CN113800376A - Aircraft engine replacement method and lever block - Google Patents
Aircraft engine replacement method and lever block Download PDFInfo
- Publication number
- CN113800376A CN113800376A CN202111160826.0A CN202111160826A CN113800376A CN 113800376 A CN113800376 A CN 113800376A CN 202111160826 A CN202111160826 A CN 202111160826A CN 113800376 A CN113800376 A CN 113800376A
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- Prior art keywords
- lever
- aircraft engine
- bracket
- lifting
- identification
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C1/00—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles
- B66C1/10—Load-engaging elements or devices attached to lifting or lowering gear of cranes or adapted for connection therewith for transmitting lifting forces to articles or groups of articles by mechanical means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/04—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack
- B66C13/08—Auxiliary devices for controlling movements of suspended loads, or preventing cable slack for depositing loads in desired attitudes or positions
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C13/00—Other constructional features or details
- B66C13/16—Applications of indicating, registering, or weighing devices
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66C—CRANES; LOAD-ENGAGING ELEMENTS OR DEVICES FOR CRANES, CAPSTANS, WINCHES, OR TACKLES
- B66C25/00—Cranes not provided for in groups B66C17/00 - B66C23/00
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B66—HOISTING; LIFTING; HAULING
- B66D—CAPSTANS; WINCHES; TACKLES, e.g. PULLEY BLOCKS; HOISTS
- B66D1/00—Rope, cable, or chain winding mechanisms; Capstans
- B66D1/02—Driving gear
- B66D1/04—Driving gear manually operated
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Devices For Conveying Motion By Means Of Endless Flexible Members (AREA)
Abstract
The invention provides an aircraft engine replacing method and a lever block, wherein the method comprises the following steps: arranging a hanger above the installation position of the engine, and installing a plurality of lever hoists on the hanger; arranging a bracket at the bottom of an aircraft engine, then fixedly connecting the bracket with the aircraft engine, and connecting a chain of the lever block with a lifting point on the bracket; simultaneously wrenching the wrenches of all the lever blocks to synchronously lower or lift the bracket, wherein the wrenches of all the lever blocks rotate by the same angle along the mark scale; lowering the bracket to a designated placement position or lifting to the engine mounting position. According to the aircraft engine replacing method, the scales are marked to enable each worker to synchronously rotate the wrenches with the same angle, so that the lifting or lowering distances of each lever block are the same, the aircraft engine can conveniently and stably reach the installation position in a correct posture, and time and labor are saved.
Description
Technical Field
The invention relates to the technical field of aerospace devices, in particular to an aircraft engine replacement method and a lever block.
Background
When the aircraft engine is installed, a hand-pulling chain block is often manually pulled to lift or lower a bracket of the aircraft engine to a specified position, and then the aircraft engine is fixed with the aircraft. Because the rotating angle of the wrench is corresponding to the length of the chain of the wrench which is lowered or lifted, and the wrench is usually a worker who pulls the chain correspondingly, the angle of the wrench pulled by different workers is difficult to determine, and errors are easy to occur, so that the lengths of the chains which are lowered or lifted by the wrench are different, the bracket cannot be kept balanced and is inclined, the tension of the chain to the lifting point of the bracket is different, the attitude of the airplane is unstable, the subsequent installation steps are not easy to occur, and if the bracket is continuously lifted or lowered, the bracket is easy to shake, so that the hanger is scraped with the structure of the airplane, and abrasion is caused; if the balance needs to be adjusted repeatedly when the lever block is lifted or lowered each time, the time and the labor are wasted.
Disclosure of Invention
The invention aims to overcome the defects in the prior art and provide an aircraft engine replacing method and a lever block.
One embodiment of the present invention provides an aircraft engine change method, comprising the steps of:
arranging a hanger above the installation position of the engine, and installing a plurality of lever hoists on the hanger;
arranging a bracket at the bottom of an aircraft engine, then fixedly connecting the bracket with the aircraft engine, arranging a plurality of lifting points around the periphery of the aircraft engine on the bracket, and connecting a chain of the lever block with the lifting points on the bracket;
simultaneously wrenching the wrenches of all the lever blocks to synchronously lower or lift the bracket, wherein the lever blocks are provided with identification scales surrounding the rotation axes of the wrenches of the lever blocks, and the wrenches of all the lever blocks rotate by the same angle along the identification scales when the wrenches of the lever blocks are simultaneously wrenched each time;
after the spanner of the lever block is wrenched for multiple times, the bracket is lowered to a specified placing position or lifted to the engine mounting position.
