CN113898614A - Decomposition process of aeroengine fan outlet guide blade assembly - Google Patents
Decomposition process of aeroengine fan outlet guide blade assembly Download PDFInfo
- Publication number
- CN113898614A CN113898614A CN202010574091.5A CN202010574091A CN113898614A CN 113898614 A CN113898614 A CN 113898614A CN 202010574091 A CN202010574091 A CN 202010574091A CN 113898614 A CN113898614 A CN 113898614A
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- CN
- China
- Prior art keywords
- clamping plate
- casing
- guide
- guide vanes
- whole circle
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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.)
- Pending
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 230000008569 process Effects 0.000 title claims abstract description 18
- 238000000354 decomposition reaction Methods 0.000 title claims description 12
- 230000004048 modification Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 206010057071 Rectal tenesmus Diseases 0.000 description 1
- 230000009471 action Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 208000012271 tenesmus Diseases 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/60—Mounting; Assembling; Disassembling
- F04D29/601—Mounting; Assembling; Disassembling specially adapted for elastic fluid pumps
Abstract
The invention aims to provide a process for disassembling an aircraft engine fan outlet guide vane assembly, which can disassemble a whole ring guide vane from a casing. Mounting a lower clamping plate on the lower flange edge of the whole circle of guide vanes, and mounting an upper clamping plate on the upper flange edge of the whole circle of guide vanes; tensioning the upper clamping plate and the lower clamping plate by using a long screw and a nut so that the whole circle of guide vanes is clamped between the upper clamping plate and the lower clamping plate; removing the threaded fastener of the guide vane and the casing; the casing and the guide blade are lifted simultaneously through the lifting device; uniformly applying downward force along the circumferential direction of the outer edge of the casing until the casing is separated from the guide blade; transferring the whole circle of guide vanes to a platform; and loosening the long screw and the nut, and removing the upper clamping plate and the lower clamping plate to enable the guide vanes to be scattered into single parts.
Description
Technical Field
The invention relates to a process for disassembling an aircraft engine fan outlet guide vane assembly.
Background
The stator assembly shown in fig. 1 and 2, namely the aircraft engine fan outlet guide vane assembly, is an important component of an aircraft engine, and the main functions of the stator assembly are flow guiding and force bearing. The assembly is composed of a plurality of fan outlet guide blades (also referred to as OGVs or guide vanes or guide blades or vanes) 2 and a casing 1, the guide vanes 2 being fixed to the inner wall of the casing 1 by means of threaded fasteners 4 to form a complete ring. For the load carrying capacity that improves the stator subassembly, the interior flange plate 22 of guide vane 2 designs into the sloping platform structure, and when forming the whole ring, mutual interlock between the guide vane, every blade can both bear the radial force of rotor, and the load carrying capacity of stator subassembly increases by a wide margin, and life also improves by a wide margin. For the guide vane, a process of decomposing one vane by one vane is adopted in the traditional process, and because the inner edge plates of the vanes are of the frustum structures and are mutually meshed, the decomposition of a single vane can not be realized in one step, and the vane can be pulled out of a casing only by adopting spiral decomposition. When the blades are disassembled, one blade is selected, the middle section of the blade is pinched by two hands, the blade is pulled loose along the direction of the inclined table by applying force upwards, as shown in figure 1, the next adjacent guide vane 2 is selected in the clockwise direction, the adjacent guide vane is pulled loose by adopting the same operation, and the rest guide vanes are sequentially selected according to the mode and pulled loose until the whole circle of the blades are pulled loose; pulling the first guide vane upwards for a short distance according to the sequence of the vanes, and pulling the next adjacent guide vane upwards for the same distance in the clockwise direction until the whole circle of guide vanes are pulled upwards for the same distance; by adopting the mode, the next round of small-amplitude pulling-up is carried out according to the sequence of the vanes, the operation is repeated for a plurality of rounds until the circumferential activity between adjacent vanes is increased and the vanes are not engaged any more after all the vanes are pulled out of the casing beyond the height 2/3 in the axial direction, and all the vanes are taken out of the casing 1 piece by piece according to the sequence of the vanes. This kind of decomposition mode, the experience requirement to the operation workman is higher, the operation workman will guarantee when decomposing that the pulling-out volume of every round of every blade is roughly the same, in case certain stator pulling-out volume is too big appears, will cause all stator to be stung each other, the stator becomes undecomposable, in addition, the stator is when pulling out, receives the gravity influence, can't avoid having the tenesmus tendency, the stator does not have fixing device, needs many operators to cooperate each other, every people both hands hold several stator for whole circle stator maintains same height.
