CN117464614A - Tool for separating compressor and combustion chamber shell of turbojet engine - Google Patents
Tool for separating compressor and combustion chamber shell of turbojet engine Download PDFInfo
- Publication number
- CN117464614A CN117464614A CN202311834894.XA CN202311834894A CN117464614A CN 117464614 A CN117464614 A CN 117464614A CN 202311834894 A CN202311834894 A CN 202311834894A CN 117464614 A CN117464614 A CN 117464614A
- Authority
- CN
- China
- Prior art keywords
- turbojet engine
- combustion chamber
- ring
- bolt
- engine compressor
- Prior art date
- 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.)
- Granted
Links
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 49
- 238000000926 separation method Methods 0.000 claims abstract description 15
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 description 4
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
Abstract
The application discloses a turbojet engine compressor and combustion chamber shell separation tool, which comprises a fixed assembly, a pressing block, a connecting bolt, an ejection bolt and a distance feedback piece; the fixing component is used for being fixed at the upper end of the combustion chamber shell; the pressing block is provided with a mounting hole and a second threaded hole; the connecting bolt is used for fixing the pressing block and the main joint; the distance feedback piece is used for displaying data measured by the distance sensor; the ejection bolt is used for propping against the upper end face of the corresponding semi-ring, and when the ejection bolt is rotated to enable the lower end of the ejection bolt to prop against the upper end face of the semi-ring, the ejection bolt is continuously rotated in the same direction, and the turbojet engine compressor can move upwards relative to the combustion chamber shell. The turbojet engine compressor is simple in structure, and can be reliably and nondestructively ejected upwards from the combustion chamber shell.
Description
Technical Field
The invention relates to a disassembling tool, in particular to a tool for separating a compressor from a combustion chamber shell of a turbojet engine.
Background
With the wider and wider application of unmanned aerial vehicles in modern war, unmanned aerial vehicles are clustered and intelligent. As the power of unmanned aerial vehicle, small-sized turbojet engine is the unmanned aerial vehicle heart, and is receiving more and more attention. The small turbojet engine has compact structure and is difficult to assemble and disassemble.
In order to prevent high-pressure gas from leaking outwards through the gap between the compressor and the combustion chamber shell, an annular sealing piece is designed between the compressor and the combustion chamber shell of the small turbojet engine, the annular sealing piece has high compression ratio, and large force is needed to separate the compressor from the combustion chamber shell during disassembly.
Disclosure of Invention
The invention aims at the problems and overcomes at least one defect, and provides a tool for separating a compressor from a combustion chamber shell of a turbojet engine.
The technical scheme adopted by the invention is as follows:
the utility model provides a turbojet engine compressor and combustion chamber casing separation instrument, has a plurality of main joints on the turbojet engine compressor, has first screw hole on the main joint, and turbojet engine compressor and combustion chamber casing separation instrument includes fixed subassembly, briquetting, connecting bolt, ejecting bolt and distance feedback piece;
the fixing assembly comprises a fixing bolt and two semi-rings, wherein the two semi-rings are respectively sleeved at the upper end of the combustion chamber shell, and are clamped and fixed at the upper end of the combustion chamber shell through the fixing bolt;
the plurality of press blocks are distributed at intervals around the axis of the fixed assembly, and each press block is provided with a mounting hole and a second threaded hole;
the connecting bolt is used for penetrating through the mounting hole of the pressing block and then fixing with the first threaded hole of the main joint, and the connecting bolt is used for fixing the pressing block and the main joint;
the distance feedback piece is fixed on the pressing block and is provided with a display screen and a distance sensor, the distance sensor is opposite to the upper surface of the semi-ring and is used for detecting the vertical distance from the upper surface of the semi-ring, and the display screen is used for displaying data measured by the distance sensor;
the ejector bolt is in threaded connection on the second threaded hole of briquetting, and ejector bolt's lower extreme is used for with the up end of corresponding semi-ring to lean on, and rotatory ejector bolt makes ejector bolt's lower extreme and the up end of semi-ring lean on the back, continues the equidirectional ejector bolt that rotates, the turbojet engine compressor can relative the combustion chamber casing upward movement.
