CN220636228U - Splicing tool for turbine guide of aero-engine - Google Patents
Splicing tool for turbine guide of aero-engine Download PDFInfo
- Publication number
- CN220636228U CN220636228U CN202322219932.2U CN202322219932U CN220636228U CN 220636228 U CN220636228 U CN 220636228U CN 202322219932 U CN202322219932 U CN 202322219932U CN 220636228 U CN220636228 U CN 220636228U
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- turbine guide
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- 230000007246 mechanism Effects 0.000 claims description 22
- 238000000034 method Methods 0.000 description 7
- 238000005495 investment casting Methods 0.000 description 5
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 2
- 230000000149 penetrating effect Effects 0.000 description 2
- 238000005266 casting Methods 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000001746 injection moulding Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 239000004576 sand Substances 0.000 description 1
- 239000002002 slurry Substances 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Abstract
The utility model discloses an aircraft engine turbine guide splicing tool, which comprises the following components: a first disc-like structure; the first disk-shaped structure is provided with a first groove for accommodating the lower part of the single blade wax mould; the central columnar structure is detachably or fixedly arranged in the middle of the first disc-shaped structure, and provides an inner side positioning surface which is matched with a part or all of the inner side surface of the split type wax mould; the second disc-shaped structure is detachably arranged at the upper end of the central columnar structure and is provided with an inner locating ring and an outer locating ring for locating the upper part of the single blade wax mould. The split die disclosed by the utility model has the advantages that the split die is simple in structure, the die is convenient to repair, the cost is low, and the single blade wax die is small in deformation or convenient to correct deformation through an orthosis; the splicing tool can ensure that single wax dies are spliced into the size of the integral guide, and the die repairing is simple and low in cost due to shrinkage rate adjustment.
Description
Technical Field
The utility model relates to the technical field of aeroengines, in particular to a splicing tool for turbine guides of an aeroengine.
Background
The turbine guide is the core hot-end component of an aircraft engine and must be manufactured using precision casting methods due to its structural complexity. The turbine guide belongs to a circular thin-wall structure, and as shown in fig. 13, the difficulty of the precision casting process is size control.
The precision casting process is to use a three-dimensional model of a product to manufacture a metal mould, manufacture a wax mould by means of injection molding, prepare a ceramic mould shell by dipping slurry and spraying sand on the surface of the wax mould for many times, remove the wax mould in the mould shell by high-pressure steam, bake the mould shell to obtain a hollow mould shell with a certain high-temperature strength, and pour molten metal into the mould shell to cool the mould shell to obtain a precision casting. In the main precise process, a plurality of links shrink, namely, the wax material shrinks when the mold presses the wax mold, the mold shell sinter shrinks when the mold shell sinter, the mold shell expands when the mold shell is heated to the pouring temperature, and the molten metal shrinks again when the mold shell is cooled. Therefore, when designing a mold, the shrinkage rate of the three-dimensional model of the product is required to be placed, so that the size of the casting after multiple shrinkage in the precision casting process is ensured to meet the design requirement of the product.
The turbine guide has a complex structure, and if the whole guide is pressed by a wax mould at one time, the mould has a complex structure, high manufacturing cost and long processing period. When the shrinkage rate of the die is not properly designed, the die repairing cost is extremely high, the period is long, the difficulty is high, even the die cannot be repaired, and in addition, the wax die of the turbine guide device which is integrally opened is extremely easy to deform.
Disclosure of Invention
Accordingly, the utility model aims to provide an aircraft engine turbine guide splicing tool.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:
an aircraft engine turbine guide splicing tool, wherein split type wax patterns for an engine turbine guide are spliced, wherein the split type wax patterns comprise a plurality of single blade wax patterns, and the single blade wax patterns surround to form an annular split type wax pattern of the engine turbine guide;
wherein, aeroengine turbine director concatenation frock includes:
a first disc-like structure; the first disk-shaped structure is provided with a first groove for accommodating the lower part of the single blade wax mould;
the central columnar structure is detachably or fixedly arranged in the middle of the first disc-shaped structure, and provides an inner side positioning surface which is matched with a part or all of the inner side surface of the split type wax mould;
the second disc-shaped structure is detachably arranged at the upper end of the central columnar structure and is provided with an inner locating ring and an outer locating ring which are used for locating the upper part of the single blade wax mould.
