CN117383399A - Lifting appliance structure for assembling and disassembling main combustion chamber of aero-engine - Google Patents
Lifting appliance structure for assembling and disassembling main combustion chamber of aero-engine Download PDFInfo
- Publication number
- CN117383399A CN117383399A CN202311445462.XA CN202311445462A CN117383399A CN 117383399 A CN117383399 A CN 117383399A CN 202311445462 A CN202311445462 A CN 202311445462A CN 117383399 A CN117383399 A CN 117383399A
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- China
- Prior art keywords
- combustion chamber
- main combustion
- connecting rod
- assembling
- support
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 88
- 238000000034 method Methods 0.000 claims abstract description 14
- 238000009434 installation Methods 0.000 claims abstract description 9
- 230000000712 assembly Effects 0.000 claims 1
- 238000000429 assembly Methods 0.000 claims 1
- 238000010276 construction Methods 0.000 claims 1
- 238000000354 decomposition reaction Methods 0.000 claims 1
- 238000012423 maintenance Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
Classifications
-
- 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
- B66C1/107—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 for lifting engines
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Combustion Methods Of Internal-Combustion Engines (AREA)
Abstract
The invention discloses a lifting appliance structure, in particular discloses a lifting appliance structure for assembling and disassembling a main combustion chamber of an aeroengine, and belongs to the technical field of design and manufacture of maintenance process equipment of the aeroengine. The lifting appliance structure for assembling and disassembling the main combustion chamber of the aeroengine can effectively ensure the installation safety of products and improve the assembling and disassembling quality and the assembling and disassembling efficiency. The lifting appliance structure comprises a supporting component, a profiling connecting component and a lifting component, wherein the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force.
Description
Technical Field
The invention relates to a lifting appliance structure, in particular to a lifting appliance structure for assembling and disassembling a main combustion chamber of an aeroengine, and belongs to the technical field of design and manufacture of maintenance process equipment of the aeroengine.
Background
The main combustion chamber is required to be assembled on the mounting edge of the bearing ring of the high-pressure compressor, so that the mounting edge holes are mutually aligned, and the mounting edge is tightly attached. The main combustion chamber is heavy and large in size, and can be assembled only by means of manual lifting, so that the manual lifting method is high in manpower demand, at least 4 persons are required to carry out the operation simultaneously, the assembly time is about 25 minutes, the labor intensity of workers is greatly increased, and faults such as falling to the ground of product parts due to improper operation can be caused. Therefore, there is an urgent need to design a hanger to reduce the manpower required for assembling the main combustion chamber while ensuring the safety of the product.
Disclosure of Invention
The technical problems to be solved by the invention are as follows: the lifting appliance structure for assembling and disassembling the main combustion chamber of the aeroengine can effectively ensure the installation safety of products and improve the assembling and disassembling quality and the assembling and disassembling efficiency.
The technical scheme adopted for solving the technical problems is as follows: the lifting appliance structure comprises a supporting component, a profiling connecting component and a lifting component, wherein the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force.
Further, the lifting assembly at least comprises a group of connecting lifting lugs which are arranged on the supporting assembly at the center of the starting point of the lifting appliance structure.
In the above-described embodiment, a plow-shaped hole which gradually increases upward is provided in the connecting lug, and the external lifting drive force is connected to the connecting lug through the plow-shaped hole.
Further, the supporting component comprises a supporting connector, a supporting connecting rod group and an adjusting locking piece group, the supporting connecting rod group is movably connected with the supporting connector under the matching of the adjusting locking piece group, the connecting lifting lug is fixedly connected with the supporting connector, and the free end of the supporting connecting rod group is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component.
