CN208380978U - A kind of low-pressure compressor casing assembling unit structure - Google Patents
A kind of low-pressure compressor casing assembling unit structure Download PDFInfo
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- CN208380978U CN208380978U CN201820511266.6U CN201820511266U CN208380978U CN 208380978 U CN208380978 U CN 208380978U CN 201820511266 U CN201820511266 U CN 201820511266U CN 208380978 U CN208380978 U CN 208380978U
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Abstract
A kind of low-pressure compressor casing assembling unit structure described in the utility model, including inner ring, casing, several blades being mounted between inner ring and casing, the inner ring and casing are integrally-built cylindrical shape, the height of the casing is high compared with the height of inner ring, the inner ring is located in casing, the two axle center is overlapped, several described blades are radially mounted to be fixed between inner ring and casing.The structure design of the utility model is reasonable, meets functional requirement, while high-quality, for ease of maintenaince and cost performance is high, especially suitable for aero-engine, missile propulsive plant.
Description
Technical field
The utility model relates to aero-engines, and in particular to a kind of low pressure aerostatic press casing assembling unit structure.
Background technique
Current aerospace engine, missile propulsive plant low-pressure compressor casing sub-assembly mostly use band edge plate leaf piece and casing
Whole electron beam welding structure.Blade is needed by being largely machined into type after precision forging, and casing needs isothermal forging blank to pass through
Casing and blade are finally carried out permanent connection using vacuum electron beam welding by machining molding.This structure is calmed the anger
The machine casing sub-assembly manufacturing cycle is long, at high cost, and maintenance cost is higher.
" a kind of axial flow compressor rotor with water conservancy diversion vanelets " disclosed in CN105927584A, including rotor blade,
Casing, wheel hub are also equipped with water conservancy diversion vanelets on the casing；The prismatic blade of the water conservancy diversion vanelets dual arc blade profile, water conservancy diversion are small
Blade root is connected with casing upstream, and circumferentially uniformly distributed on casing；Water conservancy diversion vanelets axial position is located at rotor blade leaf top
The leaf top chord strong point of upstream 10%-30%, the bending directions of water conservancy diversion vanelets is towards the direction of rotation of rotor blade.The invention makes leaf
It pushes up area's channel airflow angle of attack and invasin reduces, reduce the load of Ye Dingqu, it is suppressed that rotor blade blade-tip leakage flow is stifled
Plug flow road.The stable operation range for expanding compressor rotor improves the flow nargin of compressor.Compared with leaf top gas jet technique,
Guide-vane processor box is easy for installation, and structure is simple.Energy is provided without the external world, and saves industrial manufacturing cost.
CN203856770U is disclosed " a kind of compressor casing ", including assemblnig the first half casing and the second half machines
It is barrel-like structure after casket, the first half casings and the second half casing assemblings；The first half casings include the first installation side, the first half casings
It extends outwardly to form the first installation side with the opposite installation end of the second half casings；The second half casings include the second installation side, the
The opposite installation end of 2 half casings and the first half casings extends outwardly to form the second installation side；First installation side and the second installation
Side alignment is affixed.Its compressor casing structure is simple, number of parts is few, light-weight.After the casing, when assembling and disassembling stator blade
It is not necessary to decompose rotor blade, balance quality of rotor will not be destroyed.
The above-mentioned prior art all without solving existing for the low-pressure compressor casing sub-assembly for aero-engine very well
Problem.Therefore, it is necessary to develop it is a kind of it is high-quality, for ease of maintenaince, the high low-pressure compressor casing assembling unit structure of comprehensive cost performance.
Summary of the invention
It is reasonable in design the purpose of the utility model is to provide a kind of low pressure aerostatic press casing assembling unit structure, it is full
Sufficient functional requirement, at the same it is high-quality, for ease of maintenaince and cost performance is high, especially suitable for aero-engine, missile propulsive plant.
A kind of low pressure aerostatic press casing assembling unit structure described in the utility model, including inner ring, casing, it is mounted on inner ring
Several blades between casing, it is characterized in that: the inner ring and casing are integrally-built cylindrical shape, the casing
Height is high compared with the height of inner ring, and the inner ring is located in casing, and the two axle center is overlapped, several described blades are radially mounted solid
It is scheduled between inner ring and casing.
Further, radial equidistant on the wall of the inner ring to be equipped with several internal lobe type grooves, the upper end of the inner ring is under
End is equipped with seal coating；
The lower part of the casing wall is radial equidistant to be equipped with several siphonal lobe type grooves identical with internal lobe type groove center line, institute
The number for stating the siphonal lobe type groove of casing is equal with the number of internal lobe type groove.