Foretell aeroengine turbine director concatenation frock, wherein includes: the auxiliary positioning mechanisms each comprise an auxiliary positioning piece, the auxiliary positioning pieces provide an outer positioning surface, the auxiliary positioning pieces can move along the radial direction of the split type wax mould, and the outer positioning surfaces are matched with part or all of the outer side surfaces of the split type wax mould.
The above-mentioned aircraft engine turbine director concatenation frock, wherein, every auxiliary positioning mechanism all includes:
the positioning piece support is fixedly arranged;
the positioning piece moving piece is arranged along the radial direction of the split type wax mould and is slidably connected with the positioning piece bracket;
wherein, auxiliary positioning piece with positioning piece moving part fixed connection.
The above-mentioned aircraft engine turbine director concatenation frock, wherein, every auxiliary positioning mechanism all includes:
and the end part of the locking piece penetrates through the positioning piece support and abuts against the positioning piece moving piece so as to limit the movement of the positioning piece moving piece relative to the positioning piece support.
The aircraft engine turbine guide splicing tool comprises the auxiliary positioning piece, wherein the auxiliary positioning piece comprises a fixing part and a protruding part which are connected with each other, and a diameter reducing part is formed between the fixing part and the protruding part;
the end face of the locating piece moving piece is provided with a locating piece accommodating groove, and the shape of the locating piece accommodating groove is matched with the shape of the fixing part and the shape of at least one part of the protruding part.
The aircraft engine turbine guide splicing tool comprises a first groove inner side wall for positioning the inner side surface of the lower part of the single blade wax mould and a first groove outer side wall for positioning the outer side surface of the lower part of the single blade wax mould.
The aircraft engine turbine director concatenation frock, wherein, first groove inside wall department is equipped with first setting element, first groove outside wall department is equipped with the second setting element.
According to the splicing tool for the turbine guide of the aeroengine, the blind hole is formed in the inner side wall of the first groove, and the first positioning piece is of a columnar structure arranged in the blind hole along the axial direction of the split type wax mould;
the second locating piece is of a block-shaped structure protruding inwards from the outer side wall of the first groove along the radial direction of the split type wax mould.
The aircraft engine turbine guide splicing tool comprises a central columnar structure, wherein the central columnar structure comprises a first part and a second part which are detachably connected with each other, the first part is arranged on the upper surface of the second part, and the outer diameter of the first part is larger than that of the second part to form a central columnar structure step part;
wherein the central columnar structure step portion provides the inner positioning surface.
Foretell aeroengine turbine director concatenation frock, wherein still includes: the turntable mechanism is provided with a rotating shaft, and the first disc-shaped structure is fixedly connected with the rotating shaft.
The utility model adopts the technology, so that compared with the prior art, the utility model has the positive effects that:
(1) The utility model provides a method for separating wax molds of a turbine guider of an aeroengine into split molds and then assembling and welding the split molds into a whole by means of a splicing tool, which has the advantages that: the split die-opening die has the advantages of simple structure, convenient die repair and low cost, and the single blade wax die has small deformation or is convenient for correcting the deformation through the orthosis; the splicing tool can ensure that single wax dies are spliced into the size of the integral guide, and the die repairing is simple and low in cost due to shrinkage rate adjustment.
Drawings
Fig. 1 is a schematic view of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 2 is a schematic view of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 3 is an enlarged schematic view of a portion of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 4 is an enlarged schematic view of a portion of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 5 is a schematic cross-sectional view of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 6 is a schematic view of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 7 is a schematic cross-sectional view of an aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 8 is a schematic view of the bottom surface of a second disk-like structure of the aircraft engine turbine guide splicing tooling of the present utility model.
Fig. 9 is a schematic view of an auxiliary positioning mechanism of an aircraft engine turbine guide splicing tool of the present utility model.
Fig. 10 is an enlarged schematic view of the auxiliary positioning mechanism of the aircraft engine turbine guide splicing tool of the present utility model.
FIG. 11 is a schematic view of a single vane wax pattern of an aircraft engine turbine guide stitching tool of the present utility model.
FIG. 12 is a schematic view of a single vane wax pattern of an aircraft engine turbine guide stitching tool of the present utility model.
FIG. 13 is a schematic view of an aircraft engine turbine pilot of the present utility model.