The single-piece decomposition mode is complicated, the decomposition period is long, multiple persons are needed for cooperation, the guide vanes can be completely decomposed through 8-10 rounds of operation, the guide vanes are converted into one-person working equivalent, all the guide vanes can be decomposed generally in more than 4 hours, errors are easy to occur during operation, and the guide vanes are blocked and cannot be decomposed.
Disclosure of Invention
The invention aims to provide a process for disassembling an aircraft engine fan outlet guide vane assembly, which can disassemble a whole ring guide vane from a casing.
In order to achieve the purpose, the decomposition process of the aircraft engine fan outlet guide blade assembly, aiming at the fan outlet guide blade assembly comprising a casing and a whole circle of guide blades inserted and fixed in the casing, comprises the following steps:
mounting a lower clamping plate on the lower flange edge of the whole circle of guide vanes, and mounting an upper clamping plate on the upper flange edge of the whole circle of guide vanes;
tensioning the upper clamping plate and the lower clamping plate by using a long screw and a nut so that the whole circle of guide vanes is clamped between the upper clamping plate and the lower clamping plate;
removing the threaded fastener of the guide vane and the casing;
the casing and the guide blade are lifted simultaneously through the lifting device;
uniformly applying downward force along the circumferential direction of the outer edge of the casing until the casing is separated from the guide blade;
transferring the whole circle of guide vanes to a platform; and
and loosening the long screw and the nut, and removing the upper clamping plate and the lower clamping plate to disperse the guide vanes into single parts.
In one or more embodiments, the upper or lower jaw is configured to include an inner ring, an outer ring spaced apart from the inner ring, and a plurality of bridges connected between the inner ring and the outer ring.
In one or more embodiments, the elongated bolt is connected between the bridge portions of the upper and lower splints.
In one or more embodiments, an eye bolt is fixed to the upper clamping plate, and then a universal three-jaw spreader is mounted to the eye bolt, and the lifting device grabs the three-jaw spreader to lift the casing and the guide blade simultaneously.
In one or more embodiments, the eye bolt is secured to the inner ring of the upper clamp plate.
In one or more embodiments, the casing is struck evenly downward along its circumference with a rubber hammer until the casing disengages from the guide vanes.
The scheme breaks through the conventional method of decomposing parts one by one, and creatively provides a process method for decomposing the blades in a whole ring, so that factors such as inclined platforms and different structural sizes cannot become the limiting conditions for the decomposition of the guide vanes;
an upper clamping plate and a lower clamping plate are designed by depending on a mounting flange of the blade, and the upper clamping plate and the lower clamping plate are clamped by a screw nut, so that the whole circle of blade is clamped between the upper clamping plate and the lower clamping plate to form a whole, and the influence of the structural size of the blade on the clamping and fixing of the guide vane is avoided;
after the guide vane is integrally decomposed, the upper clamping plate and the lower clamping plate are disassembled, the guide vane can be scattered into a single zero level, parts are prevented from being decomposed one by one, and the decomposition difficulty of the guide vane is reduced.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings, in which:
FIG. 1 is a schematic illustration of an aircraft engine fan outlet guide vane assembly.
FIG. 2 is a partial cross-sectional view of an aircraft engine fan outlet guide vane assembly.
Fig. 3 is a schematic view of a guide vane in a full ring shape (a full ring guide vane) connected to a fixing tool.
