CN210650483U - Tool for detaching turbine shaft of helicopter engine - Google Patents
Tool for detaching turbine shaft of helicopter engine Download PDFInfo
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- CN210650483U CN210650483U CN201921010438.2U CN201921010438U CN210650483U CN 210650483 U CN210650483 U CN 210650483U CN 201921010438 U CN201921010438 U CN 201921010438U CN 210650483 U CN210650483 U CN 210650483U
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- gantry support
- cushion block
- universal
- clamping plate
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Abstract
The utility model provides a extracting tool of helicopter engine's turbine shaft, include: longmen support, adjustment cushion, arc cardboard, afterburning horizontal pole, elongated ejector pin, ejector pin head, general bolt, general nut, wherein: the gantry support is of an n-shaped structure; the gantry support comprises 2 end parts and 1 connecting part; adjusting cushion blocks are respectively arranged at 2 end parts of the gantry support; the adjusting cushion block is connected with the arc-shaped clamping plate through a universal bolt and a universal nut; a stress application cross rod penetrates through the connecting part of the gantry support; the stress application cross bar is connected with a long ejector rod; the end part of the long ejector rod is provided with an ejector rod head. The embodiment of the utility model provides a simple structure, convenient to use dismantles helicopter engine turbine shaft.
Description
Technical Field
The utility model relates to an aeronautical machinery processing technology field especially relates to a extracting tool of turbine shaft of machine engine rises.
Background
When the helicopter engine is repaired and maintained, the turbine shaft of the engine needs to be disassembled, but the universal tool cannot be disassembled due to the particularity of the turbine shaft of the helicopter engine. At present, the disassembly is mainly realized by manual knocking of a polished rod shaft, which is easy to be stressed unevenly, so that a turbine shaft of a helicopter engine is damaged. A helicopter engine turbine shaft mounting and dismounting tool is needed for dismounting.
SUMMERY OF THE UTILITY MODEL
The utility model aims at: the tool for mounting and dismounting the power turbine shaft is simple in structure and convenient to use.
The utility model provides a extracting tool of helicopter engine's turbine shaft, include:
longmen support, adjustment cushion, arc cardboard, afterburning horizontal pole, elongated ejector pin, ejector pin head, general bolt, general nut, wherein:
the gantry support is of an n-shaped structure;
the gantry support comprises an end part and a connecting part;
adjusting cushion blocks are respectively arranged at the end parts of the gantry support;
the adjusting cushion block is connected with the arc-shaped clamping plate through a universal bolt and a universal nut;
a stress application cross rod penetrates through the connecting part of the gantry support;
the stress application cross bar is connected with a long ejector rod;
the end part of the long ejector rod is provided with an ejector rod head.
In some examples, the gantry support comprises: the mounting structure comprises a bracket, a reinforcing block, a mounting bottom plate, a threaded hole and a through hole;
the mounting baseplate is configured to be placed on a platform of a helicopter engine;
a threaded hole is formed in the connecting part of the gantry support;
a long ejector rod penetrates through the threaded hole;
the universal bolt is arranged in the through hole.
In some examples, the adjustment cushion block is of a rectangular structure, is arranged between the mounting base plate and the arc-shaped clamping plate, and is configured to adjust the distance;
the adjusting cushion block is provided with a hole, and a universal bolt is arranged in the through hole.
In some examples, the arc-shaped clamping plate is a rectangular arc-shaped structure and is placed below the adjusting cushion block.
The arc-shaped piece on the arc-shaped clamping plate avoids the arc-shaped platform of the helicopter engine and is clamped below the arc-shaped platform;
the stress application cross rod increases torque when a turbine shaft of the engine is disassembled;
the long ejector pin is the step shaft structure, includes: a threaded shaft and an optical axis; a stress application cross rod is arranged in the through hole;
the threaded shaft passes through a threaded hole of the gantry support;
the optical axis is inserted into the head of the ejector by interference fit.
In some examples, the head is a soft material.
In some examples, the universal bolt and the universal nut pass through the hole to assemble the gantry support, the adjusting cushion block and the arc-shaped clamping plate together.
In some examples, the gantry mount is placed on the helicopter engine platform when the engine turbine shaft is removed;
fixing a universal adjusting universal bolt and a universal nut on a helicopter engine platform;
the long ejector rod is rotated, and the turbine shaft of the engine is ejected out of the engine compartment through the ejector rod head.