Further, the blade is no shroud blade, and number is equal with the number of the siphonal lobe type groove；One end of the blade
It is cooperatively connected from the siphonal lobe type groove insertion on the outside of casing with the internal lobe type groove on the internal ring wall, and by pressing, being brazed fixation,
Siphonal lobe type groove on the other end and the casing wall is cooperatively connected, and by pressing, being brazed fixation.
Further, the outer wall top of the casing is equipped with the reinforcing rib of multiple tracks annular.
The utility model relative to traditional aero-engine or the low-pressure compressor casing assembling unit structure of missile propulsive plant,
It has the advantages that
A. in terms of quality；
Since casing is overall structure, casing and inner ring are manufactured using spinning process, the blade manufactured using roller mutual aid system devised for poor peasants skill,
Metal material is after squeezing flowing, and tissue more refinement is fine and close, and intensity is higher；Part after spinning or roller are pricked, chipping allowance
Few, part cutting stress is smaller, and deflection is smaller；
B. in terms of the manufacturing cycle；
This structure is related to that machining is less, the 10-15% of traditional structure casing machining amount is accounted for, although sheet-metal formed
Technique also occupies certain manufacturing cycle, but the manufacturing cycle shortens for entirety.
C. maintenance aspect；
After the blade damage of original structure, it is such as changed without casing, is needed using the techniques rebladings such as laser melting coating, cost
Higher, this structure only needs to remove blade using machining mode, ressembles, presses, being brazed new blade, therefore tieing up
Accomplish this and efficiency is superior to original structure.
D. in terms of cost；
For entirety, using new construction, new process, either raw material investment or the manufacturing cycle is reduced, therefore at
This opposite original structure reduces, and has competitive advantage.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of the utility model；
Fig. 2 is the A of Fig. 1 to partial enlarged view；
Fig. 3 is the axonometric drawing of the utility model.
In figure: 1-inner ring, 2-blades, 3-casings, 4-reinforcing ribs, 5-blade profile slots.
Specific embodiment
The utility model is described further with reference to the accompanying drawing.
Referring to Fig. 1 and a kind of low pressure aerostatic press casing assembling unit structure shown in Fig. 3, including inner ring 1, casing 3, be located in
Several blades 2 between ring and casing, it is characterized in that:
The inner ring 1 and casing 3 are integrally-built cylindrical shape, and the height of the casing 3 is high compared with the height of inner ring 1,
The inner ring 1 is located in casing 3, and the two axle center is overlapped, several described blades 2 are radially mounted to be fixed on inner ring 1 and casing 3
Between.Inner ring and casing are all made of rotary press modelling, not only can guarantee uniform wall thickness, but also organize more refinement fine and close, and intensity is more
It is high.
Equidistant on the wall of the inner ring 1 to be equipped with several internal lobe type grooves, the top and bottom of the inner ring, which are equipped with, obturages
Coating, for cooperating progress air-flow to obturage with rotor comb tooth when work；Internal lobe type groove is manufactured using Sheet Metal Forming Technology, to guarantee blade profile
The consistency of slot.The lower part of 3 wall of casing is equidistant equipped with several siphonal lobe type grooves 5 identical with internal lobe type groove, described outer
The number of blade profile slot 5 is equal with the number of internal lobe type groove.Internal lobe type groove and siphonal lobe type groove 5 are manufactured using Sheet Metal Forming Technology, to guarantee
The consistency of inside and outside blade profile slot.
The blade 2 is no shroud blade (there was only blade, not the blade of listrium), the outer blade profile of number and the casing
The number of slot 5 is equal；Blade is bundled into type using stainless steel belt roller, and quality is stablized, while also ensuring good consistency.It is described
One end of blade 2 is cooperatively connected from the insertion of siphonal lobe type groove 5 in 3 outside of casing with the internal lobe type groove on 1 wall of inner ring, and passes through
It presses, be brazed fixation, the siphonal lobe type groove 5 on the other end and 3 wall of casing is cooperatively connected, and by pressing, being brazed fixation.It is interior
Ring, blade, the dual permanent connection mode for being pressed+being brazed using cross between casing three, ensure that the reliability of product.
The outer wall top of the casing 3 is equipped with the reinforcing rib 4 of multiple tracks annular.