In the accompanying drawings: a1, a wax pattern inner side plate; a2, an outer side plate of the wax mould; a3, a wax pattern blade part; a4, a step structure of an inner side plate of the wax pattern; a5, limiting the limit structure of the inner side plate of the wax mould; a6, limiting the limit structure of the outer side plate of the wax mould; 1. a first disc-like structure; 11. a first groove; 2. a second disc-like structure; 21. an inner positioning ring; 22. an outer positioning ring; 3. a central columnar structure; 31. a first portion; 32. a second portion; 41. an auxiliary positioning member; 411. a fixing part; 412. a protruding portion; 42. a positioning piece bracket; 43. a positioning member moving member; 44. a locking member; 51. a first positioning member; 52. a second positioning member; 9. a turntable mechanism; 91. a rotating shaft.
Detailed Description
The following description of the embodiments of the present utility model will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the utility model are shown. All other embodiments, which can be made by those skilled in the art based on the embodiments of the utility model without making any inventive effort, are intended to be within the scope of the utility model.
In the description of the present utility model, it should be understood that the terms "upper," "lower," "left," "right," "inner," "outer," "front," "rear," "transverse," "vertical," and the like are used for convenience in describing the present utility model based on the orientation or positional relationship shown in the drawings, and do not denote or imply that the device or element to be referred to must have a specific orientation, and thus should not be construed as limiting the present utility model.
In the present utility model, "horizontal" and "vertical" are used to describe a general positional relationship, and are not strictly "horizontal" or "vertical".
In the present utility model, "inner side" generally means a side toward the center of the annular structure of the wax pattern, and "outer side" generally means a side toward the outer edge of the annular structure of the wax pattern.
Referring to fig. 1 to 12, an aeroengine turbine guide splicing tool of a preferred embodiment is shown and is used for splicing split type wax patterns of an engine turbine guide, wherein the split type wax patterns comprise a plurality of single blade wax patterns, and the single blade wax patterns surround to form a split type wax pattern of an annular engine turbine guide.
Specifically, referring to fig. 11 and 12, the single blade wax pattern includes: a wax pattern inner side plate A1, a wax pattern outer side plate A2, and a wax pattern blade part A3 connecting the wax pattern inner side plate A1 and the wax pattern outer side plate A2.
Specifically, the plurality of single blade wax patterns can be sequentially lapped to form an annular structure, and the annular structure is the wax pattern of the turbine guider of the engine.
The inner side plate A1 of the wax pattern forms an inner ring of a split type wax pattern of the turbine guider of the engine, the outer side plate A2 of the wax pattern forms an outer ring of the split type wax pattern of the turbine guider of the engine, and the blade part A3 of the wax pattern forms a blade between the inner ring and the outer ring of the split type wax pattern of the turbine guider of the engine.
The wax pattern blade part A3 is of a curved surface structure, and the wax pattern blade part A3 is obliquely arranged relative to the axial direction of the split type wax pattern of the turbine guider of the engine.
The wax pattern outer plate A2 has the same extending direction as the wax pattern blade A3, that is, the extending direction of the wax pattern outer plate A2 is also inclined with respect to the axial direction of the split type wax pattern of the engine turbine guide. In other words, the upper end and the lower end of the outer plate A2 of the wax pattern are located at different positions when projected in a plan view.
The single blade wax mould is in an H shape as a whole, and two ends of the wax mould blade part A3 are respectively connected to the middle part of the wax mould inner side plate A1 and the middle part of the wax mould outer side plate A2.
Wherein, the upper end of single blade wax matrix forms the upper shed, and the lower extreme of single blade wax matrix forms the lower shed.
The upper end of the inner side plate A1 of the wax pattern is provided with a step structure A4 of the inner side plate of the wax pattern and a limit structure A5 of the inner side plate of the wax pattern. Specifically, the limiting structure A5 of the inner side plate of the wax pattern is a groove structure, in particular a groove structure with an open lower end or penetrating up and down.
The lower end of the wax pattern outer side plate A2 is provided with a wax pattern outer side plate limiting structure A6. Specifically, the limiting structure A6 of the outer side plate of the wax mould is a groove structure, in particular to a groove structure with an open lower end.
