CN217860960U - A diversified fixing device for aeroengine gas turbine rotor - Google Patents
A diversified fixing device for aeroengine gas turbine rotor Download PDFInfo
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- CN217860960U CN217860960U CN202221501305.7U CN202221501305U CN217860960U CN 217860960 U CN217860960 U CN 217860960U CN 202221501305 U CN202221501305 U CN 202221501305U CN 217860960 U CN217860960 U CN 217860960U
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- turbine rotor
- connecting plate
- gas turbine
- fixing
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Abstract
The utility model discloses a multi-azimuth fixing device for an aircraft engine gas turbine rotor, which comprises a first connecting plate, a second connecting plate, a hoop component and a fixing plate; the first connecting plate is perpendicular to the second connecting plate, the fixing plate is arranged on the end face, far away from the first connecting plate, of the second connecting plate, and a through hole for connecting the clamp assembly is formed in the first connecting plate; the hoop component is provided with a fixing part for locking the turbine rotor; through carrying out the centre gripping with fixed plate and external vice in this scheme, make first connecting plate and second connecting plate unsettled, when fixing turbine rotor on clamp subassembly, unsettled whole fixing device can have more operation spaces, fix turbine rotor through clamp subassembly, prevent that turbine rotor from removing, under the condition of restricting turbine rotor, can be through the clearance fit condition of the accurate measurement rotor of the external magnetic force table frame of cooperation and the outer steel bushing nozzle assembly of bearing.
Description
Technical Field
The utility model belongs to the technical field of the assembly of engine parts and specifically relates to a diversified fixing device for aeroengine gas turbine rotor.
Background
The aviation gas turbine starter is a small-sized airplane Auxiliary Power device (APU for short) with an upward exhaust port, is mainly used for ground starting, cold transfer, false start, unsealing and oil sealing of a main engine, can also work in a Power assembly state, and provides energy required for ground maintenance.
Due to the importance of aviation products, the processes of disassembly, assembly, repair, maintenance, cleaning and the like are required to be carried out every certain operation period. Due to the particularity and structural complexity of the aircraft gas turbine starter, certain difficulties are brought to cleaning, decomposition, fault detection, repair, assembly and test.
For example: the function of the gas turbine is to convert the energy of the gas stream into mechanical energy that drives the compressor and accessories mounted on the accessory drive case, mounted behind the combustion chamber. The gas turbine rotor is an important component of the gas turbine and is supported on two fulcrums, wherein the front fulcrum is a ball bearing, and the rear fulcrum is a roller bearing.
In the assembling process, parts such as a bearing, a distance sleeve and the like positioned on the power turbine rotor are difficult to ensure axial clearance fit with the rotor shaft during assembling, and particularly differential measurement is carried out on relative run-out between an outer steel sleeve of the bearing and the rotor shaft.
SUMMERY OF THE UTILITY MODEL
The utility model discloses aim at: to above-mentioned problem, provide a diversified fixing device for aeroengine gas turbine rotor, solved prior art assembly process, be located parts such as bearing, distance cover on the power turbine rotor and be difficult to guarantee when the assembly with the axial clearance fit's of rotor shaft problem.
The utility model discloses a realize through following scheme:
a multi-orientation fixture for an aircraft engine gas turbine rotor: the clamp comprises a first connecting plate, a second connecting plate, a clamp assembly and a fixing plate; the first connecting plate is perpendicular to the second connecting plate, the fixing plate is arranged on the end face, far away from the first connecting plate, of the second connecting plate, and a through hole for connecting the hoop component is formed in the first connecting plate; the hoop component is provided with a fixing part for locking the turbine rotor.
Based on above-mentioned a diversified fixing device's structure for aeroengine gas turbine rotor, first connecting plate is provided with first connecting hole group and second connecting hole group, the line perpendicular to second hole group's of first connecting hole group connection, the center of first connecting hole group and the center collineation of second hole group.
Based on the structure of the multidirectional fixing device for the aircraft engine gas turbine rotor, the distance of the connecting line between the first connecting hole groups and the distance of the connecting line between the second connecting hole groups are equal.
Based on the structure of the multidirectional fixing device for the aero-engine gas turbine rotor, the connecting lines of the first connecting hole groups are perpendicular to the second connecting plate, and the connecting lines of the second connecting hole groups are parallel to the second connecting plate.