The working principle of the application is as follows:
fastening the fixing component clamp at the upper end of the combustion chamber shell;
then the pressing block is fixed with a main joint on a compressor of the turbojet engine through a connecting bolt;
then manually rotating the ejection bolt to enable the lower end of the ejection bolt to abut against the upper end face of the corresponding semi-ring;
the distance feedback piece is opened to enable the display screen and the distance sensor to work, the display screen is used for displaying data measured by the distance sensor, when the data of the display screens are identical, the fixed assembly and the pressing block are accurately installed, and when the data are different, the installation positions of the parts are rechecked;
after the data of each display screen are the same, the ejection bolts are sequentially rotated one by one through a spanner, and the data change values in the corresponding display screens after each rotation are the same; after repeated times, the turbojet engine compressor can be reliably and nondestructively ejected upwards from the combustion chamber shell.
In the present application, the main joint is a part for connecting and fixing the turbojet engine compressor to other structures of the aircraft.
In practical use, the distance feedback piece of the application further comprises a controller, a battery and a control switch.
In one embodiment of the present invention, two ends of the half ring are provided with lugs, and the fixing bolts pass through the two corresponding lugs to fix the two half rings.
In one embodiment of the present invention, the inner diameter of the half ring is the same as the outer diameter of the combustion chamber housing, the upper end of the inner side wall of the half ring is provided with a circular arc-shaped limit strip, and the thickness of the circular arc-shaped limit strip is smaller than or equal to the thickness of the combustion chamber housing;
the semi-ring is hung on the upper end face of the combustion chamber shell through the circular arc limiting strip.
The circular arc limiting strip plays a role in positioning, and has a little anti-falling function in addition, when the combustion chamber shell is horizontal, the newly hung semi-rings can be prevented from falling from the combustion chamber shell directly.
In one embodiment of the invention, the device further comprises a diagonal bracing assembly, wherein the diagonal bracing assembly comprises a rotating rod, a resistance increasing pad and an elastic piece;
one end of the rotating rod is hinged to the outer ring side of the semi-ring, and the other end of the rotating rod is provided with the resistance increasing pad which is used for being in contact fit with the outer side wall of the combustion chamber shell;
the elastic piece is used for enabling the rotating rod to have a rotating trend of rotating towards the inner ring side of the semi-ring.
The inclined strut assembly is arranged, so that the hanging semi-rings can be prevented from falling off from the combustion chamber shell directly, and the whole operation experience is better and safer.
In an embodiment of the invention, the resistance increasing pad is arc-shaped.
In an embodiment of the invention, the elastic member is a torsion spring or a tension spring.
In one embodiment of the present invention, the half ring is provided with a recess for avoiding the main joint.
In one embodiment of the present invention, the number of the main joints is 3, and the number of the pressing blocks is 3.
In one embodiment of the present invention, the distance feedback member is fixed to the pressing block by a fastener.
In one embodiment of the present invention, the distance sensor is a laser sensor.
The beneficial effects of the invention are as follows: the turbojet engine compressor ejection device is simple in structure, and can eject the turbojet engine compressor upwards from the combustion chamber shell reliably and nondestructively.
Drawings
FIG. 1 is a schematic diagram of a tool for separating a compressor from a combustor casing of a turbojet engine of example 1;
FIG. 2 is a schematic view of embodiment 1 at another angle of the turbojet engine compressor and combustor casing separation tool;
FIG. 3 is a schematic illustration of the turbojet engine compressor and combustor casing separation tool in operation;
FIG. 4 is a top view of a turbojet engine compressor and combustor casing separation tool;
FIG. 5 is a cross-sectional view A-A of FIG. 4;
FIG. 6 is an enlarged view at B in FIG. 5;
FIG. 7 is a schematic view of an adapter, a press block, a connecting bolt, and an ejector bolt;
fig. 8 is a schematic diagram of a tool for separating a compressor from a combustor casing of the turbojet engine of example 2.
The reference numerals in the drawings are as follows:
1. a turbojet engine compressor; 11. a main joint; 111. a first threaded hole; 2. a combustion chamber housing; 3. an annular seal; 4. a fixing assembly; 41. a fixing bolt; 42. a half ring; 421. a lug; 422. avoiding the groove; 423. arc-shaped limit strips; 5. briquetting; 51. a mounting hole; 52. a second threaded hole; 6. a connecting bolt; 7. ejecting a bolt; 8. a distance feedback member; 81. a display screen; 82. a distance sensor; 83. a fastener; 9. a diagonal bracing assembly; 91. a rotating lever; 92. resistance increasing pad; 93. an elastic member.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It will be apparent that the embodiments described are some, but not all, of the embodiments of the present application. The components of the embodiments of the present application, which are generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations.