In this embodiment, aircraft engine turbine director concatenation frock includes:
a first disc-like structure 1; the first disc-like structure 1 is provided with a first slot 11 for receiving the lower part of the single blade wax pattern;
the central columnar structure 3 is detachably or fixedly arranged in the middle of the first disc-shaped structure 1, the central columnar structure 3 provides an inner side positioning surface, and the inner side positioning surface is matched with a part or all of the inner side surface of the split type wax mould;
the second disc-shaped structure 2, the second disc-shaped structure 2 is detachably arranged at the upper end of the central columnar structure 3, and the second disc-shaped structure 2 is provided with an inner locating ring 21 and an outer locating ring 22 for locating the upper part of the single blade wax mould.
Wherein the first groove 11 is used for accommodating the lower part of the single blade wax pattern, in particular the lower part of the inner side plate A1 of the wax pattern and the lower part of the outer side plate A2 of the wax pattern.
Specifically, as shown in fig. 5, the first groove 11 limits the inner side wall of the lower end of the inner side plate A1 of the wax pattern and the outer side wall of the lower end of the outer side plate A2 of the wax pattern to position the lower end of the single blade wax pattern.
The inner positioning surface provided by the central columnar structure 3 is used for positioning the inner side surface of the inner side plate A1 of the wax mould so as to position the inner side of the middle part of the single blade wax mould.
Wherein, the inner locating ring 21 and the outer locating ring 22 are inserted into the upper opening of the upper end of the single blade wax mould.
Specifically, referring to fig. 5, the inner sidewall of the inner positioning ring 21 abuts against the outer sidewall of the upper end of the inner side plate A1 of the wax pattern, and the outer sidewall of the outer positioning ring 22 abuts against the inner sidewall of the upper end of the outer side plate A2 of the wax pattern, so as to position the upper end of the single blade wax pattern.
Comprising the following steps: the auxiliary positioning mechanism comprises an auxiliary positioning piece 41, the auxiliary positioning piece 41 provides an outer side positioning surface, the auxiliary positioning piece 41 can move along the radial direction of the split type wax mould, and the outer side positioning surface of the auxiliary positioning piece 41 is matched with a part or all of the outer side surface of the split type wax mould. Preferably, the auxiliary positioning members 41 are arranged substantially in the vertical direction, i.e., the axial direction of the wax pattern.
Specifically, the shape of the outer positioning surface of the auxiliary positioning member 41 matches the shape of the outer surface of the outer plate A2 of the wax pattern, so as to position the outer side of the middle part of the single blade wax pattern.
Further, as a preferred embodiment, each auxiliary positioning mechanism includes: a positioning piece support 42, the positioning piece support 42 is fixedly arranged,
specifically, the positioning member support 42 may be fixed to the upper surface of the first disc structure 1. More specifically, the retainer bracket 42 is positioned in a vertically disposed rod-like configuration.
Further, as a preferred embodiment, each auxiliary positioning mechanism includes: the positioning member moving member 43, the positioning member moving member 43 is disposed along the radial direction of the split type wax pattern, and the positioning member moving member 43 is slidably connected with the positioning member bracket 42.
Specifically, a through hole is formed in the positioning member support 42 along a horizontal direction, and the positioning member moving member 42 is disposed in the through hole and can slide relative to the through hole, so as to adjust a distance between an end portion of the positioning member moving member and an outer wall of the wax pattern.
Further, as a preferred embodiment, the auxiliary positioning member 41 is fixedly connected with the positioning member moving member 43.
Specifically, the auxiliary positioning member 41 is fixed at the end of the positioning member moving member 42, and the positioning member moving member 42 can drive the auxiliary positioning member 41 to move, so that the auxiliary positioning member 41 abuts against the outer surface of the wax mold.
Further, as a preferred embodiment, each auxiliary positioning mechanism includes: and a locking member 44, wherein an end of the locking member 44 penetrates the positioning member support 42 and abuts against the positioning member moving member 43 to limit the movement of the positioning member moving member 43 relative to the positioning member support 42.
Specifically, the locking member 44 is preferably a threaded fastener, and the locking member 44 is screwed into the positioning member holder 42 at a position penetrating the positioning member holder 42, and the locking member 44 is screwed so that an end of the locking member 44 abuts against the positioning member holder 42 to prevent the movement of the positioning member holder 42 relative to the positioning member holder 43.