Based on the structure of the multidirectional fixing device for the aero-engine gas turbine rotor, the hoop component comprises a connecting plate, a connecting column, a first locking piece, a second locking piece and a locking nut; the spliced pole perpendicular to connecting plate sets up, be provided with on the connecting plate with first connecting hole group or second connecting hole group assorted connecting hole, the setting of second locking piece and first locking piece disconnect-type.
Based on the structure of the multidirectional fixing device for the aero-engine gas turbine rotor, the first locking piece is perpendicular to the connecting column, an arc-shaped groove matched with a turbine rotor shell is formed in the first locking piece, and locking holes for fixing are formed in two ends of the first locking piece;
based on above-mentioned a diversified fixing device's structure for aeroengine gas turbine rotor, be provided with on the second locking piece with turbine rotor shell assorted arc wall, and second locking piece both ends are provided with and are used for fixed locking hole.
Based on above-mentioned a diversified fixing device's structure for aeroengine gas turbine rotor, central point puts and is provided with the spacing groove on the second connecting portion, the spacing groove both sides are provided with the fixed orifices, the fixed orifices sets up along the spacing groove symmetry.
Based on the structure of the multidirectional fixing device for the aircraft engine gas turbine rotor, the size of the limiting groove is matched with the end part of the turbine rotor.
Based on above-mentioned a diversified fixing device's structure for aeroengine gas turbine rotor, the fixed plate setting is put at second connecting plate length direction's central point, and the fixed plate is perpendicular to the setting of second connecting plate.
To sum up, owing to adopted above-mentioned technical scheme, the beneficial effects of the utility model are that:
1. according to the scheme, the fixing plate and an external vice are clamped, the first connecting plate and the second connecting plate are suspended, when the turbine rotor is fixed on the hoop component, the suspended whole fixing device can have more operation spaces, the turbine rotor is fixed through the hoop component, the turbine rotor is prevented from moving, and under the condition that the turbine rotor is limited, the clearance fit condition of the rotor and the bearing outer steel sleeve nozzle component can be accurately measured by matching with an external magnetic gauge frame, and the fit size condition between the fitting surfaces of the rotor can be accurately measured; and meanwhile, when the turbine rotor is fixed, the nozzle assembly and the square head screw can be conveniently and quickly disassembled.
2. The state after the assembly spare part can effectively be inspected to this scheme, improves maintenance operating personnel work efficiency, reduces the maintenance damage rate, has reduceed maintenance quality risk, has increased the safety in production operability. The device is simple and reasonable in structure and convenient to operate, and effectively improves the production efficiency and the applicability and the conformity during working.
Drawings
FIG. 1 is a schematic view of the overall side view structure of the present invention;
FIG. 2 is a schematic view of the whole three-dimensional structure of the present invention
Fig. 3 is a schematic structural view of the first connecting plate of the present invention;
FIG. 4 is a schematic structural view of a second connecting plate according to the present invention;
fig. 5 is a schematic structural view of a fixing plate of the present invention;
description of the drawings: 1. a first connecting plate; 2. a second connecting plate; 3. a clamp assembly; 4. a fixing plate; 5. a turbine rotor; 11. a first group of connecting holes; 12. a second group of connecting holes; 21. a limiting groove; 22. a fixing hole; 31. a connecting plate; 32. connecting columns; 33. a first locking member; 34. a second locking member; 35. locking the nut; 36. an arc-shaped slot; 37. a locking hole.
Detailed Description
All of the features disclosed in this specification, or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations of features and/or steps that are mutually exclusive.
Any feature disclosed in this specification (including any accompanying claims, abstract) may be replaced by alternative features serving equivalent or similar purposes, unless expressly stated otherwise. That is, unless expressly stated otherwise, each feature is only an example of a generic series of equivalent or similar features.
In the description of the present invention, it should be understood that the terms "upper", "lower", "left", "right", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplification of the description, but do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present invention.
Furthermore, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or to implicitly indicate the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature.