In the description of the present application, it should be noted that, the azimuth or positional relationship indicated by the terms "inner", "outer", etc. are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship that is commonly put when the product of the application is used, are merely for convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like, are used merely to distinguish between descriptions and should not be construed as indicating or implying relative importance.
In the description of the present application, it should also be noted that, unless explicitly specified and limited otherwise, the terms "disposed," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
The present invention will be described in detail with reference to the accompanying drawings.
Example 1
As shown in fig. 4, 5 and 6, an annular sealing member 3 is designed between the turbojet engine compressor 1 and the combustion chamber housing 2, the annular sealing member 3 has high compression ratio, a large force is required to separate the turbojet engine compressor 1 and the combustion chamber housing from each other during disassembly, and in addition, in order to enable the turbojet engine compressor 1 to be normally separated during disassembly, the force application is required to be uniform, and the operation difficulty is high.
As shown in fig. 1, 2, 3 and 7, a tool for separating a turbojet engine compressor from a combustion chamber shell is provided, wherein the turbojet engine compressor 1 is provided with a plurality of main joints 11, the main joints 11 are provided with first threaded holes 111, and the tool for separating the turbojet engine compressor from the combustion chamber shell comprises a fixed assembly 4, a pressing block 5, a connecting bolt 6, an ejection bolt 7 and a distance feedback piece 8;
the fixing assembly 4 comprises a fixing bolt 41 and two half rings 42, wherein the two half rings 42 are respectively sleeved at the upper end of the combustion chamber shell 2 and clamped and fixed at the upper end of the combustion chamber shell 2 through the fixing bolt 41;
the plurality of pressing blocks 5 are distributed at intervals around the axis of the fixed assembly 4, and the pressing blocks 5 are provided with mounting holes 51 and second threaded holes 52;
the connecting bolt 6 is used for penetrating through the mounting hole 51 of the pressing block 5 and then being fixed with the first threaded hole 111 of the main joint 11, and the connecting bolt 6 is used for fixing the pressing block 5 and the main joint 11;
the distance feedback piece 8 is fixed on the pressing block 5, the distance feedback piece 8 is provided with a display screen 81 and a distance sensor 82, the distance sensor 82 is opposite to the upper surface of the half ring 42 and is used for detecting the vertical distance from the upper surface of the half ring 42, and the display screen 81 is used for displaying data measured by the distance sensor 82;
the ejector bolt 7 is in threaded connection with the second threaded hole 52 of the pressing block 5, the lower end of the ejector bolt 7 is used for propping against the upper end face of the corresponding semi-ring 42, and when the ejector bolt 7 is rotated to enable the lower end of the ejector bolt 7 to prop against the upper end face of the semi-ring 42, the ejector bolt 7 is continuously rotated in the same direction, and the turbojet engine compressor 1 can move upwards relative to the combustion chamber shell 2.
The working principle of the separating tool of the embodiment is as follows:
the fixing component 4 is clamped and fixed at the upper end of the combustion chamber shell 2;
then the pressing block 5 is fixed with a main joint 11 on the turbojet engine compressor 1 through a connecting bolt 6;
then the ejection bolt 7 is manually rotated, so that the lower end of the ejection bolt 7 is propped against the upper end face of the corresponding semi-ring 42;
the distance feedback piece 8 is opened to enable the display screen 81 and the distance sensor 82 to work, the display screen 81 is used for displaying data measured by the distance sensor 82, when the data of the display screens 81 are identical, the fixed assembly 4 and the pressing block 5 are accurately installed, and when the data are different, the installation positions of the parts are rechecked;
after the data of each display screen 81 are the same, the ejection bolts 7 are sequentially rotated one by one through a spanner, and the data change values in the corresponding display screens 81 after each rotation are the same; after repeated times, the turbojet engine compressor 1 can be reliably and nondestructively ejected upwards from the combustion chamber shell 2.
In the present application, the main joint 11 is a component for connecting and fixing the turbojet engine compressor 1 to other structures of the aircraft.
In actual use, the distance feedback member 8 of the present application further comprises a controller, a battery and a control switch. In actual use, the distance sensor 82 may be a laser sensor.
As shown in fig. 1 and 2, in the present embodiment, the two ends of the half ring 42 are provided with lugs 421, and the fixing bolts 41 pass through the two corresponding lugs 421 to fix the two half rings 42.
