CN203584577U - Connecting structure of gas compressor and turbine - Google Patents
Connecting structure of gas compressor and turbine Download PDFInfo
- Publication number
- CN203584577U CN203584577U CN201320813369.5U CN201320813369U CN203584577U CN 203584577 U CN203584577 U CN 203584577U CN 201320813369 U CN201320813369 U CN 201320813369U CN 203584577 U CN203584577 U CN 203584577U
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- Prior art keywords
- turbine
- gas compressor
- drum barrel
- linkage structure
- axle
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- 235000004443 Ricinus communis Nutrition 0.000 claims description 20
- 244000126211 Hericium coralloides Species 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 238000007789 sealing Methods 0.000 abstract 2
- 238000010586 diagram Methods 0.000 description 5
- 230000008878 coupling Effects 0.000 description 4
- 238000010168 coupling process Methods 0.000 description 4
- 238000005859 coupling reaction Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 238000010276 construction Methods 0.000 description 2
- 238000010304 firing Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000000712 assembly Effects 0.000 description 1
- 238000000429 assembly Methods 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 210000003850 cellular structure Anatomy 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 230000004927 fusion Effects 0.000 description 1
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Abstract
The utility model relates to a connecting structure of a gas compressor and a turbine. The connecting structure of the gas compressor and the turbine comprises a gas compressor rear shaft neck, a labyrinth sealing disc and a turbine drum cylinder shaft front end which form a whole. According to the utility model, the gas compressor rear shaft neck, the labyrinth sealing disc and the turbine drum cylinder shaft front end act as a whole, structures of installation edges, bolts and the like of a traditional device are cancelled, and the problems of the traditional structure that multiple local parts are needed, are complex to assemble, are high in weight and weak in integral rigidity and the like are solved.
Description
Technical field
The utility model relates to field of fluid machinery, relates in particular to the linkage structure of a kind of gas compressor and turbine.
Background technique
Gas turbine engine consists of gas compressor, firing chamber, turbine and the spare part that connects them.As shown in Figure 1, in traditional gas turbine engine, compressor rotor and turbine rotor have formed engine rotor jointly.Wherein the air after gas compressor compression can be through preposition Diffuser flowing in combustion chamber, and firing chamber effluent air drives turbine rotor, and compressor rotor is driven by turbine rotor.In compressor rotor rear end, generally all there is a castor tooth seal pan, mainly play the effect that regulates the motor axial force producing due to gas flow.Enlarged view in conjunction with Fig. 2 can be seen, between gas compressor and turbine rotor, by rigid coupling, be connected, this coupling links together axle journal a2, castor tooth seal pan a4 after gas compressor and turbine drum barrel axle a3 by bolt a1, to realize being connected of gas compressor and turbine rotor.This structural design relative complex, local number of parts increases, and assembling difficulty is large.And, because this component internal is bolted, increased local mounting edge and number of bolts, and then increased the weight of motor.
Model utility content
The purpose of this utility model is the linkage structure that proposes a kind of gas compressor and turbine, can reduce number of spare parts, reduces assembling difficulty.
For achieving the above object, the utility model provides the linkage structure of a kind of gas compressor and turbine, comprise axle journal after gas compressor, castor tooth seal pan and turbine drum barrel axle front end, and after described gas compressor, axle journal, castor tooth seal pan and turbine drum barrel axle front end form an entirety.
Further, after described gas compressor, axle journal and turbine drum barrel axle front end are all set to be default angle of inclination between the axis of described turbine, and described default angle of inclination is consistent with the trend of the comb tooth of described castor tooth seal pan.
Further, turbine drum barrel axle is divided into two-part along the axial direction of described turbine, and connects by bolt.
Further, two-part of turbine drum barrel axle are connected with bolt by circular arc end tooth.
Further, axle journal, castor tooth seal pan and the integrated manufacture of turbine drum barrel axle front end after described gas compressor.
Further, after described gas compressor, axle journal, castor tooth seal pan and turbine drum barrel axle front end are combined into an entirety by welding manner.
Based on technique scheme, the utility model is done as a whole by axle journal, castor tooth seal pan and turbine drum barrel axle front end after gas compressor, the structures such as the mounting edge of prior device and bolt have been cancelled, solved the local part that conventional construction brings on the high side, the problems such as assembling is complicated, and the higher and integral rigidity of weight is weak.
