CN2674106Y - Mixing type turbine rotator - Google Patents
Mixing type turbine rotator Download PDFInfo
- Publication number
- CN2674106Y CN2674106Y CN 200420030263 CN200420030263U CN2674106Y CN 2674106 Y CN2674106 Y CN 2674106Y CN 200420030263 CN200420030263 CN 200420030263 CN 200420030263 U CN200420030263 U CN 200420030263U CN 2674106 Y CN2674106 Y CN 2674106Y
- Authority
- CN
- China
- Prior art keywords
- turbine
- dish
- drum barrel
- limit
- panels
- 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.)
- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model relates to a mixing type turbine rotator which is arranged in a gas turbine. On the basis of turbine rotators with turbine panels and shafts, at least a plurality of the front ends of the turbine panels are provided with drum barrels with segmented type grate toothed rings, and the back ends of the turbine panels are provided with Y-type mounting edges for connecting among the turbine panels. The front of a first stage turbine panel is provided with a hanging panel which is connected with a hanging panel of a compressor rotor, and a back-front stage turbine panel is provided with a tapered drum barrel. A column-shaped drum barrel is arranged between two back stage turbine panels, and the back end face of a final stage turbine panel is provided with a sealing panel. The segmented type grate toothed rings sealed with stator honeycomb sealing rings are arranged on the turbine panels and each drum barrel central pipes of panel shafts are arranged at the centers of the turbine panels and the shafts. The mixing type turbine rotator which combines the turbine panels, the drum barrels , and the shafts together has the advantages of high hardness, good strength, good seal, simple structure, safety, reliability, long service life, convenient repair, and low cost.
Description
Technical field
The utility model relates to a kind of turbine rotor, particularly about obturaging and the fixed center piping has seal pan and hangs the turbine rotor of dish by dish, drum and the mixed rotor formed of axle journal and in order to solve.
Background technique
At present, turbine rotor in the gas turbine is many by the turbine dish that links to each other with axle, the drum barrel that links to each other with the turbine dish constitutes, the turbine rotor of working under high load connects the Bolt Connection that adopt because of the split of its turbine dish, drum barrel, axle more, cause turbine rotor flexural rigidity mechanical strength to descend, influence working life, increase amount of maintenance, cost of production is improved.
The model utility content
At above-mentioned deficiency, the purpose of this utility model is will provide a kind of to work under high load, has that big reliability, life-span are long, simple in structure, easy to maintenance, rigidity and a big a kind of combined turbine rotor of intensity.
The utility model is that the technological scheme that its technical problem of solution is taked is that turbine dish front-end faces at different levels are provided with drum barrel, ear end face is provided with fork-shaped the limit is installed, the drum barrel of turbine dish is installed the limit with the fork-shaped of previous stage turbine dish and is linked to each other, wherein the 1st grade of turbine dish front end drum barrel with hang dish and link to each other, this dish front end fork-shaped installation limit is hung dish with compressor rotor and is linked to each other, cylindrical drum barrel and its fork-shaped set between back two stage turbine dish are installed the limit grafting, end face is provided with conical drum barrel after the back top turbine dish, be provided with among the final stage turbine dish, lower protruding edge, upper flange is connected with conical drum barrel coupling on the top turbine dish of back, lower protruding edge is connected with axle journal, final stage turbine back-end disk face is provided with flange and is mated the seal pan that is connected, the seal pan mesopore is installed the limit and is linked to each other with axle journal, the limit is installed before the seal pan is provided with the tapped hole that is used to adjust balance stable equilibrium piece, seal pan wheel rim place studs with the segmented comb ring gear of obturaging, each drum barrel outer shroud is provided with and the stator honeycomb ring segmented comb ring gear that is complementary and is used to obturage of obturaging, center at turbine dish and axle is provided with central tube of disk shaft, and fix with hanging the dish and the interior installation limit of one-level turbine dish, constituted dish thus, drum barrel, the axle journal group is the mixed rotor of one.
The beneficial effects of the utility model are: good rigidity, intensity are big, and seal performance is strong, good cooling results, reduces energy loss, improves efficiency of turbine, and functional reliability strengthens under high load, and the life-span prolongs relatively, and simple in structure, and is easy to maintenance, and cost is low.
Description of drawings
The utility model is described in further detail below in conjunction with accompanying drawing.
Fig. 1 is the utility model rotor structure schematic representation.
Among the figure: 1 turbine dish, 2 drum barrels, 3 dish drum structures, 4 pins, 5 bolts, 6 axle journals, 7 cylindrical drum barrels, 8 circular cones
The shape drum barrel, 9 bolts, 10 seal pans, 11 screws, the 12 comb ring gears of obturaging, 13 hang dish, 14 bolts,
15 central tube of disk shaft, 16,17,18 bolts.