Compared with the prior art, the aircraft engine replacing method enables each worker to synchronously rotate the wrenches with the same angle through the identification scales, enables the lifting or lowering distances of each lever block to be the same, greatly avoids the situation that the stress of each lever block is unbalanced due to the fact that the bracket inclines left and right, is convenient for enabling the aircraft engine to quickly and stably reach the installation position in a correct posture, and is time-saving and labor-saving.
In one embodiment, after pulling the wrench of each of the lever blocks, the pulling force of each of the lever blocks on the lifting point is determined, and if the pulling force exceeds a pulling force limit value, the wrench of the corresponding lever block is pulled to lift the corresponding lifting point.
In one embodiment, after the wrench of each of the wrench blocks is wrenched, the pulling force of each of the wrench blocks on the lifting point is determined, and if the difference between the maximum pulling force and the minimum pulling force exceeds a preset value, the wrench of the wrench block corresponding to the maximum pulling force is wrenched to lift the corresponding lifting point.
In one embodiment, a plurality of load cells are mounted on the hanger, the lever blocks are connected to the load cells in a one-to-one correspondence, and the tension of the lever blocks on the lifting point is measured by the load cells.
In one embodiment, the index value of the identification scale is 5 °.
In one embodiment, the identification scale is uniformly divided into 4 sub-identification scales, the 4 sub-identification scales are sequentially connected end to end and are arranged around the rotation axis of the wrench of the lever block, and special identification parts are arranged at positions at intervals of 15 degrees from the starting point to the end point of the sub-identification scales.
In one embodiment, the position of the wrench of the lever block relative to the identification scale is determined by a pointer on the wrench of the lever block.
In one embodiment, 4 of the lever blocks are mounted on a bracket, and the lifting points are provided at positions on both sides of the bracket at the front end of the aircraft engine and on both sides of the rear end of the aircraft engine.
Another embodiment of the present invention provides an arm hoist applied to the above method for replacing an aircraft engine, including: the chain type chain lifting device comprises a body, a lifting chain wheel arranged in the body, a chain in transmission connection with the lifting chain wheel, a wrench connected with the lifting chain wheel and identification scales arranged on the body, wherein the identification scales are arranged around the rotating axis of the wrench of the lever block.
In one embodiment, the marking scale comprises 4 sub-marking scales, the 4 sub-marking scales are sequentially connected end to end and are arranged around the rotation axis of the wrench of the lever block, and special marking parts are arranged at positions, at intervals of 15 degrees, from the starting point to the end point of each sub-marking scale.
In order that the invention may be more clearly understood, specific embodiments thereof will be described hereinafter with reference to the accompanying drawings.
Drawings
FIG. 1 is a process diagram of an aircraft engine change method in accordance with an embodiment of the invention;
FIG. 2 is an exploded view of an aircraft engine, pylon and bracket according to one embodiment of the invention;
fig. 3 is a schematic structural diagram of a lever block according to an embodiment of the present invention.
Description of reference numerals:
10. a hanger; 20. a lever block; 21. a body; 22. a wrench; 23. a chain; 24. marking scales; 25. a special identification part; 30. a bracket; 40. an aircraft engine; 50. a force gauge.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1, a process diagram of an aircraft engine replacing method according to an embodiment of the present invention is shown, the aircraft engine replacing method including the following steps:
s1: the hanger 10 is disposed above an engine mounting position, and a plurality of lever blocks 20 are mounted on the hanger 10, and a top of the lever blocks is generally provided with hooks by which a bottom of the hanger 10 can be mounted.
S2: arranging a bracket 30 at the bottom of an aircraft engine 40, fixedly connecting the bracket 30 with the aircraft engine 40, arranging a plurality of lifting points around the periphery of the aircraft engine 40 on the bracket 30, and connecting the chain 23 of the lever block 20 with the lifting points on the bracket 30. In the present embodiment, 4 of the lever blocks 20 are mounted on the hanger 10, but the number of the lever blocks 20 may be adjusted according to the size of the aircraft engine 40; correspondingly, the lifting points are arranged at positions on two sides of the bracket 30 close to the front end of the aircraft engine 40 and on two sides close to the rear end of the aircraft engine 40, and the total number of the lifting points is 4, so that the stability of the aircraft engine 40 is favorably maintained. It should be noted that, when the aircraft engine 40 is taken down, the chain 23 of the lever block 20 should be connected to the lifting point on the bracket 30, and then the bracket 30 is lifted to the bottom of the aircraft engine 40, and then the bracket 30 is fixedly connected to the aircraft engine 40; when the aircraft engine 40 is installed, the aircraft engine 40 is arranged on the bracket 30 in advance, the bracket 30 is fixedly connected with the aircraft engine 40, and then the chain 23 of the lever block 20 is connected with the lifting point on the bracket 30.