The preferred mode of above-mentioned scheme is, supports the connecting rod group and includes a fixed support connecting rod, a movable support connecting rod and a support rod that cup joints, and fixed support connecting rod and cup joint the bracing piece and be connected with the both sides that support the connector along same radial respectively through a tip of each, and the movable support connecting rod is through cup jointing the bracing piece and along radial telescopic arranging on supporting the connector under the cooperation of adjustment locking piece group, and the free end of fixed support connecting rod and movable support connecting rod is through profile modeling coupling assembling and the detachable fixed connection of main combustion chamber that needs to install respectively.
Further, the adjusting locking piece group comprises a group of positioning bolts, bolt holes are respectively formed in corresponding positions of the sleeved support rods and the movable support connecting rods, and the movable support connecting rods which are adjusted to be in position are fixedly connected with the sleeved support rods through the bolt holes and the positioning bolts.
The preferred mode of above-mentioned scheme is, is provided with the hole that passes on the support connector, and the movable support connecting rod stretches into and cup joints the corresponding section of bracing piece with fixed support connecting rod after passing the hole that passes.
Further, the profiling connecting assembly comprises two groups of arc-shaped connectors, and a group of arc-shaped connectors are fixedly arranged at the connecting ends of the movable supporting connecting rod and the fixed supporting connecting rod respectively; in the assembly and disassembly process of the main combustion chamber of the aeroengine, each group of arc-shaped connectors are detachably connected with the main combustion chamber respectively under the cooperation of the movable support connecting rod, the fixed support connecting rod and the positioning bolt.
The preferred mode of above-mentioned scheme is, all is provided with the clamp groove respectively in the outside of first group arc connector, and the thickness and the degree of depth of clamp groove are the thickness and the width of the installation limit of main combustion chamber respectively adapt to.
Further, along the arc direction, at least two fixing grooves are sequentially arranged on the arc-shaped connecting head at the clamping groove position, and the distance between the mounting holes of the mounting edge is adapted to the distance between two adjacent fixing grooves.
The beneficial effects of the invention are as follows: according to the technical scheme, a set of lifting appliance structure comprising a supporting component, a profiling connecting component and a lifting component is arranged, and the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; and then in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force. The technical problem that no tool body is available when the main combustion chamber of the aeroengine is assembled and disassembled in the prior art is solved, meanwhile, when the main combustion chamber of the aeroengine is assembled and disassembled by adopting the lifting device structure provided by the application, the lifting device structure is connected with the main combustion chamber in advance only by manpower, and then the main combustion chamber can be assembled and disassembled through an external lifting driving force, so that the safety of product installation can be effectively ensured, and the assembly and disassembly quality and the assembly and disassembly efficiency can be improved.
Drawings
FIG. 1 is a front view of a spreader structure of the present invention for use in assembling and disassembling a main combustion chamber of an aircraft engine;
fig. 2 is a top view of fig. 1.
Marked in the figure as: the connecting lug 1, the plow hole 2, the supporting connector 3, the fixed supporting connecting rod 4, the movable supporting connecting rod 5, the sleeved supporting rod 6, the positioning bolt 7, the arc-shaped connector 8, the clamping groove 9 and the fixed groove 10.
Detailed Description
The lifting appliance structure for assembling and disassembling the main combustion chamber of the aeroengine, provided by the invention, can effectively ensure the installation safety of products and improve the assembling and disassembling quality and the assembling and disassembling efficiency as shown in fig. 1 and 2. The lifting appliance structure comprises a supporting component, a profiling connecting component and a lifting component, wherein the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force. According to the technical scheme, a set of lifting appliance structure comprising a supporting component, a profiling connecting component and a lifting component is arranged, and the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; and then in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force. The technical problem that no tool body is available when the main combustion chamber of the aeroengine is assembled and disassembled in the prior art is solved, meanwhile, when the main combustion chamber of the aeroengine is assembled and disassembled by adopting the lifting device structure provided by the application, the lifting device structure is connected with the main combustion chamber in advance only by manpower, and then the main combustion chamber can be assembled and disassembled through an external lifting driving force, so that the safety of product installation can be effectively ensured, and the assembly and disassembly quality and the assembly and disassembly efficiency can be improved.