More specifically, as a preferred embodiment, the upper surface of the positioning member moving member 43 is provided with a long groove, and the end of the locking member 44 is disposed in the long groove, please refer to the long groove structure at the section shown in fig. 5.
Further, as a preferred embodiment, a plurality of auxiliary positioning mechanisms, in particular a plurality of symmetrically arranged auxiliary positioning mechanisms, in particular two pairs, or three pairs, or four pairs of auxiliary positioning mechanisms are included.
Specifically, the auxiliary positioning piece 41 of each auxiliary positioning mechanism is adjusted to integrally adjust the form of the working mold.
Of course, in other embodiments, the number of auxiliary positioning structures may be odd.
Further, as a preferred embodiment, the auxiliary positioning member 41 includes a fixing portion 411 and a protruding portion 412 connected to each other, and a reduced diameter portion is formed between the fixing portion 411 and the protruding portion 412.
Further, as a preferred embodiment, a positioning member accommodating groove is formed at the end surface of the positioning member moving member 43, and the shape of the positioning member accommodating groove of the positioning member moving member 43 matches the shape of the fixing portion 411 and the shape of at least a part of the protruding portion 412.
Specifically, the positioning member receiving groove also has a shape matching the reduced diameter portion for restricting the position of the auxiliary positioning member 41.
Further, as a preferred embodiment, the inner positioning ring 21 and the outer positioning ring 22 are both annular structures. It should be noted that the ring structure is not particularly limited to a closed ring structure, but should also include an open ring structure, i.e., a ring structure having a notch or opening, as long as the general shape thereof forms a ring shape.
Further, as a preferred embodiment, the first groove 11 is provided with a first groove inner side wall for positioning the inner side surface of the lower portion of the single blade wax pattern, and a first groove outer side wall for positioning the outer side surface of the lower portion of the single blade wax pattern.
Specifically, as shown in fig. 5, the first groove inner side wall of the first groove 11 limits the inner side wall of the lower end of the wax pattern inner side plate A1, and the first groove outer side wall of the first groove 11 limits the outer side wall of the lower end of the wax pattern outer side plate A2, so as to position the lower end of the single blade wax pattern.
Further, as a preferred embodiment, a first positioning member 51 is provided at the inner side wall of the first groove, and a second positioning member 52 is provided at the outer side wall of the first groove.
Further, as a preferred embodiment, as shown in fig. 9 and 10, a blind hole is formed at the inner side wall of the first groove, and the first positioning member 51 is a columnar structure disposed in the blind hole along the axial direction of the split wax mold.
Specifically, the shape of the first positioning member 51 is matched with the shape of the wax pattern inner plate limiting structure A5, and the first positioning member 51 is operatively inserted into the interior of the wax pattern inner plate limiting structure A5.
Further, as a preferred embodiment, referring to fig. 9 and 10, the second positioning member 52 is a block structure protruding inward from the outer side wall of the first groove along the radial direction of the split wax pattern, especially a rectangular block structure.
Specifically, the shape of the second positioning member 52 matches the shape of the wax pattern outer side plate retaining structure A6, and the second positioning member 52 is operatively inserted into the interior of the wax pattern outer side plate retaining structure A6.
Preferably, the split type wax pattern is integrally positioned by the first groove 11, the inner positioning surface provided by the central columnar structure 3, the inner positioning ring 21 and the outer positioning ring 22.
Preferably, the positioning of each individual blade wax pattern is performed by a first positioning member 51 and a second positioning member 52.
Further, as a preferred embodiment, the central columnar structure 3 includes a first portion 31 and a second portion 32 detachably connected to each other, the first portion 31 being provided on an upper surface of the second portion 32, an outer diameter of the first portion 31 being larger than an outer diameter of the second portion 32 to form a central columnar structure step;
wherein, the central columnar structure step part provides an inner side locating surface.
Specifically, the shape of the central columnar structure step portion matches the shape of the wax pattern inner side plate step structure A4.
Further, as a preferred embodiment, the method further comprises: the turntable mechanism 9. The turntable mechanism 9 is provided with a rotating shaft 91, and the first disc-shaped structure 1 is fixedly connected with the rotating shaft 91. Rotation of the first disc-like structure 1 is provided by a turntable mechanism 9.
The foregoing description is only illustrative of the preferred embodiments of the present utility model and is not to be construed as limiting the scope of the utility model, and it will be appreciated by those skilled in the art that equivalent substitutions and obvious variations may be made using the description and illustrations of the present utility model, and are intended to be included within the scope of the present utility model.