The embodiment of the utility model provides a simple structure, convenient to use dismantles helicopter engine turbine shaft.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic structural view of a tool for removing a turbine shaft of a helicopter engine according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a gantry support 1 according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an adjusting pad 2 according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of the arc-shaped clamping plate 3 according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of the push rod 5 according to an embodiment of the present invention.
The device comprises a gantry support 1, an adjusting cushion block 2, an arc-shaped clamping plate 3, a stress application cross rod 4, a long ejector rod 5, an ejector rod head 6, a universal bolt 7, a universal nut 8, a support 1-1, a reinforcing block 1-2, an installation bottom plate 1-3, threaded holes 1-4, through holes 1-5, cushion block through holes 2-1, an arc-shaped piece 3-1, a threaded shaft 5-1 and an optical shaft 5-2
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the drawings in the embodiments of the present invention are combined below to clearly and completely describe the technical solutions in the embodiments of the present invention. It is to be understood that the embodiments described are only some of the embodiments of the present invention, and not all of them. Based on the embodiments in the present invention, all other embodiments obtained by a person of ordinary skill in the art without creative work belong to the protection scope of the present invention.
Features and illustrative embodiments of various aspects of the invention are described in detail below. In the following detailed description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The present invention is in no way limited to any specific arrangement and method set forth below, but rather covers any improvement, replacement or modification of structures, methods, devices without departing from the spirit of the invention. In the drawings and the following description, well-known structures and techniques are not shown to avoid unnecessarily obscuring the present invention.
It should be noted that, in case of conflict, the features of the embodiments and examples of the present invention may be combined with each other, and the respective embodiments may be mutually referred and cited. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
Referring to fig. 1, 2, 3, 4, the tool for removing a turbine shaft of a helicopter engine may comprise: the device comprises a gantry support 1, an adjusting cushion block 2, an arc-shaped clamping plate 3, a stress application cross rod 4, a long ejector rod 5, an ejector rod head 6, a universal bolt 7 and a universal nut 8; the gantry support 1 is a gantry supporting structure, wherein a support 1-1, a reinforcing block 1-2 and a mounting bottom plate 1-3 adopt a welding structure, the mounting bottom plate 1-3 is used for being placed on a helicopter engine platform, a threaded hole 1-4 is used for supporting a long ejector rod 5, and a through hole 1-5 is used for passing through a universal bolt 7; the adjusting cushion block 2 is of a rectangular structure, is arranged between the mounting base plate 1-3 and the arc-shaped clamping plate 3 and is used for adjusting the distance, a cushion block through hole 2-1 is used for the universal bolt 7, the arc-shaped clamping plate 3 is arranged below the adjusting cushion block 2, and the arc-shaped clamping plate 3-1 is used for avoiding an arc-shaped platform of a helicopter engine and is clamped below the platform; the stressing crossbar 4 is used to increase the torque when the engine is dismounted.
Fig. 5 is a schematic structural diagram of the push rod 5 according to an embodiment of the present invention.
As shown in figure 5, the long ejector rod 5 is of a stepped shaft structure and consists of a threaded shaft 5-1 and an optical shaft 5-2, wherein the threaded shaft 5-1 is used for being inserted into an ejector rod head 6 through a stress application cross rod 4, the threaded shaft 5-1 passes through a threaded hole 1-4 of the gantry support 1, the optical shaft 5-2 is in interference fit, the ejector rod head 6 is made of soft materials and avoids damaging a turbine shaft of an engine, and the gantry support 1, the adjusting cushion block 2 and the arc-shaped clamping plate 3 are assembled together through holes by a universal bolt 7 and a universal nut 8.
The utility model discloses an operation application method of engine turbine shaft installation extracting tool can include following several steps:
the method comprises the following steps: placing the gantry support 1 on a helicopter engine platform, as shown in fig. 3;
step two: fixing the gantry support 1 on a helicopter engine platform by using a universal adjusting universal bolt 7 and a universal nut 8;
step three: by rotating the elongated carrier rod 5, the engine turbine shaft is pushed out of the engine compartment by the carrier rod head 6.