Fig. 4 is a partial sectional view of a full ring vane in connection with a fixture.
FIG. 5 is a schematic illustration of an exploded process of an aircraft engine fan outlet guide vane assembly.
Fig. 6 is a schematic view of a fixture.
Fig. 7 is a half sectional view of the fixing tool.
Detailed Description
The following discloses many different embodiments or examples for implementing the subject technology described. Specific examples of components and arrangements are described below to simplify the present disclosure, but these are merely examples and do not limit the scope of the invention. For example, if a first feature is formed over or on a second feature described later in the specification, this may include embodiments in which the first and second features are formed in direct contact, and may also include embodiments in which additional features are formed between the first and second features, such that the first and second features may not be in direct contact. Additionally, reference numerals and/or letters may be repeated among the various examples throughout this disclosure. This repetition is for the purpose of simplicity and clarity and does not in itself dictate a relationship between the various embodiments and/or configurations discussed. Further, when a first element is described as being coupled or coupled to a second element, the description includes embodiments in which the first and second elements are directly coupled or coupled to each other, as well as embodiments in which one or more additional intervening elements are added to indirectly couple or couple the first and second elements to each other.
The process of disassembling the aircraft engine fan outlet guide vane assembly is described in detail below with reference to fig. 1-7. As shown in fig. 1 and 2, the fan outlet guide blade assembly includes a casing 1 and a full circle of guide blades 2 inserted and fixed in the casing 1. As shown in fig. 2, the inner edge plate 22 of the guide vane 2 has a mounting flange 21 including an upper flange edge 210 and a lower flange edge 211 spaced apart in the axial direction, where the terms "upper" and "lower" are referred to the state of the casing 1, when the inlet of the casing 1 for inserting the guide vane 2 is directed upward. The upper flange 210 of the complete ring of guide vanes 2 forms an annular structure, as does the lower flange of the complete ring of guide vanes 2.
As shown in fig. 3 and 4, the lower clip 9 is attached to the lower flange 211 of the full turn guide vane 2, and the upper clip 5 is attached to the upper flange 210 of the full turn guide vane 2. Fig. 6 shows the shape of the upper and lower jaws 5, 9, which are a full ring.
With continued reference to fig. 3 and 4 and 6, the upper and lower clamping plates 5, 9 are tightened with the long screw 6 and the nut 7 so that the complete turn of the guide vane 2 is clamped between the upper and lower clamping plates 5, 9, which corresponds to connecting the complete turn of the guide vane 2 into one piece.
The threaded fasteners 4 of the guide vane 2 and the casing 1 are removed, and the guide vane 2 and the casing 1 are held together by friction force formed by mutual cooperation.
Subsequently, as shown in fig. 5, the casing 1 and the guide blade 2 are lifted simultaneously by the lifting device, and the casing 1 is still held by the guide blade 2 by its own weight, which cannot overcome the frictional force therebetween.
In a suspended state, downward force F is uniformly applied along the circumferential direction of the outer edge of the casing 1 until the casing 1 is separated from the guide blade 2, and at the moment, the whole circle of guide blades 2 are still connected into a whole. The action of disengaging the guide vanes 2 may be stepwise.
Next, the complete turn of the guide vane 2 is transferred to the platform, by which the complete turn of the guide vane 2 is supported.
Then, the long screw 6 and the nut 4 are loosened, the upper clamping plate 5 and the lower clamping plate 9 are removed, and the guide vane 2 can be scattered into single parts.
During the detachment of the casing 1 and the guide blades 2, the guide blades cannot be detached from one another because the entire guide blade 2 remains integral during the entire detachment process. According to the steps, the guide vane does not need to be supported by a plurality of people, the whole circle of guide vanes is lifted by the lifting device, and the guide vane can be decomposed by a single person.
