CN1291142C - Air-bleed transmission equipment of combustion turbine - Google Patents
Air-bleed transmission equipment of combustion turbine Download PDFInfo
- Publication number
- CN1291142C CN1291142C CN 200410021109 CN200410021109A CN1291142C CN 1291142 C CN1291142 C CN 1291142C CN 200410021109 CN200410021109 CN 200410021109 CN 200410021109 A CN200410021109 A CN 200410021109A CN 1291142 C CN1291142 C CN 1291142C
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- CN
- China
- Prior art keywords
- sleeve
- ring
- disks
- air entraining
- cooling
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- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to an air bleed transmission device of a gas turbine, which can be used for cooling flat penetration disks and blades in the inner rotor cavity of the gas turbine. The present invention comprises rotor drums, the flat penetration disks and the Y-shaped installation side of a compressor rotor, wherein a left upper sleeve and a left lower sleeve are arranged between the flat penetration disks in some stage; the left upper sleeve is connected with the left lower sleeve through an annular component; a right upper sleeve and a right lower sleeve are arranged between the flat penetration disks in some stage in the other group; rings are arranged between the sleeves and are provided with a plurality of radial type air bleed pipes; the corresponding drums are provided with air bleed ports; one end of the right upper sleeve and the right lower sleeve is provided with a sealing ring used for enclosing. Thus, a plurality of delamination shunting cavities are formed. Therefore, the present invention realizes the purpose of cooling the flat penetration disks and the blades in a delamination shunting mode.
Description
Technical field
The present invention relates to a kind of gas turbine cold air transmitting set.Particularly carry out the device that multi-cavity, layering cool off turbine dish and blade about rotor internal cavity.
Background technique
Fuel gas temperature can reach more than 1200～1300 ℃ before the gas turbine turbine at present, and the turbine part temperatures that is exposed in the hot combustion gas is very high, can't proper functioning to its cooling.Turbine parts cooling medium normally extracts and sends into the turbine parts from gas compressor.
General combustion machine adopts single stream that the turbine parts are carried out the order cooling.The order cooling scheme is from the wheel disc and the blade of the air elder generation cooling turbine first order high temperature of gas compressor one-level extraction certain pressure and temperature, and the remaining cooling air pressure in cooling back descends, and the temperature raising enters second level turbine wheel disc and blade, and order is carried out like this.The wheel disc of turbine later stages and blade make cooling effect descend greatly because cooling air temperature increases substantially, real is not ideal.
Summary of the invention
At above-mentioned deficiency, the objective of the invention is to provide a kind of and penetrate the rotor internal cavity cold air transmitting set that formula air entraining pipe and layering sleeve are formed by the width of cloth, purport solves the problem that multichannel bleed layering is carried, overcoming general combustion machine cooling air cools off in proper order, influence the shortcoming of cooling effect, wherein radial air entraining pipe can reduce the temperature rising that produces in the rotation effect of coiling chamber internal cause wheel disc because of air-flow, the layering sleeve also plays the effect of heat screen except that steering flow, reduce the temperature rise of cooling air in transmission course, further improve turbine dish and blade cooling effect, guarantee turbine dish and blade proper functioning.
The technological scheme that the present invention is taked for its concrete technical problem of solution is: including rotor drum, dish and compressor rotor fork-shaped are installed the limit at interior combustion machine rotor inner chamber cold air transmitting set, be between preceding some grades of dishes, to be provided with upper left sleeve, the lower-left sleeve, between the some grades of dishes in back, be provided with upper right sleeve with the lower-left sleeve is consecutive, its below is provided with the sleeve group that is linked to each other with sleeve behind the bottom right by the bottom right front sleeve, upper left, be provided with left side ring between the lower sleeve left end, left side ring is provided with some radial air entraining pipes, the right-hand member bottom of lower-left sleeve is provided with middle ring, this ring is provided with some upper left sleeves that pass, the radial air entraining pipe of lower-left sleeve, this ring has left seal ring, right seal ring, right seal ring links to each other with the bottom right front sleeve, the drum barrel of corresponding radial air entraining pipe has several bleed holes, constitutes layering thus, the multi-cavity air flue.
The invention has the beneficial effects as follows to have overcome the ill effect that prior art is cooled off step by step, realize layering shunting cooling purpose, guaranteed turbine dish and blade proper functioning.
Description of drawings
The invention will be further described below in conjunction with accompanying drawing.
Fig. 1 is a gas turbine air entraining transmission device structural representation of the present invention.