As shown in fig. 1, 2, 4, 5 and 6, in the present embodiment, the inner diameter of the half ring 42 is the same as the outer diameter of the combustion chamber housing 2, the upper end of the inner side wall of the half ring 42 has a circular arc-shaped limiting strip 423, and the thickness of the circular arc-shaped limiting strip 423 is smaller than or equal to the thickness of the combustion chamber housing 2;
the semi-ring 42 is hung on the upper end surface of the combustion chamber shell 2 through an arc-shaped limiting strip 423.
The circular arc limiting bar 423 plays a role in positioning, and has a little anti-falling function in addition, so that the newly hung semi-ring 42 can be prevented from falling directly from the combustion chamber shell 2 when the combustion chamber shell 2 is horizontal.
In the present embodiment, as shown in fig. 1 and 3, the half ring 42 has a relief groove 422 that mates with the main joint 11.
In this embodiment, there are 3 main joints 11 and 3 compacts 5.
As shown in fig. 1, in the present embodiment, the distance feedback member 8 is fixed to the pressing block 5 by a fastener 83.
Example 2
As shown in fig. 8, the difference between the present embodiment and embodiment 1 is that in the present embodiment, the present embodiment further includes a diagonal bracing assembly 9, and the diagonal bracing assembly 9 includes a rotation rod 91, a resistance increasing pad 92, and an elastic member 93;
one end of the rotating rod 91 is hinged to the outer ring side of the half ring 42, and the other end of the rotating rod is provided with a resistance increasing pad 92, wherein the resistance increasing pad 92 is used for being in contact fit with the outer side wall of the combustion chamber shell 2;
the elastic member 93 serves to make the rotation lever 91 have a rotation tendency to rotate toward the inner ring side of the half ring 42.
The diagonal bracing assembly 9 can prevent the newly hung semi-rings 42 from directly falling off the combustion chamber shell 2, and the whole operation experience is better and safer.
In this embodiment, the resistance increasing pad 92 is arc-shaped, and the elastic member 93 is a tension spring. In other embodiments, the elastic member 93 may also be a torsion spring.
The foregoing description is only of the preferred embodiments of the present invention, and is not intended to limit the scope of the invention, but rather is intended to cover all equivalent structures as modifications within the scope of the invention, either directly or indirectly, as may be contemplated by the present invention.
Claims (10)
1. The tool for separating the turbojet engine compressor from the combustion chamber shell is characterized by comprising a fixed assembly, a pressing block, a connecting bolt, an ejection bolt and a distance feedback piece;
the fixing assembly comprises a fixing bolt and two semi-rings, wherein the two semi-rings are respectively sleeved at the upper end of the combustion chamber shell, and are clamped and fixed at the upper end of the combustion chamber shell through the fixing bolt;
the plurality of press blocks are distributed at intervals around the axis of the fixed assembly, and each press block is provided with a mounting hole and a second threaded hole;
the connecting bolt is used for penetrating through the mounting hole of the pressing block and then fixing with the first threaded hole of the main joint, and the connecting bolt is used for fixing the pressing block and the main joint;
the distance feedback piece is fixed on the pressing block and is provided with a display screen and a distance sensor, the distance sensor is opposite to the upper surface of the semi-ring and is used for detecting the vertical distance from the upper surface of the semi-ring, and the display screen is used for displaying data measured by the distance sensor;
the ejector bolt is in threaded connection on the second threaded hole of briquetting, and ejector bolt's lower extreme is used for with the up end of corresponding semi-ring to lean on, and rotatory ejector bolt makes ejector bolt's lower extreme and the up end of semi-ring lean on the back, continues the equidirectional ejector bolt that rotates, the turbojet engine compressor can relative the combustion chamber casing upward movement.
2. The turbojet engine compressor and combustor casing separation tool of claim 1, wherein the two ends of the half rings are provided with lugs, and the two half rings are fixed after the fixing bolts pass through the two corresponding lugs.
3. The turbojet engine compressor and combustor casing separation tool of claim 1, wherein the inner diameter of the half ring is the same as the outer diameter of the combustor casing, the upper end of the inner side wall of the half ring is provided with a circular arc-shaped limit strip, and the thickness of the circular arc-shaped limit strip is smaller than or equal to the thickness of the combustor casing;
the semi-ring is hung on the upper end face of the combustion chamber shell through the circular arc limiting strip.
4. The turbojet engine compressor and combustor casing separation tool of claim 3, further comprising a diagonal bracing assembly comprising a rotating rod, a resistance-increasing pad, and an elastic member;
one end of the rotating rod is hinged to the outer ring side of the semi-ring, and the other end of the rotating rod is provided with the resistance increasing pad which is used for being in contact fit with the outer side wall of the combustion chamber shell;
the elastic piece is used for enabling the rotating rod to have a rotating trend of rotating towards the inner ring side of the semi-ring.