Fig. 6 and 7 show a specific structure of the fixing tool, and the upper clamp plate 5 is configured to include an inner ring 52, an outer ring 51, and bridges 53, the inner ring 52 and the outer ring 51 being spaced apart, and a plurality of bridges 53 being connected between the inner ring 52 and the outer ring 51. Likewise, the lower plate 9 is also configured to include an inner ring 92, an outer ring 91, and a plurality of bridge portions 93, the inner ring 92 and the outer ring 91 being spaced apart, the plurality of bridge portions 93 being connected between the inner ring 92 and the outer ring 91. Each splint passes through the bridge portion and connects two annular shapes, can realize the bulk strength of frock, forms the space between two annular shapes, sees through the inside connection condition that can see through the space, and two annular shapes provide the portion of gripping, the operation of being convenient for, adjustment, transport, and material has still been saved to this kind of structure in addition, has lightened the weight of frock.
Referring to fig. 6 and 7, the long bolt 6 connects between the bridging portions 53, 93 of the upper and lower clamping plates 5, 9. In this way, the long bolts 6 transmit the fastening force to the bridge parts 53, 93, to the respective outer rings 51, 91, and to the upper and lower flange sides of the full-circle guide vane 2, while the respective inner rings 52 receive the tensile force of the hoisting device, and the bridge parts 53, 93 distribute the force to the inner and outer rings.
As shown in fig. 5 to 7, the eye bolt 8 is fixed to the upper clamp plate 5, and then a general three-jaw hanger is mounted on the eye bolt 8, and a lifting device hooks the three-jaw hanger to lift the receiver 1 and the guide blade 2 at the same time. A three jaw spreader is shown schematically in figure 5. The three-jaw lifting appliance is used for lifting, so that the lifting process is quicker, and the stress of the tool is more uniform.
The eyebolt 8 is fixed to the inner ring 52 of the upper clamping plate 5 to make the distribution of the stress of the tool more reasonable.
One way of applying the force F is by striking it evenly downward with a rubber hammer along the circumference of the casing until the casing is disengaged from the guide vanes, as shown in fig. 5. Even if a rubber hammer is used for knocking, the whole ring of guide vanes are restrained, so that the casing is easy to have component force with the guide vanes, and the clamping condition cannot occur.
Although the present invention has been disclosed in terms of the preferred embodiment, it is not intended to limit the invention, and variations and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention. Therefore, any modification, equivalent change and modification of the above embodiments according to the technical essence of the present invention are within the protection scope defined by the claims of the present invention, unless the technical essence of the present invention departs from the content of the present invention.
Claims (6)
1. Aeroengine fan outlet guide vane subassembly's decomposition technology, this fan outlet guide vane subassembly include cartridge and fix whole circle guide vane in the cartridge, its characterized in that includes:
mounting a lower clamping plate on the lower flange edge of the whole circle of guide vanes, and mounting an upper clamping plate on the upper flange edge of the whole circle of guide vanes;
tensioning the upper clamping plate and the lower clamping plate by using a long screw and a nut so that the whole circle of guide vanes is clamped between the upper clamping plate and the lower clamping plate;
removing the threaded fastener of the guide vane and the casing;
the casing and the guide blade are lifted simultaneously through the lifting device;
uniformly applying downward force along the circumferential direction of the outer edge of the casing until the casing is separated from the guide blade;
transferring the whole circle of guide vanes to a platform;
and loosening the long screw and the nut, and removing the upper clamping plate and the lower clamping plate to disperse the guide vanes into single parts.
2. The disassembly process of claim 1, wherein the upper or lower clamp plate is configured to include an inner ring, an outer ring, and a plurality of bridges connected between the inner and outer rings.
3. The disassembly process of claim 2, wherein the long bolt is coupled between the bridge portions of the upper and lower jaws.
4. The disassembly process of claim 1, wherein an eye bolt is fixed to the upper clamping plate, and then a universal three-jaw hanger is mounted to the eye bolt, and the lifting device grabs the three-jaw hanger to lift the casing and the guide blade simultaneously.