Example 1
As shown in fig. 1 to 5, the utility model provides a technical solution:
a multi-orientation fixture for an aircraft engine gas turbine rotor 5 includes at least, but is not limited to, a first connection plate 311, a second connection plate 312, a yoke assembly 3, and a fixture plate 4; the first connecting plate 311 is arranged perpendicular to the second connecting plate 312, the fixing plate 4 is arranged on the end surface, far away from the first connecting plate 311, of the second connecting plate 312, and a through hole for connecting the hoop component 3 is formed in the first connecting plate 311; the yoke assembly 3 is provided with a fixing portion for locking the turbine rotor 5.
Based on the structure, the fixing plate 4 is clamped by an external vice, the first connecting plate 311 and the second connecting plate 312 are suspended, when the turbine rotor 5 is fixed on the hoop component 3, the suspended whole fixing device can have more working space, the turbine rotor 5 is fixed through the hoop component 3, the turbine rotor 5 is prevented from moving, and under the condition of limiting the turbine rotor 5, the clearance fit condition of the rotor and the bearing outer steel sleeve nozzle component and the fit size condition between the fitting surfaces of the rotor can be accurately measured by matching with an external magnetic gauge frame; simultaneously, when the turbine rotor 5 is fixed, the nozzle assembly and the square head screw can be conveniently and quickly disassembled.
As an example, the first connection plate 311 is provided with a first connection hole group 11 and a second connection hole group 12, a connection line of the first connection hole group 11 is perpendicular to a connection of the second connection hole group, and a center of the first connection hole group 11 is collinear with a center of the second connection hole group, and a distance of the connection line between the first connection hole group 11 and a distance of the connection line between the second connection hole group 12 are set to be equal.
In a preferred embodiment, the connecting lines of the first connecting hole groups 11 are arranged perpendicular to the second connecting plate 312, and the connecting lines of the second connecting hole groups 12 are arranged parallel to the second connecting plate 312.
Based on the above structure, the first and second connection hole groups 11 and 12 perpendicular to each other are provided, so that the clip assembly 3 can be selected when being fixed, and the clip assembly 3 is vertically fixed or the clip assembly 3 is horizontally fixed. The present embodiment is mainly exemplified by vertical fixing.
By way of example, the clip assembly 3 includes a web 31, a connecting post 32, a first locking member 33, a second locking member 34, and a lock nut 35; the connecting column 32 is arranged perpendicular to the connecting plate 31, and the connecting plate 31 is provided with a connecting hole matched with the first connecting hole group 11 or the second connecting hole group 12 and is fixed with the first connecting plate 311 through the connecting hole; the second locking member 34 is provided separately from the first locking member 33.
The first locking piece 33 is perpendicular to the connecting column 32, an arc-shaped groove 36 matched with the shell of the turbine rotor 5 is formed in the first locking piece 33, and locking holes 37 for fixing are formed in two ends of the first locking piece 33;
the second locking piece 34 is similar to the first locking piece 33 in arrangement, an arc-shaped groove 36 matched with the shell of the turbine rotor 5 is arranged on the second locking piece 34, and locking holes 37 for fixing are arranged at two ends of the second locking piece 34.
Based on above-mentioned structure, according to operational environment, carry out horizontal locking or vertical locking with first connecting plate 311 with connecting plate 31, then the second locking piece 34 through the disconnect-type setting cooperates first locking piece 33, locks turbine rotor 5 in arc-shaped groove 36, guarantees that turbine rotor 5's location is accurate, keeps vertical or keep the level, makes things convenient for follow-up operation flow.
As an example, a limiting groove 21 is formed at a central position on the second connecting portion, fixing holes 22 are formed at both sides of the limiting groove 21, and the fixing holes 22 are symmetrically formed along the limiting groove 21.
As a preferred embodiment, the limiting groove 21 is dimensioned to fit the end of the turbine rotor 5.
Based on above-mentioned structure, be connected fixed plate 4 and second connecting plate 312 through fixed orifices 22, simultaneously when turbine rotor 5 is being fixed by the vertical spacing of clamping hoop component 3, spacing groove 21 can be fixed turbine rotor 5's tip, makes whole device more firm to turbine rotor 5's fixed, can carry out the operation that becomes more meticulous.
As an example, the fixing plate 4 is disposed at a central position in a length direction of the second connecting plate 312, and the fixing plate 4 is disposed perpendicular to the second connecting plate 312, and the fixing plate 4 is locked with the fixing hole 22 by a bolt.