Among the figure: 1 drum barrel, 2 radial air entraining pipes, 3 prime dishes, 4 ring parts, 5 left side rings, 6 upper left sleeves, 7 lower-left sleeves, 8 preceding middle rank dishes, 9 bolts, 10 left seal rings, 11 bolts, 12 bottom right front sleeves, sleeve behind 13 bottom rights, 14 upper right sleeves, 15 back level dishes, ring in 16,17 right seal rings, 18 drum barrels, 19 radial air entraining pipes, 20 back middle rank dishes.
Embodiment
By accompanying drawing 1 as can be known, the present invention includes the rotor drum dish and the compressor rotor fork-shaped is installed the limit at interior combustion machine rotor inner chamber cold air transmitting set, at prime dish 3, be provided with the upper left sleeve 6 that connects by ring part 4 between the back middle rank dish 20, lower-left sleeve 7, at back middle rank dish 20, be provided with upper right sleeve 14 with lower-left sleeve 7 is consecutive between the back level dish 15, its below is provided with the sleeve group that is linked to each other with sleeve 13 behind the bottom right by bottom right front sleeve 12, upper left, lower sleeve 6, be provided with left side ring 5 between 7 the left end, left side ring 5 is provided with some radial air entraining pipes, ring 16 during sleeve right-hand member bottom, lower-left is provided with, this ring is provided with some upper left sleeves 6 that pass, the radial air entraining pipe 19 of lower-left sleeve 7, this ring have left seal ring 10, right seal ring 17, right seal ring 17 links to each other with bottom right front sleeve 12, corresponding radial air entraining pipe 2,19 at drum barrel 1, have several bleed holes on 18, thereby constituted a plurality of layered separating cavities, realized the purpose of layering shunting cooling turbine dish and blade.
Claims (1)
1, a kind of rotor drum that includes, dish and compressor rotor fork-shaped are installed the limit at interior gas turbine air entraining transmission device, it is characterized in that between preceding some grades of dishes, being provided with upper left sleeve, the lower-left sleeve, between the some grades of dishes in back, be provided with upper right sleeve with the lower-left sleeve is consecutive, its below is provided with the sleeve group that is linked to each other with sleeve behind the bottom right by the bottom right front sleeve, upper left, be provided with left side ring between the lower sleeve left end, left side ring is provided with some radial air entraining pipes, sleeve right-hand member bottom, lower-left is provided with middle ring, this ring is provided with some upper left sleeves that pass, the radial air entraining pipe of lower-left sleeve, this ring has left seal ring, right seal ring, right seal ring links to each other with the bottom right front sleeve, the drum barrel of corresponding radial air entraining pipe has several bleed holes, constitutes layering thus, the multi-cavity air flue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200410021109 CN1291142C (en) | 2004-02-04 | 2004-02-04 | Air-bleed transmission equipment of combustion turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 200410021109 CN1291142C (en) | 2004-02-04 | 2004-02-04 | Air-bleed transmission equipment of combustion turbine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1558099A CN1558099A (en) | 2004-12-29 |
| CN1291142C true CN1291142C (en) | 2006-12-20 |
Family
ID=34351924
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 200410021109 Expired - Fee Related CN1291142C (en) | 2004-02-04 | 2004-02-04 | Air-bleed transmission equipment of combustion turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1291142C (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20070151257A1 (en) * | 2006-01-05 | 2007-07-05 | Maier Mark S | Method and apparatus for enabling engine turn down |
| CN102661201B (en) * | 2012-04-28 | 2014-02-12 | 中国航空动力机械研究所 | Air entraining structure of engine |
| EP2865850B1 (en) * | 2013-10-24 | 2018-01-03 | Ansaldo Energia Switzerland AG | Impingement cooling arrangement |
| CN105156214A (en) * | 2015-07-09 | 2015-12-16 | 中国航空工业集团公司沈阳发动机设计研究所 | Disc cavity gas collecting device for heavy-duty gas turbine |
| US10196928B2 (en) | 2016-03-02 | 2019-02-05 | General Electric Company | Method and system for piping failure detection in a gas turbine bleeding air system |
| CN110566515B (en) * | 2019-09-22 | 2020-12-18 | 中国航发沈阳发动机研究所 | Gas-entraining structure on inner side of gas compressor |
| CN111946464B (en) * | 2020-07-21 | 2021-09-07 | 中国科学院工程热物理研究所 | Flow guide blocking sealing structure for rear bearing cavity of high-pressure turbine disc |
| GB2603792A (en) * | 2021-02-15 | 2022-08-17 | Rolls Royce Plc | Air guide tube connection |
-
2004
- 2004-02-04 CN CN 200410021109 patent/CN1291142C/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| CN1558099A (en) | 2004-12-29 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20061220 Termination date: 20160204 |