S3: simultaneously wrenching the wrenches 22 of all the lever blocks 20, so that all the lever blocks 20 synchronously lower or lift the bracket 30. The lever blocks 20 are provided with identification scales 24 surrounding the rotation axis of the wrench 22 of the lever blocks 20, and when the wrench 22 of the lever blocks 20 is simultaneously wrenched each time, the wrenches 22 of all the lever blocks 20 rotate at the same angle along the identification scales 24, so that each lifting point is lifted up or lowered down to the same height, and the bracket 30 is prevented from inclining.
S4: after the wrench 22 of the lever block 20 is wrenched a plurality of times, the bracket 30 is lowered to a designated placement position or lifted to the engine mounting position. In the present embodiment, when the aircraft engine 40 is removed, the connection structure between the aircraft engine 40 and the aircraft is removed, then the wrenches 22 of all the lever blocks 20 are simultaneously pulled, so that all the lever blocks 20 simultaneously lower the bracket 30, and after the wrenches 22 of the lever blocks 20 are pulled for a plurality of times, the bracket 30 is lowered onto a moving vehicle or other designated positions. When the aircraft engine 40 is installed, the wrenches 22 of all the lever blocks 20 are simultaneously pulled, so that all the lever blocks 20 simultaneously lift the bracket 30, after the wrenches 22 of the lever blocks 20 are pulled for multiple times, the bracket 30 is lifted to an engine installation position, and then the aircraft engine 40 is fixedly installed on the engine installation position of the aircraft.
In some alternative embodiments, a plurality of load cells 50 are installed on the hanger 10, the lever blocks 20 are connected to the load cells 50 in a one-to-one correspondence, and the tension of the lever blocks 20 to the lifting point is measured by the load cells 50. In the present embodiment, the load cell 50 is provided with hooks at both top and bottom thereof, the top of the load cell 50 is hooked on the hanger 10 by the hooks, the bottom of the load cell 50 is connected to the hook at the top of the lever block 20 by the hook, and the hook at the bottom of the load cell 50 is connected to the measuring end of the load cell 50, so that the pulling force of the lever block 20 to the tray 30 is determined by measuring the pulling force of the lever block 20 to the load cell 50.
When the chain 23 of the lever block 20 is connected with the bracket 30, a fixing pin is usually used to pass through the bracket 30 and the aperture of the chain 23, so as to fix the chain 23 and the bracket 30, in some alternative embodiments, after the wrench 22 of the lever block 20 is wrenched each time, the tension of each lever block 20 to the lifting point is determined, and if the tension exceeds the tension limit value, the corresponding wrench 22 of the lever block 20 is wrenched to lift the corresponding lifting point, so as to reduce the tension at the lifting point, and avoid the situation that the connection structure of the chain 23 of the lever block 20 and the bracket 30 is broken due to the excessive tension at the lifting point. Of course, the chain 23 of the lever block 20 may be provided with a hook, and the chain 23 of the lever block 20 may be connected to the bracket 30 through the hook.
In some optional embodiments, after pulling the wrench 22 of each of the lever hoists 20, the pulling force of each of the lever hoists 20 to the lifting point is determined, and if the difference between the maximum pulling force and the minimum pulling force exceeds a preset value, it indicates that each lifting point position of the bracket 30 is in an unbalanced state, which easily causes the bracket 30 to shake, and the aircraft engine 40 is in an unbalanced state, which easily causes the aircraft engine 40 and the structure of the aircraft to scrape against each other, and at this time, the wrench 22 of the lever hoist 20 corresponding to the maximum pulling force is pulled to lift the corresponding lifting point, so that the lifting point corresponding to the maximum pulling force is lifted, thereby reducing the pulling force at the lifting point.
In order to facilitate the identification of the rotation angle of the wrench 22 of the lever block 20, in some alternative embodiments, the index scale 24 has a division value of 5 ° for easy identification by the staff.