Based on above-mentioned structure, fixed plate 4 through perpendicular setting is connected with outside vice, sets up fixed plate 4 simultaneously at second connecting plate 312 length direction's central point and puts, is located vertical fixation turbine rotor 5 the time directly under promptly, so can guarantee the stability of mechanics distribution, makes the centre gripping dynamics distribute evenly.
Through this device, can effectively inspect the state behind the assembly spare part, improve maintenance operating personnel work efficiency, reduce the maintenance damage rate, reduce maintenance quality risk, increase the safety in production operability. The device is simple and reasonable in structure and convenient to operate, and effectively improves the production efficiency and the applicability and the conformity during working.
The above description is only exemplary of the present invention and should not be taken as limiting the scope of the present invention, as any modifications, equivalents, improvements and the like made within the spirit and principles of the present invention are intended to be included within the scope of the present invention.
Claims (10)
1. A diversified fixing device for aeroengine gas turbine rotor which characterized in that: the clamp comprises a first connecting plate, a second connecting plate, a clamp assembly and a fixing plate; the first connecting plate is perpendicular to the second connecting plate, the fixing plate is arranged on the end face, far away from the first connecting plate, of the second connecting plate, and a clamp assembly connecting through hole is formed in the first connecting plate; the hoop component is provided with a fixing part for locking the turbine rotor.
2. The multi-orientation fixture for an aircraft engine gas turbine rotor as claimed in claim 1, wherein: the first connecting plate is provided with a first connecting hole group and a second connecting hole group, the connecting line of the first connecting hole group is perpendicular to the connection of the second connecting hole group, and the center of the first connecting hole group is collinear with the center of the second connecting hole group.
3. The multi-azimuth fixture for an aircraft engine gas turbine rotor as claimed in claim 2, wherein: and the distance of the connecting lines between the first connecting hole groups is equal to the distance of the connecting lines between the second connecting hole groups.
4. The multi-orientation fixture for an aircraft engine gas turbine rotor as claimed in claim 3, wherein: the connecting line of the first connecting hole group is perpendicular to the second connecting plate, and the connecting line of the second connecting hole group is parallel to the second connecting plate.
5. The multi-orientation fixture for an aircraft engine gas turbine rotor as claimed in claim 4, wherein: the clamp component comprises a connecting plate, a connecting column, a first locking piece, a second locking piece and a locking nut; the spliced pole perpendicular to connecting plate sets up, be provided with on the connecting plate with first connecting hole group or second connecting hole group assorted connecting hole, the second locking piece sets up with first locking piece disconnect-type.
6. An multi-orientation fixture for an aircraft engine gas turbine rotor according to claim 5, wherein: the first locking part is perpendicular to the connecting column, an arc-shaped groove matched with the turbine rotor shell is formed in the first locking part, and locking holes used for fixing are formed in the two ends of the first locking part.
7. An multi-orientation fixture for an aircraft engine gas turbine rotor according to claim 6, wherein: the second locking piece is provided with an arc-shaped groove matched with the turbine rotor shell, and locking holes for fixing are formed in two ends of the second locking piece.
8. The multi-orientation fixture for an aircraft engine gas turbine rotor as claimed in claim 7, wherein: the second connecting plate is provided with a limiting groove in the center, fixing holes are formed in two sides of the limiting groove, and the fixing holes are symmetrically formed along the limiting groove.
9. The multi-orientation fixture for an aircraft engine gas turbine rotor as claimed in claim 8, wherein: the size of the limiting groove is matched with the end part of the turbine rotor.
10. The multi-azimuth fixture for an aircraft engine gas turbine rotor according to claim 9, wherein: the fixed plate is arranged at the center of the second connecting plate in the length direction and is perpendicular to the second connecting plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221501305.7U CN217860960U (en) | 2022-06-16 | 2022-06-16 | A diversified fixing device for aeroengine gas turbine rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221501305.7U CN217860960U (en) | 2022-06-16 | 2022-06-16 | A diversified fixing device for aeroengine gas turbine rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217860960U true CN217860960U (en) | 2022-11-22 |
Family
ID=84095322
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221501305.7U Active CN217860960U (en) | 2022-06-16 | 2022-06-16 | A diversified fixing device for aeroengine gas turbine rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217860960U (en) |
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2022
- 2022-06-16 CN CN202221501305.7U patent/CN217860960U/en active Active
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