Embodiment
The utlity model has some grades of turbine dishes (1) as seen from the figure, at least some turbine dish front-end faces are provided with drum barrel (2) or dish and the drum barrel weldering dish drum structure (3) for one, turbine back-end disk face is provided with fork-shaped the limit is installed, the fork-shaped of the drum barrel of turbine dish and previous stage turbine dish install the limit with several radially pin (4) two level dishes are connected together, wherein the drum barrel of first order turbine dish (1) with hang dish (13) and be welded as a whole, this dish front end fork-shaped installation limit is hung dish with pressure newspaper machine rotor and is linked to each other, adopt frame type drum barrel structure between the back two stage turbine dish (1), be provided with cylindrical drum barrel (7) and the limit grafting be installed with the fork-shaped of this two stage turbine dish (1), it is the conical drum barrel (8) of one that back top turbine dish (1) is provided with its weldering, be provided with among the final stage turbine dish (1), lower protruding edge, conical drum barrel (8) coupling on upper flange and the back top turbine dish, connect with several accurate bolts (9), lower protruding edge is connected with several accurate bolts (5) with axle journal (6), final stage turbine back-end disk face is provided with flange and is mated the seal pan (10) that is connected, the limit is installed after this center hole place to be connected with axle journal (6) with bolt (18), the screw (11) that the limit is provided with the stable equilibrium piece is installed before this dish, the wheel rim place of seal pan (10) studs with the segmented comb ring gear (12) of obturaging, each drum barrel outer shroud is provided with and the quiet honeycomb ring segmented comb ring gear (12) that is complementary and is used to obturage of obturaging, be provided with in the center of turbine dish (1) and axle central tube of disk shaft (15) and with the interior installation limit of hanging dish (13) and one-level turbine dish (1) by bolt (16,17) fixing, constituted dish thus, drum barrel, the axle journal group is the mixed rotor of one.
Claims (3)
1, a kind of combined turbine rotor, it includes turbine dish and axle, it is characterized in that at least some turbine dish front-end faces are provided with drum barrel in some grades of turbine dishes, ear end face is provided with fork-shaped the limit is installed, the limit is provided with the hole, several radially pin will be close to the drum barrel of turbine stage and fork-shaped through this and limit is installed is connected as a single entity, wherein final stage turbine dish is provided with upper and lower flange, upper flange links to each other with conical drum barrel on being located at back top turbine dish, and lower protruding edge links to each other with the fork-shaped installation limit that the axle journal front end is provided with; Final stage turbine back-end disk face is provided with flange and is mated the seal pan that is connected, and the installation limit at this center hole place links to each other with axle journal; Be provided with cylindrical drum barrel between back two stage turbine dish; First order turbine dish front end drum barrel with hang dish weldering and be one, hang dish front end fork-shaped and the limit is installed hangs dish with compressor rotor and link to each other; Turbine dish and the Kong Chu of journal centre are provided with central tube of disk shaft, this pipe with hang the dish link to each other with the interior installation limit of one-level dish.
2, combined turbine rotor according to claim 1 is characterized in that outside the said drum barrel that ring is provided with and the stator honeycomb segmented comb ring gear that is used to obturage that ring is complementary of obturaging.
3, combined turbine rotor according to claim 1 is characterized in that installing before the said seal pan limit and is provided with the hole that is used to adjust balance stable equilibrium piece and wheel rim place and is provided with the segmented comb ring gear of obturaging.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420030263 CN2674106Y (en) | 2004-02-04 | 2004-02-04 | Mixing type turbine rotator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200420030263 CN2674106Y (en) | 2004-02-04 | 2004-02-04 | Mixing type turbine rotator |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2674106Y true CN2674106Y (en) | 2005-01-26 |
Family
ID=34483660
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200420030263 Expired - Fee Related CN2674106Y (en) | 2004-02-04 | 2004-02-04 | Mixing type turbine rotator |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2674106Y (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102959183A (en) * | 2010-07-05 | 2013-03-06 | 西门子公司 | Combined sealing and balancing arrangement for a turbine disc |
| CN101191423B (en) * | 2006-11-28 | 2013-03-13 | 通用电气公司 | Rotary assembly components and methods of fabricating such components |
| CN107063612A (en) * | 2017-04-18 | 2017-08-18 | 东北大学 | A kind of blisk kinematic similarity is test bed |
| CN109356660A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | Twin-stage high-pressure turbine turns stator component |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
-
2004
- 2004-02-04 CN CN 200420030263 patent/CN2674106Y/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101191423B (en) * | 2006-11-28 | 2013-03-13 | 通用电气公司 | Rotary assembly components and methods of fabricating such components |
| CN102959183A (en) * | 2010-07-05 | 2013-03-06 | 西门子公司 | Combined sealing and balancing arrangement for a turbine disc |
| CN102959183B (en) * | 2010-07-05 | 2015-09-23 | 西门子公司 | For combined labyrinth and carbon gland and the Equilibrator of turbine disk |
| US9593581B2 (en) | 2010-07-05 | 2017-03-14 | Siemens Aktiengesellschaft | Combined sealing and balancing arrangement for a turbine disc |
| CN107063612A (en) * | 2017-04-18 | 2017-08-18 | 东北大学 | A kind of blisk kinematic similarity is test bed |
| CN107063612B (en) * | 2017-04-18 | 2019-06-25 | 东北大学 | A kind of integral blade disk kinematic similarity is test bed |
| CN109356660A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | Twin-stage high-pressure turbine turns stator component |
| CN109356660B (en) * | 2018-12-14 | 2021-11-19 | 中国航发沈阳发动机研究所 | Double-stage high-pressure turbine rotor-stator assembly |
| CN113847280A (en) * | 2021-10-10 | 2021-12-28 | 中国航发沈阳发动机研究所 | Compressor rotor interstage bleed air structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20050126 Termination date: 20120204 |