Correspondingly, in order to maximize the structure of each part of the lifting appliance structure as far as possible in combination with the actual condition of production, the lifting assembly at least comprises a group of connecting lifting lugs 1, and the connecting lifting lugs 1 are arranged on a supporting assembly at the center of the starting point of the lifting appliance structure. And a plow-shaped hole 2 gradually increasing upward is provided on the connecting shackle 1, and an external lifting driving force is connected to the connecting shackle 1 through the plow-shaped hole 2. The support assembly comprises a support connector 3, a support connecting rod group and an adjustment locking piece group, wherein the support connecting rod group is movably connected with the support connector 3 under the cooperation of the adjustment locking piece group, the connection lifting lug 1 is fixedly connected with the support connector 3, and the free end of the support connecting rod group is detachably and fixedly connected with a main combustion chamber to be installed through a profiling connecting assembly. More specifically, the support connecting rod group include a fixed support connecting rod 4, a movable support connecting rod 5 and a support rod 6 that cup joints, fixed support connecting rod 4 and cup joint the bracing piece 6 and be connected with the both sides of support connector 3 along same radial through a tip of each respectively, movable support connecting rod 5 is along radial telescopic arranging on support connector 3 under the cooperation of adjustment locking piece group through cup jointing bracing piece 6, fixed support connecting rod 4 and movable support connecting rod 5's free end is through profile modeling coupling assembling and the detachable fixed connection of main combustion chamber that needs to install respectively. The adjusting locking piece group comprises a group of positioning bolts 7, bolt holes are respectively formed in corresponding positions of the sleeved support rods 6 and the movable support connecting rods 5, and the movable support connecting rods 5 which are adjusted to be in position are fixedly connected with the sleeved support rods 6 through the bolt holes and the positioning bolts 7. For convenient regulation, guarantee the intensity of hoist structure itself again simultaneously, this application is provided with the hole that passes on the support connector 3, and the one end that movable support connecting rod 5 stretched into cup joints bracing piece 6 passes and passes the hole after cup joints with the corresponding section of fixed support connecting rod 4.
Furthermore, in order to facilitate the connection of the lifting appliance structure and the main combustion chamber, and simultaneously ensure the stability and reliability of the connection, the profiling connecting assembly comprises two groups of arc-shaped connectors 8, and a group of arc-shaped connectors 8 are respectively and fixedly arranged at the connecting ends of the movable supporting connecting rod 5 and the fixed supporting connecting rod 4; in the assembly and disassembly process of the main combustion chamber of the aeroengine, each group of arc-shaped connectors 8 are detachably connected with the main combustion chamber respectively under the cooperation of the movable support connecting rod 5, the fixed support connecting rod 4 and the positioning bolt 7. And the main combustion chamber is combined with the structural characteristics that the main combustion chamber comprises a mounting edge and a connecting hole, the outer sides of the first group of arc connectors 8 are respectively provided with a clamping groove 9, and the thickness and the depth of the clamping grooves 9 are respectively matched with the thickness and the width of the mounting edge of the main combustion chamber. Along the arc direction, at least two fixing grooves 10 are sequentially arranged on the arc-shaped connector 8 at the position of the clamping groove 9, and the distance between the mounting holes of the mounting edge is matched with the distance between the two adjacent fixing grooves 10.
In summary, the hanger structure provided by the application has the advantages of installing and decomposing the main combustion chamber of the aeroengine,
the main combustion chamber can be stably assembled and disassembled, and the labor force is released while the main combustion chamber is safely used, so that the quality and the efficiency of assembling and disassembling the main combustion chamber are improved. The maintenance cost of the engine is reduced, and the maintenance period of the engine is shortened.
