CN116276002A - Inner nut dismounting structure of aero-engine rotor journal disc cavity - Google Patents
Inner nut dismounting structure of aero-engine rotor journal disc cavity Download PDFInfo
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- CN116276002A CN116276002A CN202211522240.9A CN202211522240A CN116276002A CN 116276002 A CN116276002 A CN 116276002A CN 202211522240 A CN202211522240 A CN 202211522240A CN 116276002 A CN116276002 A CN 116276002A
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- support
- journal
- disc cavity
- rotor
- wrench
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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
- B23P19/00—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes
- B23P19/04—Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts
- B23P19/06—Screw or nut setting or loosening machines
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- Mechanical Engineering (AREA)
- Hand Tools For Fitting Together And Separating, Or Other Hand Tools (AREA)
Abstract
The application belongs to aeroengine rotor axle journal dish intracavity nut dismouting technical field, concretely relates to aeroengine rotor axle journal dish intracavity nut dismouting structure, include: the support plate is connected to the stator case and is provided with a perforation; the connecting rod penetrates through the through hole and extends into the rotor journal disc cavity; the support is connected with one end of the connecting rod extending into the rotor journal disc cavity; the support cylinder is connected to the support; the wrench shaft penetrates through the supporting cylinder and is connected with the supporting cylinder in a matched manner through spiral threads; the wrench head is connected to one end of the wrench shaft and is provided with a wrench hole; the wrench hole is clamped on a nut which is connected with the end part of the rotor shaft neck and the connecting edge of the drum barrel; the hydraulic cylinder is connected to the supporting cylinder; the transmission arm is connected to the hydraulic rod of the hydraulic cylinder and is hinged with the other end of the wrench shaft; the handle is hinged to the other end of the connecting rod and is provided with a strip-shaped hole; the support block is connected to the support plate; the rolling rod is arranged in the strip-shaped hole and connected to the supporting block.
Description
Technical Field
The application belongs to the technical field of disassembly and assembly of nuts in a shaft neck disc cavity of an aeroengine rotor, and particularly relates to a disassembly and assembly structure of nuts in a shaft neck disc cavity of an aeroengine rotor.
Background
The aeroengine rotor component is arranged in the stator casing, wherein a screw is fixed at the end part of the rotor shaft neck, and the screw is connected with the connecting edge of the drum barrel in a matched manner through the screw, and the screw is positioned in the disc cavity of the rotor shaft neck, so that the rotor shaft neck is integrally slender, the inner space is narrow, and the screw is difficult to disassemble and assemble.
The present application has been made in view of the existence of the above-mentioned technical drawbacks.
It should be noted that the above disclosure of the background art is only for aiding in understanding the inventive concept and technical solution of the present invention, which is not necessarily prior art to the present application, and should not be used for evaluating the novelty and the creativity of the present application in the case where no clear evidence indicates that the above content has been disclosed at the filing date of the present application.
Disclosure of Invention
The purpose of the application is to provide an aircraft engine rotor journal disc cavity inner nut dismounting structure, so as to overcome or alleviate the technical defects of at least one aspect of the known technology.
The technical scheme of the application is as follows:
an aeroengine rotor journal dish intracavity nut dismouting structure includes:
the support plate is connected to the stator case and is provided with a perforation;
the connecting rod penetrates through the through hole and extends into the rotor journal disc cavity;
the support is connected with one end of the connecting rod extending into the rotor journal disc cavity;
the support cylinder is connected to the support;
the wrench shaft penetrates through the supporting cylinder and is connected with the supporting cylinder in a matched manner through spiral threads;
the wrench head is connected to one end of the wrench shaft and is provided with a wrench hole; the wrench hole is clamped on a nut which is connected with the end part of the rotor shaft neck and the connecting edge of the drum barrel;
the hydraulic cylinder is connected to the supporting cylinder;
the transmission arm is connected to the hydraulic rod of the hydraulic cylinder and is hinged with the other end of the wrench shaft;
the handle is hinged to the other end of the connecting rod and is provided with a strip-shaped hole;
the support block is connected to the support plate;
the rolling rod is arranged in the strip-shaped hole and connected to the supporting block.