In some embodiments, the dismounting tool for the turbine shaft of the helicopter engine comprises a gantry support 1, an adjusting cushion block 2, an arc-shaped clamping plate 3, a stress application cross rod 4, a long ejector rod 5, an ejector rod head 6, a universal bolt 7 and a universal nut 8; the gantry support 1 is a gantry supporting structure, wherein a support 1-1, a reinforcing block 1-2 and a mounting bottom plate 1-3 adopt a welding structure, the mounting bottom plate 1-3 is used for being placed on a helicopter engine platform, a threaded hole 1-4 is used for supporting a long ejector rod 5, and a through hole 1-5 is used for passing through a universal bolt 7; the adjusting cushion block 2 is of a rectangular structure, is arranged between the mounting base plate 1-3 and the arc-shaped clamping plate 3 and is used for adjusting the distance, the cushion block through hole 2-1 is used for passing through the universal bolt 7, the arc-shaped clamping plate 3 is of a rectangular arc-shaped structure and is arranged below the adjusting cushion block 2, and the arc 3-1 is used for avoiding an arc-shaped platform of a helicopter engine and is clamped below the platform; the stress application cross rod 4 is used for increasing torque when an engine is disassembled, the long ejector rod 5 is of a stepped shaft structure and consists of a threaded shaft 5-1 and an optical shaft 5-2, wherein the threaded shaft 5-1 is used for passing through the stress application cross rod 4, the threaded shaft 5-1 passes through a threaded hole 1-4 of the gantry support 1, the optical shaft 5-2 is inserted into the ejector rod head 6 in an interference assembly mode, the ejector rod head 6 is made of soft materials and avoids damaging a turbine shaft of the engine, and the gantry support 1, the adjusting cushion block 2 and the arc-shaped clamping plate 3 are assembled together through holes of a universal bolt 7 and a universal nut 8.
The utility model provides a extracting tool of helicopter engine's turbine shaft, include: the device comprises a gantry support 1, an adjusting cushion block 2, an arc-shaped clamping plate 3, a stress application cross rod 4, a long ejector rod 5, an ejector rod head 6, a universal bolt 7 and a universal nut 8. Wherein: the gantry support 1 is of an n-shaped structure; the gantry support 1 comprises 2 end parts and 1 connecting part; adjusting cushion blocks 2 are respectively arranged at 2 end parts of the gantry support 1; the adjusting cushion block 2 is connected with the arc-shaped clamping plate 3 through a universal bolt 7 and a universal nut 8; a stress application cross rod 4 penetrates through the connecting part of the gantry support 1; the stress application cross rod 4 is connected with a long ejector rod 5; the end part of the long mandril 5 is provided with a mandril head 6.
In some embodiments, gantry support 1 comprises: the device comprises a support 1-1, a reinforcing block 1-2, a mounting base plate 1-3, a threaded hole 1-4 and a through hole 1-5; the mounting baseplate 1-3 is configured to be placed on a platform of a helicopter engine; threaded holes 1-4 are arranged on the connecting part of the gantry bracket 1; a long ejector rod 5 penetrates through the threaded holes 1-4; the universal bolts 7 are arranged in the through holes 1-5.
In some embodiments, the adjusting pad 2 is a rectangular structure, is placed between the mounting base plates 1-3 and the arc-shaped clamping plate 3, and is configured to adjust the distance;
the adjusting cushion block 2 is provided with a cushion block through hole 2-1, and a universal bolt 7 is arranged in the cushion block through hole 2-1.
In some embodiments, the arc-shaped clamping plate 3 is a rectangular arc-shaped structure and is placed below the adjusting cushion block 2. The arc-shaped piece 3-1 on the arc-shaped clamping plate 3 avoids the arc-shaped platform of the helicopter engine and is clamped below the arc-shaped platform; the stress application cross rod 4 increases torque when a turbine shaft of an engine is disassembled; the long ejector pin 5 is of a stepped shaft structure, including: a threaded shaft 5-1 and an optical axis 5-2; a stress application cross rod 4 is arranged in the threaded shaft 5-1; the threaded shaft 5-1 passes through a threaded hole 1-4 of the gantry support 1; the optical axis 5-2 is interference fit inserted into the head 6.
In some embodiments, the head 6 is a soft material.
In some embodiments, the gantry support 1, the adjusting cushion block 2 and the arc-shaped clamping plate 3 are assembled together through holes by the universal bolts 7 and the universal nuts 8.