Claims (10)
1. The splicing tool for the turbine guide of the aero-engine is characterized by being used for splicing split type wax patterns of the turbine guide of the engine, wherein the split type wax patterns comprise a plurality of single blade wax patterns, and the single blade wax patterns surround to form an annular split type wax pattern of the turbine guide of the engine;
wherein, aeroengine turbine director concatenation frock includes:
a first disc-like structure; the first disk-shaped structure is provided with a first groove for accommodating the lower part of the single blade wax mould;
the central columnar structure is detachably or fixedly arranged in the middle of the first disc-shaped structure, and provides an inner side positioning surface which is matched with a part or all of the inner side surface of the split type wax mould;
the second disc-shaped structure is detachably arranged at the upper end of the central columnar structure and is provided with an inner locating ring and an outer locating ring which are used for locating the upper part of the single blade wax mould.
2. The aircraft engine turbine guide splicing tool of claim 1, comprising: the auxiliary positioning mechanisms each comprise an auxiliary positioning piece, the auxiliary positioning pieces provide an outer positioning surface, the auxiliary positioning pieces can move along the radial direction of the split type wax mould, and the outer positioning surfaces are matched with part or all of the outer side surfaces of the split type wax mould.
3. The aircraft engine turbine guide stitching tool as recited in claim 2, wherein each of the auxiliary locating mechanisms includes:
the positioning piece support is fixedly arranged;
the positioning piece moving piece is arranged along the radial direction of the split type wax mould and is slidably connected with the positioning piece bracket;
wherein, auxiliary positioning piece with positioning piece moving part fixed connection.
4. An aircraft engine turbine guide stitching tool as claimed in claim 3 wherein each said auxiliary locating mechanism comprises:
and the end part of the locking piece penetrates through the positioning piece support and abuts against the positioning piece moving piece so as to limit the movement of the positioning piece moving piece relative to the positioning piece support.
5. The aircraft engine turbine guide splicing tool of claim 3, wherein the auxiliary positioning piece comprises a fixing part and a protruding part which are connected with each other, and a reducing part is formed between the fixing part and the protruding part;
the end face of the locating piece moving piece is provided with a locating piece accommodating groove, and the shape of the locating piece accommodating groove is matched with the shape of the fixing part and the shape of at least one part of the protruding part.
6. The aircraft engine turbine guide stitching tool of claim 1 wherein the first slot is provided with a first slot inner side wall for locating an inner side of a lower portion of the single blade wax pattern and a first slot outer side wall for locating an outer side of the lower portion of the single blade wax pattern.
7. The aircraft engine turbine guide splicing tool of claim 6, wherein a first locating piece is arranged at the inner side wall of the first groove, and a second locating piece is arranged at the outer side wall of the first groove.
8. The aircraft engine turbine guide splicing tool of claim 7, wherein a blind hole is formed in the inner side wall of the first groove, and the first positioning piece is a columnar structure arranged in the blind hole along the axial direction of the split type wax pattern;
the second locating piece is of a block-shaped structure protruding inwards from the outer side wall of the first groove along the radial direction of the split type wax mould.
9. The aircraft engine turbine guide splicing tool of claim 1, wherein the central columnar structure comprises a first portion and a second portion detachably connected to each other, the first portion is provided on an upper surface of the second portion, and an outer diameter of the first portion is larger than an outer diameter of the second portion to form a central columnar structure step;
wherein the central columnar structure step portion provides the inner positioning surface.
10. The aircraft engine turbine guide stitching tool of claim 1, further comprising: the turntable mechanism is provided with a rotating shaft, and the first disc-shaped structure is fixedly connected with the rotating shaft.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322219932.2U CN220636228U (en) | 2023-08-17 | 2023-08-17 | Splicing tool for turbine guide of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202322219932.2U CN220636228U (en) | 2023-08-17 | 2023-08-17 | Splicing tool for turbine guide of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN220636228U true CN220636228U (en) | 2024-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202322219932.2U Active CN220636228U (en) | 2023-08-17 | 2023-08-17 | Splicing tool for turbine guide of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN220636228U (en) |
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2023
- 2023-08-17 CN CN202322219932.2U patent/CN220636228U/en active Active
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