According to at least one embodiment of the application, in the nut dismounting structure in the shaft neck disc cavity of the aeroengine rotor, the support plates are connected through bolts by utilizing bolt holes on the connecting edges of the stator casing.
According to at least one embodiment of the application, in the nut dismounting structure in the cavity of the rotor journal disc of the aeroengine, the support plate is connected to the screw rod of the rotor part at the front end of the rotor journal through the screw sleeve by using the bolts.
According to at least one embodiment of the present application, in the nut dismounting structure in the shaft neck disc cavity of the aero-engine rotor, the through holes are special-shaped holes.
According to at least one embodiment of the present application, in the nut dismounting structure in the shaft neck disc cavity of the aero-engine rotor, the support comprises:
the upper wall plate is connected with one end of the connecting rod extending into the rotor journal disc cavity;
the lower wall plate is connected with the upper wall plate, and a cavity is formed between the lower wall plate and the upper wall plate; the drive arm is located within the cavity.
According to at least one embodiment of the present application, in the nut dismounting structure in the shaft neck disc cavity of the aeroengine rotor, the supporting cylinder is connected to the support through the flange disc by the bolts.
According to at least one embodiment of the present application, in the nut dismounting structure in the journal disc cavity of the aeroengine rotor, the supporting cylinder and the corresponding wrench shaft, wrench head, hydraulic cylinder and transmission arm are provided with a plurality of groups.
According to at least one embodiment of the present application, in the nut dismounting structure in the shaft neck disc cavity of the aero-engine rotor, a groove is formed in the handle; the side walls on two sides of the slot are provided with strip-shaped holes;
each end of the rolling rod correspondingly extends into one strip-shaped hole.
According to at least one embodiment of the present application, in the nut dismounting structure in the journal disc cavity of the aero-engine rotor, two support blocks are arranged between the grooves;
according to at least one embodiment of the present application, in the nut dismounting structure in the shaft neck disc cavity of the aero-engine rotor, the nut dismounting structure further comprises:
the hinge shaft is hinged between one end of the connecting rod, which is back to the support, and two grooved side walls.
Drawings
Fig. 1 is an application schematic diagram of a nut dismounting structure in a journal disc cavity of an aero-engine rotor provided by an embodiment of the application;
FIG. 2 is a schematic view of an aircraft engine rotor journal disc cavity nut assembly and disassembly structure provided in an embodiment of the present application;
FIG. 3 is a schematic view of a portion of a nut assembly and disassembly structure in a journal disc cavity of an aircraft engine rotor provided in an embodiment of the present application;
FIG. 4 is a partial cross-sectional view of an aircraft engine rotor journal disc intracavity nut removal structure provided by an embodiment of the present application;
wherein:
1-supporting plates; 2-stator case; 3-connecting rod; 4-rotor journals; 5-supporting seats; 6-supporting a cylinder; 7-a spanner shaft; 8-wrench head; 9-drum; 10-nuts; 11-a hydraulic cylinder; 12-a drive arm; 13-a handle; 14-supporting blocks; 15-rolling bars; 16-hinge axis.
For the purpose of better illustrating the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced and do not represent the actual product dimensions, and furthermore, the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solution of the present application and the advantages thereof more apparent, the technical solution of the present application will be more fully described in detail below with reference to the accompanying drawings, it being understood that the specific embodiments described herein are only some of the embodiments of the present application, which are for explanation of the present application, not for limitation of the present application. It should be noted that, for convenience of description, only the portion relevant to the present application is shown in the drawings, and other relevant portions may refer to a general design, and without conflict, the embodiments and technical features in the embodiments may be combined with each other to obtain new embodiments.