In some embodiments, gantry support 1 is placed on the helicopter engine platform when the engine turbine shaft is disassembled; fixing the gantry support 1 on a helicopter engine platform by using a universal adjusting universal bolt 7 and a universal nut 8; by rotating the elongated carrier rod 5, the engine turbine shaft is pushed out of the engine compartment by the carrier rod head 6.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of various equivalent modifications or substitutions within the technical scope of the present invention, and these modifications or substitutions should be covered within the protection scope of the present invention.
Claims (6)
1. A tool for removing a turbine shaft of a helicopter engine, comprising:
longmen support (1), adjustment cushion (2), arc cardboard (3), afterburning horizontal pole (4), long ejector pin (5), ejector pin head (6), general bolt (7), general nut (8), wherein:
the gantry support (1) is of an n-shaped structure;
the gantry support (1) comprises 2 end parts and 1 connecting part;
adjusting cushion blocks (2) are respectively arranged at 2 ends of the gantry support (1);
the adjusting cushion block (2) is connected with the arc-shaped clamping plate (3) through a universal bolt (7) and a universal nut (8);
a stress application cross rod (4) penetrates through the connecting part of the gantry support (1);
the stress application cross rod (4) is connected with a long ejector rod (5);
the end part of the long ejector rod (5) is provided with an ejector rod head (6).
2. The removal tool of claim 1, wherein:
gantry support (1) includes: the device comprises a support (1-1), a reinforcing block (1-2), a mounting base plate (1-3), threaded holes (1-4) and through holes (1-5);
the mounting baseplate (1-3) is configured to be placed on a platform of a helicopter engine;
threaded holes (1-4) are formed in the connecting part of the gantry support (1);
a long ejector rod (5) penetrates through the threaded holes (1-4);
the universal bolt (7) is arranged in the through hole (1-5).
3. The removal tool of claim 1, wherein:
the adjusting cushion block (2) is of a rectangular structure, is arranged between the mounting bottom plate (1-3) and the arc-shaped clamping plate (3), and is configured to adjust the distance;
the adjusting cushion block (2) is provided with a cushion block through hole (2-1), and a universal bolt (7) is arranged in the cushion block through hole (2-1).
4. The removal tool of claim 1, wherein:
the arc-shaped clamping plate (3) is of a rectangular arc-shaped structure and is placed below the adjusting cushion block (2);
an arc-shaped piece (3-1) on the arc-shaped clamping plate (3) avoids an arc-shaped platform of the helicopter engine and is clamped below the arc-shaped platform;
the stress application cross rod (4) increases the moment when the turbine shaft of the engine is disassembled;
elongated ejector pin (5) are the step shaft structure, include: a threaded shaft (5-1) and an optical axis (5-2); a stress application cross rod (4) is arranged in the threaded shaft (5-1);
the threaded shaft (5-1) passes through a threaded hole (1-4) of the gantry support (1);
the optical axis (5-2) is inserted into the head (6) in an interference fit.
5. The removal tool of claim 1, wherein:
the ejector head (6) is made of soft material.
6. The removal tool of any one of claims 1-5, wherein:
the gantry support (1), the adjusting cushion block (2) and the arc-shaped clamping plate (3) are assembled together through holes of the universal bolt (7) and the universal nut (8).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921010438.2U CN210650483U (en) | 2019-07-01 | 2019-07-01 | Tool for detaching turbine shaft of helicopter engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921010438.2U CN210650483U (en) | 2019-07-01 | 2019-07-01 | Tool for detaching turbine shaft of helicopter engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210650483U true CN210650483U (en) | 2020-06-02 |
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ID=70836287
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921010438.2U Active CN210650483U (en) | 2019-07-01 | 2019-07-01 | Tool for detaching turbine shaft of helicopter engine |
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| Country | Link |
|---|---|
| CN (1) | CN210650483U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113770967A (en) * | 2021-09-16 | 2021-12-10 | 攀钢集团西昌钢钒有限公司 | Device for disassembling hammer head component of crusher |
-
2019
- 2019-07-01 CN CN201921010438.2U patent/CN210650483U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113770967A (en) * | 2021-09-16 | 2021-12-10 | 攀钢集团西昌钢钒有限公司 | Device for disassembling hammer head component of crusher |
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