on the surface of the guider (100).
8. The machining method according to claim 7, further comprising, after the 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 defects of the guide (100).
9. Guide, characterized in that it is obtained by the process according to any one of claims 1 to 8.
10. Turbine, characterized in that it comprises a guide (100) according to claim 9.
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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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| 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 true CN115502671A (en) | 2022-12-23 |
| CN115502671B CN115502671B (en) | 2023-07-21 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH370805A (en) * | 1958-11-07 | 1963-07-31 | Parsons & Marine Eng Turbine | Method for manufacturing a turbine nozzle |
| CN104454027A (en) * | 2014-10-31 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Machining method of power turbine guider |
| CN106514149A (en) * | 2016-11-29 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method of integral guide apparatus |
| CN111655987A (en) * | 2018-02-28 | 2020-09-11 | 三菱重工发动机和增压器株式会社 | Radial turbine and turbocharger |
| CN115091210A (en) * | 2022-08-03 | 2022-09-23 | 中国航发南方工业有限公司 | Power turbine guider machining method |
-
2022
- 2022-10-27 CN CN202211324059.7A patent/CN115502671B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH370805A (en) * | 1958-11-07 | 1963-07-31 | Parsons & Marine Eng Turbine | Method for manufacturing a turbine nozzle |
| CN104454027A (en) * | 2014-10-31 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Machining method of power turbine guider |
| CN106514149A (en) * | 2016-11-29 | 2017-03-22 | 沈阳黎明航空发动机(集团)有限责任公司 | Processing method of integral guide apparatus |
| CN111655987A (en) * | 2018-02-28 | 2020-09-11 | 三菱重工发动机和增压器株式会社 | Radial turbine and turbocharger |
| CN115091210A (en) * | 2022-08-03 | 2022-09-23 | 中国航发南方工业有限公司 | Power turbine guider machining method |
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| Publication number | Publication date |
|---|---|
| CN115502671B (en) | 2023-07-21 |
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