Furthermore, unless defined otherwise, technical or scientific terms used in the description of this application should be given the ordinary meaning as understood by one of ordinary skill in the art to which this application belongs. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," "outer," and the like as used in this description are merely used to indicate relative directions or positional relationships, and do not imply that a device or element must have a particular orientation, be configured and operated in a particular orientation, and that the relative positional relationships may be changed when the absolute position of the object being described is changed, and thus should not be construed as limiting the present application. The terms "first," "second," "third," and the like, as used in the description herein, are used for descriptive purposes only and are not to be construed as indicating or implying any particular importance to the various components. The use of the terms "a," "an," or "the" and similar referents in the description of the invention are not to be construed as limited in number to the precise location of at least one. As used in this description, the terms "comprises," "comprising," or the like are intended to cover an element or article that appears before the term and that is listed after the term and its equivalents, without excluding other elements or articles.
Furthermore, unless specifically stated and limited otherwise, the terms "mounted," "connected," and the like in the description herein are to be construed broadly and refer to either a fixed connection, a removable connection, or an integral connection, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can also be communicated with the inside of two elements, and the specific meaning of the two elements can be understood by a person skilled in the art according to specific situations.
The present application is described in further detail below with reference to fig. 1-4.
An aeroengine rotor journal dish intracavity nut dismouting structure includes:
the support plate 1 is connected to the stator case 2 and is provided with a perforation;
the connecting rod 3 penetrates through the through hole and extends into the disc cavity of the rotor shaft neck 4;
the support 5 is connected with one end of the connecting rod 3 extending into the disc cavity of the rotor journal 4;
a support cylinder 6 connected to the support 5;
the wrench shaft 7 penetrates through the supporting cylinder 6 and is connected with the supporting cylinder 6 in a matched mode through spiral threads;
the wrench head 8 is connected to one end of the wrench shaft 7 and is provided with a wrench hole; the wrenching holes are clamped on nuts 10 which are connected with the end parts of the rotor shaft necks 4 and the connecting edges of the drums 9;
a hydraulic cylinder 11 connected to the support cylinder 6;
the transmission arm 12 is connected to the hydraulic rod of the hydraulic cylinder 11 and is hinged with the other end of the wrench shaft 7;
a handle 13 hinged to the other end of the connecting rod 3 and having a bar-shaped hole thereon;
a support block 14 connected to the support plate 1;
the rolling rod 15 is arranged in the strip-shaped hole and is connected to the supporting block 14.
For the nut dismounting structure in the aeroengine rotor shaft neck disc cavity disclosed by the embodiment, as can be understood by a person skilled in the art, the hydraulic cylinder 11 can be operated to stretch and retract, the driving arm drives the wrench shaft 7 to stretch and retract, and the wrench shaft 7 is connected with the supporting cylinder 6 in a matched manner through the spiral threads, so that the wrench head 8 can be driven to screw the nut 10 while stretching and retracting, and therefore the dismounting of the nut in the aeroengine rotor shaft neck disc cavity is realized, and the dismounting is convenient and quick.
For the nut dismounting structure in the cavity of the rotor journal disc of the aeroengine disclosed by the embodiment, as can be understood by those skilled in the art, when the hydraulic rod of the hydraulic cylinder 11 stretches and contracts, the connecting rod 3 can be tensioned by the handle 13 based on the lever principle, so that the spanner Kong Baochi is clamped on the nut 10 connecting the end part of the rotor journal 4 and the connecting edge of the drum 9, the disconnection is avoided, and in the process, the rolling rod 15 can roll in the strip-shaped hole, and the clamping stagnation is avoided.
In some optional embodiments, in the nut dismounting structure in the shaft neck disc cavity of the aeroengine rotor, the support plate 1 is connected by bolts through bolt holes on the connecting edges of the stator casing 2, and the existing structure of the stator casing 2 is not damaged.