5. The turbojet engine compressor and combustor casing separation tool of claim 4, wherein the resistance increasing pad is arcuate.
6. The turbojet engine compressor and combustor casing separation tool of claim 4, wherein the resilient member is a torsion spring or a tension spring.
7. The turbojet engine compressor and combustor casing separation tool of claim 1, wherein the half ring has relief grooves thereon that mate with the main joint.
8. The turbojet engine compressor and combustor casing separation tool of claim 1 wherein there are 3 main joints and 3 briquettes.
9. The turbojet engine compressor and combustor casing separation tool of claim 1, wherein the distance feedback member is secured to the compact by a fastener.
10. The turbojet engine compressor and combustor casing separation tool of claim 1, wherein the distance sensor is a laser sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311834894.XA CN117464614B (en) | 2023-12-28 | 2023-12-28 | Tool for separating compressor and combustion chamber shell of turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311834894.XA CN117464614B (en) | 2023-12-28 | 2023-12-28 | Tool for separating compressor and combustion chamber shell of turbojet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117464614A true CN117464614A (en) | 2024-01-30 |
| CN117464614B CN117464614B (en) | 2024-04-02 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311834894.XA Active CN117464614B (en) | 2023-12-28 | 2023-12-28 | Tool for separating compressor and combustion chamber shell of turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117464614B (en) |
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| CN102615623A (en) * | 2012-04-19 | 2012-08-01 | 西安飞机工业（集团）有限责任公司 | Mounting and dismounting tool for bush with double lug holes |
| CN104400749A (en) * | 2014-11-24 | 2015-03-11 | 歌尔声学股份有限公司 | Rubber gasket assembling device and rubber gasket assembling method |
| CN106938454A (en) * | 2017-04-25 | 2017-07-11 | 上海众源燃油分配器制造有限公司 | A kind of device assembled for high pressure oil rail seal nipple |
| CN111300316A (en) * | 2019-12-23 | 2020-06-19 | 苏州智华汽车电子有限公司 | A tool for equipment of on-vehicle camera dustcoat |
| CN113532870A (en) * | 2021-08-11 | 2021-10-22 | 中国科学院力学研究所 | Online identification system for working mode of engine |
| CN113910139A (en) * | 2021-10-09 | 2022-01-11 | 中船澄西船舶修造有限公司 | Fixing tool for expansion joint of desulfurizing tower |
| CN115182814A (en) * | 2022-04-13 | 2022-10-14 | 南京理工大学 | Rotary detonation turbine engine device |
| CN219704840U (en) * | 2023-05-29 | 2023-09-19 | 清航空天(北京)科技有限公司 | Fixed frock of dismantling of turbojet engine rotor and stator |
-
2023
- 2023-12-28 CN CN202311834894.XA patent/CN117464614B/en active Active
Patent Citations (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1231027A2 (en) * | 2001-02-12 | 2002-08-14 | Rothenberger Werkzeuge Aktiengesellschaft | Press head for connecting pipes |
| US20050120701A1 (en) * | 2003-12-08 | 2005-06-09 | Child Malcolm S. | Nozzle bolting arrangement for a turbine |
| CN102335901A (en) * | 2011-09-28 | 2012-02-01 | 河南省通信电缆有限公司 | Rotary installation machine of movable optical-fiber connector |
| CN102615623A (en) * | 2012-04-19 | 2012-08-01 | 西安飞机工业（集团）有限责任公司 | Mounting and dismounting tool for bush with double lug holes |
| CN104400749A (en) * | 2014-11-24 | 2015-03-11 | 歌尔声学股份有限公司 | Rubber gasket assembling device and rubber gasket assembling method |
| CN106938454A (en) * | 2017-04-25 | 2017-07-11 | 上海众源燃油分配器制造有限公司 | A kind of device assembled for high pressure oil rail seal nipple |
| CN111300316A (en) * | 2019-12-23 | 2020-06-19 | 苏州智华汽车电子有限公司 | A tool for equipment of on-vehicle camera dustcoat |
| CN113532870A (en) * | 2021-08-11 | 2021-10-22 | 中国科学院力学研究所 | Online identification system for working mode of engine |
| CN113910139A (en) * | 2021-10-09 | 2022-01-11 | 中船澄西船舶修造有限公司 | Fixing tool for expansion joint of desulfurizing tower |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN117464614B (en) | 2024-04-02 |
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