Accompanying drawing explanation
Accompanying drawing described herein is used to provide further understanding of the present utility model, forms the application's a part, and schematic description and description of the present utility model is used for explaining the utility model, does not form improper restriction of the present utility model.In the accompanying drawings:
Fig. 1 is the part-structure schematic diagram that traditional gas turbine engine comprises compressor rotor, turbine rotor and part assemblies.
Fig. 2 is the enlarged diagram of the linkage structure between gas compressor and turbine rotor in Fig. 1.
Fig. 3 is an embodiment's of the linkage structure of the utility model gas compressor and turbine structural representation.
Fig. 4 is the part-structure schematic diagram of the linkage structure embodiment's of application the utility model gas compressor and turbine gas turbine engine.
Embodiment
Below by drawings and Examples, the technical solution of the utility model is described in further detail.
In traditional gas turbine engine, between gas compressor and turbine rotor, by rigid coupling, be connected, for construction bolt, need to be in compressor rotor rear end, be that after gas compressor, axle journal setting has certain thickness mounting edge, at turbine drum barrel axle, near one end of gas compressor, certain thickness mounting edge is also set, thereby facilitate the fixing of bolt and install, this has brought parts to increase thereupon, need to install the problems such as location.
Consider conventional gas turbine motor why exist these problems be mainly because rigid coupling adopt bolt install, and if save bolt install, can overcome above problem thereupon.Based on this thinking, the utility model has adopted axle journal, castor tooth seal pan and the integrated structural type of turbine drum barrel axle front end after gas compressor.As shown in Figure 3, in the present embodiment, the linkage structure of gas compressor and turbine comprises axle journal 2 after gas compressor, castor tooth seal pan 4 and turbine drum barrel axle front end 3, and wherein, after gas compressor, axle journal 2, castor tooth seal pan 4 and turbine drum barrel axle front end 3 form an entirety.The formation of this entirety can be integrated manufacture, or is combined into an entirety by welding manner.
The linkage structure of comparison diagram 2, the linkage structure in Fig. 3 embodiment has been saved mounting edge and the bolt of both sides, has reduced parts, has therefore saved manufacture cost, has also alleviated the weight of motor, improves the efficiency of motor.From integral rigidity, this integrated linkage structure is better than the integral rigidity of bolt fastening structure, and this just makes motor promote to some extent reliability.In addition, because Fig. 3 embodiment does not relate to aligning of mounting edge upper bolt hole, therefore save the location and installation problem of axle journal, castor tooth seal pan and turbine drum barrel axle front end after gas compressor, thereby shortened installation time, improved efficiency of assembling.
From dynamic performance, the linkage structure of Fig. 2 in the axial direction distance is longer, can increase fulcrum span, be unfavorable for the dynamic performance of engine rotor, and Fig. 3 embodiment is in the axial direction apart from shorter, this makes motor fulcrum layout compacter, the critical speed of rotation of engine rotor can increase because of reducing of rotor span simultaneously, away from the working speed of motor, and then reduces the vibration producing, avoid the impact of resonance, be conducive to improve the dynamic performance of engine rotor.
In order to make axle journal after integrated gas compressor, castor tooth seal pan and turbine drum barrel axle front end have better been given play to the advantage of fusion, preferably (stepped according to the trend of castor tooth, have angle to tilt) axle journal after gas compressor and turbine shaft front end are made to inclination, and angle is consistent with castor tooth trend, be about to axle journal 2 after gas compressor and turbine shaft drum barrel axle front end 3 is all set to and the axis of turbine between be default angle of inclination, this default angle of inclination is consistent with the trend of comb tooth 1, this conforming inclination can reduce the problem of stress concentration of this linkage structure, more contribute to the transmission of moment of torsion.Meanwhile, the cellular structure that comb tooth can be corresponding with it matches, and plays certain effect of obturaging and controls the mobile effect of cooled gas.