In some optional embodiments, in the nut dismounting structure in the cavity of the rotor journal disc of the aeroengine, the support plate 1 is connected to the screw rod of the rotor component at the front end of the rotor journal 4 through bolts by utilizing threaded sleeves, the existing structure of the rotor component is not damaged, the position of the nut 10 connecting the rotor component at the front end of the rotor journal 4 with the connecting edge of the rotor journal 4 and the drum 9 is relatively fixed, and the support plate 1 is connected to the rotor component at the front end of the rotor journal 4, so that the positioning of the wrench head 8 and the nut 10 in the radial direction can be ensured.
In some optional embodiments, in the nut dismounting structure in the cavity of the journal disc of the aeroengine rotor, the through holes are special-shaped holes, and the cross section shape of the connecting rod 3 matched with the through holes is special-shaped, specifically, the through holes can be square, oval, flat and the like, so that when the nut 10 in the cavity of the journal disc of the aeroengine rotor is screwed, the connecting rod 3 is effectively restrained to rotate, and torque generated by screwing the nut 10 is effectively transmitted to the stator case 2 through the support plate 1 to be carried.
In some alternative embodiments, in the above nut dismounting structure in the cavity of the journal disk of the aeroengine rotor, the support 5 comprises:
the upper wall plate is connected to one end of the connecting rod 3 extending into the disc cavity of the rotor shaft neck 4 and is in centering fit;
the lower wall plate is connected with the upper wall plate, in particular to the lower wall plate by bolts, and a cavity is formed between the lower wall plate and the upper wall plate; the actuator arm 12 is located within the cavity.
In some alternative embodiments, in the above-mentioned nut dismounting structure in the cavity of the journal disc of the aeroengine rotor, the supporting cylinder 6 is connected to the support 5 by bolts and flanges.
In some alternative embodiments, in the above nut dismounting structure in the cavity of the journal disc of the aeroengine rotor, the supporting cylinder 6 and the corresponding wrench shaft 7, wrench head 8, hydraulic cylinder 11 and transmission arm 12 have a plurality of groups, the specific number and the distribution position thereof can be determined according to the actual number of the connecting side nuts 10 connecting the end of the rotor journal 4 and the drum 9, so that the synchronous dismounting of a plurality of nuts in the cavity of the journal disc of the aeroengine rotor can be realized, and the situation of uneven stress and larger local deformation is avoided.
In some alternative embodiments, in the nut dismounting structure in the cavity of the journal disc of the aeroengine rotor, the handle 13 is provided with a groove; the side walls on two sides of the slot are provided with strip-shaped holes;
each end of the roller 15 extends into a corresponding one of the bar-shaped holes to enable a firm support for the handle 13.
In some alternative embodiments, in the nut dismounting structure in the shaft neck disc cavity of the aeroengine rotor, two support blocks 14 are arranged between the grooves;
in some optional embodiments, in the nut dismounting structure in the journal disc cavity of the aeroengine rotor, the method further includes:
the hinge shaft 16 is hinged between two grooved side walls at one end of the connecting rod 3 facing away from the support 5.
The disassembly and assembly structure of the nut in the shaft neck disc cavity of the aero-engine rotor disclosed by the embodiment can be carried out by referring to the following steps when the structure is specifically applied:
the support 5 is detached from the connecting rod 3, and simultaneously the support cylinder 6, the wrench shaft 7, the wrench head 8, the hydraulic cylinder 11 and the transmission arm 12 can be detached from the support 5;
the connecting rod 3 extends into a disc cavity of the rotor journal 4 and connects the support plate 1 with the stator case 2 and the rotor part at the front end of the rotor journal 4;
connecting the support 5 to the connecting rod 3, aligning the wrenching holes with nuts 10 connecting the ends of the rotor journals 4 and the connecting edges of the drums 9;
pulling the connecting rod 3 by the handle 13 to clamp the wrench hole on the nut 10 connecting the end of the rotor shaft neck 4 and the connecting edge of the drum barrel 9;
the hydraulic cylinder 11 is operated to extend and retract, the nut 10 is screwed, and the nut in the shaft neck disc cavity of the rotor of the aeroengine is dismounted.