When assembling, sequentially include the following steps:
A. on non-standard equipment that inner ring 1 and casing 3 is fixed, guarantee the concentric and phase of the two with the characteristic of equipment itself
To height；
B. the blade 2 of no hat is inserted on the outside of casing, with the unique dress of axial restraint ring+radially fixed environmental protection card blade
With position；
C. cross is carried out to external end head in blade 2 one by one in such a way that the special riveted joint in equipment is symmetrical using 180 °
It presses, blade 2, casing 3,1 three of inner ring is fixed up；
D. it will be cleaned up at riveting with acetone, smear solder later, in such a way that flame gun is symmetrical using 180 °
External end head in blade is brazed one by one；
E. stress-relieving by beat treatment is carried out after the completion of welding；
F. side is installed to the front and back of this structure after and inner ring carries out turning and drilling；
G. position plasma spraying abradable coating and turning coating are reenacted after the completion of machining.
When air-flow flows through the casing through rotor acting, the special flow passage formed using inner ring, blade and casing is to air-flow
It is compressed and is rectified, so that the gas for obtaining regulation pressure is mixed for combustion chamber and fired.
Claims (4)
1. a kind of low-pressure compressor casing assembling unit structure, including inner ring (1), casing (3) and several blades (2), feature
Be: the inner ring (1) and casing (3) are integrally-built cylindrical shape, the height of the height of the casing (3) compared with inner ring (1)
Height, the inner ring (1) are located in casing (3), and the two axle center is overlapped, several described blades (2) are radially mounted be fixed in
Between ring (1) and casing (3).
2. low-pressure compressor casing assembling unit structure according to claim 1, it is characterized in that: on the wall of the inner ring (1)
Equidistant to be equipped with several internal lobe type grooves, the top and bottom of the inner ring are equipped with seal coating；The lower part of casing (3) wall
It is radial equidistant to be equipped with several siphonal lobe type grooves (5) identical with internal lobe type groove, the number and interior blade profile of the siphonal lobe type groove (5)
The number of slot is equal, and axis is overlapped.
3. low-pressure compressor casing assembling unit structure according to claim 2, it is characterized in that: the blade (2) is no hat
Blade, number are equal with the number of the siphonal lobe type groove (5)；One end of the blade (2) is from the siphonal lobe type groove on the outside of casing (3)
(5) it is inserted into and is cooperatively connected with the internal lobe type groove on the inner ring (1) wall, and by pressing, being brazed fixation, the other end and the machine
Blade profile slot (5) on casket (3) wall is cooperatively connected, and by pressing, being brazed fixation.
4. low-pressure compressor casing assembling unit structure according to claim 1 or 2, it is characterized in that: the casing (3) is outer
Wall top is equipped with the reinforcing rib (4) of multiple tracks annular.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820511266.6U CN208380978U (en) | 2018-04-11 | 2018-04-11 | A kind of low-pressure compressor casing assembling unit structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820511266.6U CN208380978U (en) | 2018-04-11 | 2018-04-11 | A kind of low-pressure compressor casing assembling unit structure |
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| Publication Number | Publication Date |
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| CN208380978U true CN208380978U (en) | 2019-01-15 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN113878191A (en) * | 2021-09-09 | 2022-01-04 | 中国航发南方工业有限公司 | Multistage vacuum brazing processing method for high-pressure turbine guide component |
| CN114043109A (en) * | 2021-12-15 | 2022-02-15 | 中国航发动力股份有限公司 | Composite connection method of large-size round-square 3D printer case |
| CN114962338A (en) * | 2022-04-27 | 2022-08-30 | 四川航天中天动力装备有限责任公司 | Split type stator casing structure of turbojet engine and assembly method thereof |
-
2018
- 2018-04-11 CN CN201820511266.6U patent/CN208380978U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110617115A (en) * | 2019-10-29 | 2019-12-27 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN110617115B (en) * | 2019-10-29 | 2021-11-02 | 北京动力机械研究所 | Turbine engine guide ring assembly produced by additive manufacturing mode |
| CN113878191A (en) * | 2021-09-09 | 2022-01-04 | 中国航发南方工业有限公司 | Multistage vacuum brazing processing method for high-pressure turbine guide component |
| CN114043109A (en) * | 2021-12-15 | 2022-02-15 | 中国航发动力股份有限公司 | Composite connection method of large-size round-square 3D printer case |
| CN114962338A (en) * | 2022-04-27 | 2022-08-30 | 四川航天中天动力装备有限责任公司 | Split type stator casing structure of turbojet engine and assembly method thereof |
| CN114962338B (en) * | 2022-04-27 | 2024-04-12 | 四川航天中天动力装备有限责任公司 | Split stator casing structure of turbojet engine and assembly method thereof |
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Effective date of registration: 20200416 Granted publication date: 20190115 |
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