5. The disassembly process of claim 4, wherein the eye bolt is secured to the inner ring of the upper clamp plate.
6. The decomposition process according to claim 1, wherein the casing is uniformly struck downward by a rubber hammer along the circumference of the outer edge of the casing until the casing is separated from the guide vanes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010574091.5A CN113898614A (en) | 2020-06-22 | 2020-06-22 | Decomposition process of aeroengine fan outlet guide blade assembly |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010574091.5A CN113898614A (en) | 2020-06-22 | 2020-06-22 | Decomposition process of aeroengine fan outlet guide blade assembly |
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| Publication Number | Publication Date |
|---|---|
| CN113898614A true CN113898614A (en) | 2022-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202010574091.5A Pending CN113898614A (en) | 2020-06-22 | 2020-06-22 | Decomposition process of aeroengine fan outlet guide blade assembly |
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|---|---|---|---|---|
| KR20000011751U (en) * | 1998-12-08 | 2000-07-05 | 김형국 | Nozzle Segment Disassembly Tool |
| CN104093938A (en) * | 2011-12-09 | 2014-10-08 | 通用电气公司 | Quick engine change assembly for outlet guide vanes |
| CN204640099U (en) * | 2015-04-30 | 2015-09-16 | 中国航空动力机械研究所 | Provision for disengagement |
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| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| CN209291768U (en) * | 2018-12-18 | 2019-08-23 | 中国航发沈阳发动机研究所 | Engine low-pressure turbine turns stator and hangs division of labor dress |
| US20190271330A1 (en) * | 2016-11-15 | 2019-09-05 | Genera! Electric Company | Inlet guide vane removal tools and methods |
| CN209396765U (en) * | 2018-12-06 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | The fixture for lifting and overturning for turbine rear casing |
| CN110497355A (en) * | 2019-08-30 | 2019-11-26 | 中国航发动力股份有限公司 | A kind of decomposition mechanism of matable assembly |
| CN110695910A (en) * | 2019-10-30 | 2020-01-17 | 中船动力有限公司 | Tool and method for disassembling and assembling exhaust valve and valve seat of diesel engine |
| CN210010912U (en) * | 2019-06-05 | 2020-02-04 | 中国航发商用航空发动机有限责任公司 | Assembly tool for split case |
-
2020
- 2020-06-22 CN CN202010574091.5A patent/CN113898614A/en active Pending
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20000011751U (en) * | 1998-12-08 | 2000-07-05 | 김형국 | Nozzle Segment Disassembly Tool |
| CN104093938A (en) * | 2011-12-09 | 2014-10-08 | 通用电气公司 | Quick engine change assembly for outlet guide vanes |
| CN204640099U (en) * | 2015-04-30 | 2015-09-16 | 中国航空动力机械研究所 | Provision for disengagement |
| CN107214659A (en) * | 2016-03-22 | 2017-09-29 | 中国航发商用航空发动机有限责任公司 | Rectifier fan-shaped section handler and rectifier fan-shaped section handling method |
| US20190271330A1 (en) * | 2016-11-15 | 2019-09-05 | Genera! Electric Company | Inlet guide vane removal tools and methods |
| CN107584273A (en) * | 2017-10-23 | 2018-01-16 | 中国航发成都发动机有限公司 | A kind of engine turbine blade integral installation and provision for disengagement and method |
| CN209396765U (en) * | 2018-12-06 | 2019-09-17 | 中国航发商用航空发动机有限责任公司 | The fixture for lifting and overturning for turbine rear casing |
| CN209291768U (en) * | 2018-12-18 | 2019-08-23 | 中国航发沈阳发动机研究所 | Engine low-pressure turbine turns stator and hangs division of labor dress |
| CN210010912U (en) * | 2019-06-05 | 2020-02-04 | 中国航发商用航空发动机有限责任公司 | Assembly tool for split case |
| CN110497355A (en) * | 2019-08-30 | 2019-11-26 | 中国航发动力股份有限公司 | A kind of decomposition mechanism of matable assembly |
| CN110695910A (en) * | 2019-10-30 | 2020-01-17 | 中船动力有限公司 | Tool and method for disassembling and assembling exhaust valve and valve seat of diesel engine |
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