In the description, each embodiment is described in a progressive manner, and each embodiment is mainly described by the differences from other embodiments, so that the same similar parts among the embodiments are mutually referred.
Having thus described the technical aspects of the present application with reference to the preferred embodiments illustrated in the accompanying drawings, it should be understood by those skilled in the art that the scope of the present application is not limited to the specific embodiments, and those skilled in the art may make equivalent changes or substitutions to the relevant technical features without departing from the principles of the present application, and those changes or substitutions will now fall within the scope of the present application.
Claims (10)
1. An aeroengine rotor journal dish intracavity nut dismouting structure, characterized by comprising:
the support plate (1) is connected to the stator case (2) and is provided with a perforation;
the connecting rod (3) penetrates through the through hole and extends into the disc cavity of the rotor shaft neck (4);
the support (5) is connected with one end of the connecting rod (3) extending into the disc cavity of the rotor journal (4);
a support cylinder (6) connected to the support (5);
the wrench shaft (7) penetrates through the supporting cylinder (6) and is connected with the supporting cylinder (6) in a matching way through spiral threads;
the wrench head (8) is connected to one end of the wrench shaft (7) and is provided with a wrench hole; the wrench hole is clamped on a nut (10) connected with the end part of the rotor shaft neck (4) and the connecting edge of the drum barrel (9);
a hydraulic cylinder (11) connected to the support cylinder (6);
the transmission arm (12) is connected to a hydraulic rod of the hydraulic cylinder (11) and is hinged with the other end of the wrench shaft (7);
a handle (13) hinged to the other end of the connecting rod (3) and provided with a bar-shaped hole;
the support block (14) is connected to the support plate (1);
the rolling rod (15) is arranged in the strip-shaped hole and is connected to the supporting block (14).
2. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the support plates (1) are connected through bolts by utilizing bolt holes on the connecting edges of the stator casing (2).
3. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the support plate (1) is connected with a screw rod of a rotor part at the front end of the rotor journal (4) through a screw sleeve by bolts.
4. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the perforation is a special-shaped hole.
5. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the support (5) comprises:
the upper wall plate is connected with one end of the connecting rod (3) extending into the disc cavity of the rotor shaft neck (4);
the lower wall plate is connected with the upper wall plate, and a cavity is formed between the lower wall plate and the upper wall plate; the actuator arm (12) is located within the cavity.
6. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the supporting cylinder (6) is connected to the support (5) through bolts and flanges.
7. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the supporting cylinder (6) and the corresponding wrench shaft (7), the wrench head (8), the hydraulic cylinder (11) and the transmission arm (12) are provided with a plurality of groups.
8. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 1, wherein,
the handle (13) is provided with a slot; the side walls on two sides of the slot are provided with strip-shaped holes;
each end of the rolling rod (15) correspondingly extends into one strip-shaped hole.
9. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 8, wherein,
two support blocks (14) are arranged between the grooves.
10. The assembly and disassembly structure for nuts in a journal disc cavity of an aircraft engine rotor according to claim 8, wherein,
further comprises:
the hinge shaft (16) is hinged between two grooved side walls at one end of the connecting rod (3) back to the support (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211522240.9A CN116276002A (en) | 2022-11-30 | 2022-11-30 | Inner nut dismounting structure of aero-engine rotor journal disc cavity |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211522240.9A CN116276002A (en) | 2022-11-30 | 2022-11-30 | Inner nut dismounting structure of aero-engine rotor journal disc cavity |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116276002A true CN116276002A (en) | 2023-06-23 |
Family
ID=86831146
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211522240.9A Pending CN116276002A (en) | 2022-11-30 | 2022-11-30 | Inner nut dismounting structure of aero-engine rotor journal disc cavity |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116276002A (en) |
-
2022
- 2022-11-30 CN CN202211522240.9A patent/CN116276002A/en active Pending
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