Since an employee usually commands the wrench 22 of the wrench 20, in order to make it easier for the employee to rotate the wrench 22 of the wrench 20 to a certain angle commonly used and to facilitate commanding and reducing the operation difficulty, in some optional embodiments, the identification scale 24 is uniformly divided into 4 sub-identification scales 24, the sub-identification scales 24 respectively identify angles of 90 °, the 4 sub-identification scales 24 are sequentially connected end to end, the sub-identification scales are arranged around the rotation axis of the wrench 22 of the wrench 20, and a special identification portion 25 is disposed at a position of 15 ° interval from the start point to the end point of the sub-identification scale 24, that is, the special identification portions 25 are disposed at positions of 0 °, 15 °, 30 °, 45 °, 60 °, 75 ° and 90 ° from the start point to the end point of the sub-identification scale 24.
In order to facilitate the identification of the angle of rotation of the lever block 20, in some alternative embodiments, the position of the wrench 22 of the lever block 20 relative to the identification scale 24 is determined by a pointer on the wrench 22 of the lever block 20, the pointer being aligned with the identification scale 24.
Another embodiment of the present invention provides an arm block 20, which can be used in the above-mentioned method for replacing an aircraft engine, and comprises: the lifting chain wheel is arranged in the body 21, the chain 23 is in transmission connection with the lifting chain wheel, the wrench 22 is connected with the lifting chain wheel, and the identification scale 24 is arranged on the body 21, the identification scale 24 is arranged around the rotation axis of the wrench 22 of the lever block 20, the wrench 22 is connected with the lifting chain wheel through a rotating shaft, a pointer is further arranged at the edge of the wrench 22 close to the rotating shaft, and the pointer extends along the radial direction of the rotating shaft. In this embodiment, an identification ring is provided between the wrench 22 and the body 21, the identification ring being arranged around the axis of rotation, and an identification scale 24 being provided on the identification ring. The improvement of the present invention is the identification structure on the lever block, and the rotating structure of the lifting sprocket and the chain 23 and the driving connection structure of the lifting sprocket and the wrench 22 inside the lever block 20 are well known to those skilled in the art, and thus will not be described and illustrated herein.
In some optional embodiments, the identification scale 24 includes 4 sub-identification scales 24, the 4 sub-identification scales 24 are sequentially connected end to end and arranged around the rotation axis of the wrench 22 of the lever block 20, and the positions of the starting point to the ending point of the sub-identification scales 24, which are spaced by 15 °, are provided with special identification portions 25.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. An aircraft engine change method, comprising the steps of:
arranging a hanger above the installation position of the engine, and installing a plurality of lever hoists on the hanger;
arranging a bracket at the bottom of an aircraft engine, then fixedly connecting the bracket with the aircraft engine, arranging a plurality of lifting points around the periphery of the aircraft engine on the bracket, and connecting a chain of the lever block with the lifting points on the bracket;
simultaneously wrenching the wrenches of all the lever blocks to synchronously lower or lift the bracket, wherein the lever blocks are provided with identification scales surrounding the rotation axes of the wrenches of the lever blocks, and the wrenches of all the lever blocks rotate by the same angle along the identification scales when the wrenches of the lever blocks are simultaneously wrenched each time;
after the spanner of the lever block is wrenched for multiple times, the bracket is lowered to a specified placing position or lifted to the engine mounting position.
2. An aircraft engine change method according to claim 1, wherein: and after the spanner of each lever hoist is pulled, determining the pulling force of each lever hoist on the lifting point, and if the pulling force exceeds the pulling force limit value, pulling the corresponding spanner of the lever hoist to lift the corresponding lifting point.
3. An aircraft engine change method according to claim 1, wherein: and after the spanner of each lever hoist is pulled, determining the pulling force of each lever hoist on the lifting point, and if the difference between the maximum pulling force and the minimum pulling force exceeds a preset value, pulling the spanner of the lever hoist corresponding to the maximum pulling force to lift the corresponding lifting point.
4. An aircraft engine change method according to claim 2 or 3, characterised in that: and a plurality of dynamometers are arranged on the hanging bracket, the lever hoists are correspondingly connected with the dynamometers one by one, and the tension of the lever hoists on the lifting points is measured through the dynamometers.
5. An aircraft engine change method according to claim 1, wherein: the index scale has a division value of 5 °.
6. An aircraft engine change method according to any one of claims 1 or 5, characterised in that: the identification scales are evenly divided into 4 sub-identification scales, the 4 sub-identification scales are sequentially connected end to end and are arranged around the rotating axis of a wrench of the lever block, and special identification parts are arranged at the positions, at intervals of 15 degrees, from the starting point to the end point of the sub-identification scales.