As shown in Figure 4, be the part-structure schematic diagram of the linkage structure embodiment's of application the utility model gas compressor and turbine gas turbine engine.In Fig. 4, turbine drum barrel axle can be divided into two-part along the axial direction of turbine, is respectively turbine drum barrel axle front end 3 and turbine drum barrel shaft rear end 5, and the two connects by bolt 6.Where necessary, two-part of turbine drum barrel axle can also be connected with bolt by circular arc end tooth, to increase the centering effect of linkage structure under hot state (being the working state of motor).
Finally should be noted that: above embodiment is only in order to illustrate that the technical solution of the utility model is not intended to limit; Although the utility model is had been described in detail with reference to preferred embodiment, those of ordinary skill in the field are to be understood that: still can modify or part technical characteristics is equal to replacement embodiment of the present utility model; And not departing from the spirit of technical solutions of the utility model, it all should be encompassed in the middle of the technological scheme scope of the utility model request protection.
Claims (6)
1. a linkage structure for gas compressor and turbine, is characterized in that, comprises axle journal after gas compressor, castor tooth seal pan and turbine drum barrel axle front end, and after described gas compressor, axle journal, castor tooth seal pan and turbine drum barrel axle front end form an entirety.
2. the linkage structure of gas compressor according to claim 1 and turbine, it is characterized in that, after described gas compressor, axle journal and turbine drum barrel axle front end are all set to be default angle of inclination between the axis of described turbine, and described default angle of inclination is consistent with the trend of the comb tooth of described castor tooth seal pan.
3. the linkage structure of gas compressor according to claim 2 and turbine, is characterized in that, turbine drum barrel axle is divided into two-part along the axial direction of described turbine, and connects by bolt.
4. the linkage structure of gas compressor according to claim 2 and turbine, is characterized in that, two-part of turbine drum barrel axle are connected with bolt by circular arc end tooth.
5. the linkage structure of gas compressor according to claim 1 and turbine, is characterized in that, axle journal, castor tooth seal pan and the integrated manufacture of turbine drum barrel axle front end after described gas compressor.
6. the linkage structure of gas compressor according to claim 1 and turbine, is characterized in that, after described gas compressor, axle journal, castor tooth seal pan and turbine drum barrel axle front end are combined into an entirety by welding manner.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320813369.5U CN203584577U (en) | 2013-12-11 | 2013-12-11 | Connecting structure of gas compressor and turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201320813369.5U CN203584577U (en) | 2013-12-11 | 2013-12-11 | Connecting structure of gas compressor and turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203584577U true CN203584577U (en) | 2014-05-07 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201320813369.5U Expired - Lifetime CN203584577U (en) | 2013-12-11 | 2013-12-11 | Connecting structure of gas compressor and turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203584577U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105402157A (en) * | 2015-12-25 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Integral type disk shaft structure |
| CN105971920A (en) * | 2016-06-22 | 2016-09-28 | 中国航空工业集团公司沈阳发动机设计研究所 | Compressor test device |
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN113898414A (en) * | 2021-12-09 | 2022-01-07 | 成都中科翼能科技有限公司 | Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine |
-
2013
- 2013-12-11 CN CN201320813369.5U patent/CN203584577U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105402157A (en) * | 2015-12-25 | 2016-03-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Integral type disk shaft structure |
| CN105402157B (en) * | 2015-12-25 | 2018-06-05 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of monoblock type dish axle structure |
| CN105971920A (en) * | 2016-06-22 | 2016-09-28 | 中国航空工业集团公司沈阳发动机设计研究所 | Compressor test device |
| CN105971920B (en) * | 2016-06-22 | 2018-01-30 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of Compressor test device |
| CN111577652A (en) * | 2020-05-11 | 2020-08-25 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN111577652B (en) * | 2020-05-11 | 2021-09-03 | 中国航发沈阳发动机研究所 | Drum barrel structure and compressor rotor disc connecting structure thereof |
| CN113898414A (en) * | 2021-12-09 | 2022-01-07 | 成都中科翼能科技有限公司 | Reinforcing structure for preventing thermal vibration deformation of high-pressure rotor of gas turbine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: AECC COMMERCIAL AIRCRAFT ENGINE Co.,Ltd. Address before: 201108 Shanghai city Minhang District Lotus Road No. 3998 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20140507 |
|
| CX01 | Expiry of patent term |