In terms of comparison with respect to the specific efficiency,
1) The assembly and disassembly convenience of the main combustion chamber is improved, the assembly time of the original 4 people for 25 minutes is shortened to 1 person for 2 minutes, and the efficiency is improved by 1- (1 multiplied by 2)/(4 multiplied by 25) =80%;
2) The requirement for manpower during assembly and disassembly of the main combustion chamber is reduced, and meanwhile, the safety of products is ensured.
The technical scheme of the application is further described by the following specific examples:
aiming at the technical problems pointed out in the background art, the application designs a lifting appliance for a main combustion chamber of an aero-engine. The design size of the lifting appliance refers to the radial size of the rear mounting edge of the combustion chamber, and in order to ensure that the lifting appliance can be freely mounted and disassembled in the use process, one end of the lifting appliance is designed to be a movable end, the other end of the lifting appliance is designed to be a fixed end, and the movable end can be retracted inwards. The lifting appliance is provided with a positioning pin hole, so that the movable end of the lifting appliance can be fixed in the using process. The movable end can be locked by inserting the locating pin into the locating pin hole when the lifting appliance is installed.
The technical solutions of the present application are described in further detail below with reference to the accompanying drawings, but the scope of protection of the present application is not limited to the following description.
Example 1
The main combustion chamber is assembled by the main combustion chamber lifting appliance of the aeroengine, and the main combustion chamber comprises the following steps:
s1, taking out the locating pin, so that the movable end of the lifting appliance can move freely.
S2, retracting the movable end of the lifting appliance inwards, and installing the fixed end at the rear installation side of the main combustion chamber.
S3, adjusting the movable end to enable the movable end of the lifting appliance to be mounted on the symmetrical position of the rear mounting edge of the main combustion chamber, and aligning the pin holes.
S4, inserting the positioning pin into the positioning pin hole and locking.
S5, lifting the main combustion chamber by using a crane, and slowly lifting the main combustion chamber to be assembled on the mounting edge of the bearing ring of the high-pressure compressor.
S6, taking down the lifting appliance.
Example two
The main combustion chamber of the aircraft engine is decomposed by a lifting appliance, and the main combustion chamber comprises the following steps:
s1, taking out the locating pin, so that the movable end of the lifting appliance can move freely.
S2, retracting the movable end of the lifting appliance inwards, and installing the fixed end at the rear installation side of the main combustion chamber.
S3, adjusting the movable end to enable the movable end of the lifting appliance to be mounted on the symmetrical position of the rear mounting edge of the main combustion chamber, and aligning the pin holes.
S4, inserting the positioning pin into the positioning pin hole and locking.
S5, lifting the main combustion chamber by using a crane, and slowly lifting the main combustion chamber so that the front mounting edge of the main combustion chamber is separated from the mounting edge of the bearing ring of the high-pressure compressor.
S6, the main combustion chamber is prevented from being arranged on the frame, and the lifting appliance is taken down.
The foregoing is merely a preferred embodiment of the present application and it is to be understood that the present application is not limited to the form disclosed herein and is not to be construed as an exclusive example of other embodiments, but is capable of use in various other combinations, modifications and environments and is capable of changes within the scope of the inventive concept, either as a result of the foregoing teachings or as a result of the knowledge or technology of the relevant art. And that modifications and variations which do not depart from the spirit and scope of the present invention are intended to be within the scope of the appended claims.
Claims (10)
1. A hoist structure that is used for aircraft engine main combustion chamber assembly, decomposition, its characterized in that: the lifting appliance structure comprises a supporting component, a profiling connecting component and a lifting component, wherein the supporting component is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting component; in the assembly and disassembly process of the main combustion chamber of the aero-engine, the main combustion chamber is hoisted or put down through the supporting component under the cooperation of the hoisting component and the external hoisting driving force.
2. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 1, wherein: the lifting assembly at least comprises a group of connecting lifting lugs (1), and the connecting lifting lugs (1) are arranged on the supporting assembly at the center of the starting point of the lifting appliance structure.
3. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 2, wherein: the connecting lifting lug (1) is provided with a plow-shaped hole (2) which gradually increases upwards, and the external lifting driving force is connected with the connecting lifting lug (1) through the plow-shaped hole (2).
4. A spreader construction for the assembly and disassembly of the main combustion chamber of an aircraft engine according to claim 1, 2 or 3, characterized in that: the support assembly comprises a support connector (3), a support connecting rod group and an adjustment locking piece group, wherein the support connecting rod group is movably connected with the support connector (3) under the cooperation of the adjustment locking piece group, the connection lifting lug (1) is fixedly connected with the support connector (3), and the free end of the support connecting rod group is detachably and fixedly connected with a main combustion chamber to be installed through the profiling connecting assembly.
5. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 4, wherein: the support connecting rod group comprises a fixed support connecting rod (4), a movable support connecting rod (5) and a sleeved support rod (6), wherein the fixed support connecting rod (4) and the sleeved support rod (6) are respectively connected with two sides of the support connecting head (3) along the same radial direction through one end part of each fixed support connecting rod, the movable support connecting rod (5) is arranged on the support connecting head (3) along the radial direction in a telescopic manner through the sleeved support rod (6) under the matching of the adjustment locking piece group, and the free ends of the fixed support connecting rod (4) and the movable support connecting rod (5) are respectively connected with a main combustion chamber to be installed in a detachable and fixed mode through profiling connecting assemblies.
6. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 5, wherein: the adjusting locking piece group comprises a group of positioning bolts (7), bolt holes are respectively formed in corresponding positions of the sleeved support rods (6) and the movable support connecting rods (5), and the movable support connecting rods (5) which are adjusted to be in position are fixedly connected with the sleeved support rods (6) through the bolt holes and the positioning bolts (7).
7. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 6, wherein: the support connector (3) is provided with a through hole, and one end of the movable support connecting rod (5) extending into the sleeve joint supporting rod (6) is sleeved with the corresponding section of the fixed support connecting rod (4) after passing through the through hole.
8. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 7, wherein: the profiling connecting assembly comprises two groups of arc-shaped connectors (8), and a group of arc-shaped connectors (8) are respectively and fixedly arranged at the connecting ends of the movable supporting connecting rod (5) and the fixed supporting connecting rod (4); in the assembly and disassembly process of the main combustion chamber of the aeroengine, each group of arc-shaped connectors (8) are detachably connected with the main combustion chamber respectively under the cooperation of the movable support connecting rod (5), the fixed support connecting rod (4) and the positioning bolt (7).
9. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 8, wherein: the outer sides of the first group of arc connectors (8) are respectively provided with a clamping groove (9), and the thickness and the depth of the clamping grooves (9) are respectively matched with the thickness and the width of the installation edge of the main combustion chamber.
10. The hanger structure for assembling and disassembling a main combustion chamber of an aircraft engine according to claim 9, wherein: along the arc direction, at least two fixing grooves (10) are sequentially arranged on the arc connector (8) at the position of the clamping groove (9), and the distance between the mounting holes of the mounting edges is matched with the distance between the two adjacent fixing grooves (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311445462.XA CN117383399A (en) | 2023-11-01 | 2023-11-01 | Lifting appliance structure for assembling and disassembling main combustion chamber of aero-engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311445462.XA CN117383399A (en) | 2023-11-01 | 2023-11-01 | Lifting appliance structure for assembling and disassembling main combustion chamber of aero-engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117383399A true CN117383399A (en) | 2024-01-12 |
Family
ID=89464637
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311445462.XA Pending CN117383399A (en) | 2023-11-01 | 2023-11-01 | Lifting appliance structure for assembling and disassembling main combustion chamber of aero-engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117383399A (en) |
-
2023
- 2023-11-01 CN CN202311445462.XA patent/CN117383399A/en active Pending
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