7. An aircraft engine change method according to any one of claims 1, 2, 3 or 5, wherein: and determining the position of the wrench of the lever block relative to the identification scale through a pointer on the wrench of the lever block.
8. An aircraft engine change method according to any one of claims 1, 2, 3 or 5, wherein: 4 lever blocks are arranged on the lifting frame, and lifting points are arranged at the positions of the two sides of the bracket at the front end of the aircraft engine and the two sides of the rear end of the aircraft engine.
9. An arm-hoist to be applied to the aircraft engine replacement method according to any one of claims 1 to 8, characterized by comprising: the chain type chain lifting device comprises a body, a lifting chain wheel arranged in the body, a chain in transmission connection with the lifting chain wheel, a wrench connected with the lifting chain wheel and identification scales arranged on the body, wherein the identification scales are arranged around the rotating axis of the wrench of the lever block.
10. A lever block as defined in claim 9, wherein: the identification scales comprise 4 sub-identification scales, the 4 sub-identification scales are sequentially connected end to end and are arranged around the rotation axis of the wrench of the lever block, and special identification parts are arranged at positions, at intervals of 15 degrees, from the starting point to the end point of each sub-identification scale.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160826.0A CN113800376A (en) | 2021-09-30 | 2021-09-30 | Aircraft engine replacement method and lever block |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111160826.0A CN113800376A (en) | 2021-09-30 | 2021-09-30 | Aircraft engine replacement method and lever block |
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| Publication Number | Publication Date |
|---|---|
| CN113800376A true CN113800376A (en) | 2021-12-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111160826.0A Pending CN113800376A (en) | 2021-09-30 | 2021-09-30 | Aircraft engine replacement method and lever block |
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| CN (1) | CN113800376A (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2724920A1 (en) * | 1994-09-27 | 1996-03-29 | Int De Nacelles Toulouse Soc | Swingletree for handling of heavy aircraft engines |
| CN204825531U (en) * | 2015-08-03 | 2015-12-02 | 中冶建工集团有限公司 | Reversal of natural order of things formula rail installation appurtenance |
| CN206156656U (en) * | 2016-11-11 | 2017-05-10 | 国家电网公司 | Tight for line lever block who takes tension measurement mechanism |
| CN208313483U (en) * | 2018-05-10 | 2019-01-01 | 张阳生 | A kind of transmission line of electricity corner steel tower electrification jacking tensile test system |
| US20200324915A1 (en) * | 2019-04-11 | 2020-10-15 | The Boeing Company | Systems and methods for moving a vehicle component relative to the vehicle structure |
| CN112441252A (en) * | 2020-10-14 | 2021-03-05 | 广州飞机维修工程有限公司 | Dismounting method of aircraft engine |
| CN113044733A (en) * | 2021-03-12 | 2021-06-29 | 中航西飞民用飞机有限责任公司 | Engine installation vehicle and engine installation method |
| CN213651697U (en) * | 2020-10-10 | 2021-07-09 | 浙江华欣电力机具制造有限公司 | Safe and shake-proof hoist |
-
2021
- 2021-09-30 CN CN202111160826.0A patent/CN113800376A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2724920A1 (en) * | 1994-09-27 | 1996-03-29 | Int De Nacelles Toulouse Soc | Swingletree for handling of heavy aircraft engines |
| CN204825531U (en) * | 2015-08-03 | 2015-12-02 | 中冶建工集团有限公司 | Reversal of natural order of things formula rail installation appurtenance |
| CN206156656U (en) * | 2016-11-11 | 2017-05-10 | 国家电网公司 | Tight for line lever block who takes tension measurement mechanism |
| CN208313483U (en) * | 2018-05-10 | 2019-01-01 | 张阳生 | A kind of transmission line of electricity corner steel tower electrification jacking tensile test system |
| US20200324915A1 (en) * | 2019-04-11 | 2020-10-15 | The Boeing Company | Systems and methods for moving a vehicle component relative to the vehicle structure |
| CN213651697U (en) * | 2020-10-10 | 2021-07-09 | 浙江华欣电力机具制造有限公司 | Safe and shake-proof hoist |
| CN112441252A (en) * | 2020-10-14 | 2021-03-05 | 广州飞机维修工程有限公司 | Dismounting method of aircraft engine |
| CN113044733A (en) * | 2021-03-12 | 2021-06-29 | 中航西飞民用飞机有限责任公司 | Engine installation vehicle and engine installation method |
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