CN201697162U - Carbon deposit prevention liquid fuel nozzle for gas turbine - Google Patents
Carbon deposit prevention liquid fuel nozzle for gas turbine Download PDFInfo
- Publication number
- CN201697162U CN201697162U CN2010201791214U CN201020179121U CN201697162U CN 201697162 U CN201697162 U CN 201697162U CN 2010201791214 U CN2010201791214 U CN 2010201791214U CN 201020179121 U CN201020179121 U CN 201020179121U CN 201697162 U CN201697162 U CN 201697162U
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- nozzle
- liquid fuel
- gas turbine
- carbon deposit
- jet pipe
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Abstract
A carbon deposit prevention liquid fuel nozzle for a gas turbine is characterized by comprising a nozzle body, an air cap, a central cyclone, a heat insulation ring, an injection pipe, a fuel nozzle, a liquid fuel inlet and a central air inlet, wherein the nozzle body is hollow inside, the hollow injection pipe is installed in the nozzle body, the hollow heat insulation ring is installed in the injection pipe, the central cyclone is installed in the heat insulation ring, the fuel nozzle is positioned at the front end of the injection pipe, the air cap covers the front end of the nozzle body, the axis of the liquid fuel inlet is vertical to that of the injection pipe, and the central air inlet is positioned at the rear end of the injection pipe. The utility model has the advantages that: the utility model adopts the corresponding technical measures to protect the nozzle in a cooling way, can effectively prevent the end surface of the nozzle from forming carbon deposit, cannot influence the fuel injection property due to a large quantity of carbon deposit formed after long-time work, greatly improves the service lives of a gas turbine combustion chamber and turbine components, and effectively reduces the use and maintenance costs of the gas turbine.
Description
Technical field
The utility model relates to the gas-turbine combustion chamber structure of using gases fuel work, particularly a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine.
Background technology
Nozzle is the important process parts of gas-turbine combustion chamber, and fuel is to infeed gas-turbine combustion chamber by nozzle in the course of work, and realizes and burning room air mixing and burning.Because nozzle is directly in the face of the elevated temperature heat combustion gas in the gas turbine course of work, if it is improper to design, after working long hours, can form carbon deposit at nozzle face, and then influence spray characteristics such as the spray angle of gaseous fuel and the uniformity, cause combustor exit temperature field quality to worsen, even cause the high temperature ablation of burner inner liner and turbo blade.And, after carbon trumpet comes off, also may cause the abrasion of turbo blade.Must change nozzle when therefore, carbon deposit is relatively more serious.And if gas turbine frequent refuelling nozzle in running will certainly influence the availability of gas turbine, and increase the use and the maintenance cost of gas turbine.
Traditional gaseous fuel gas-turbine combustion chamber, air is through mixing and burn at head of combustion chamber with the fuel of oblique ejection behind the air cyclone eddy flow.Because there is stronger recirculating zone in head of combustion chamber, and nozzle does not adopt corresponding cooling provision, therefore the nozzle surface temperature is very high in the gas turbine course of work, after working long hours, formed a large amount of carbon deposits at nozzle face, combustor exit temperature field or even gas turbine hardware have been constituted serious threat.
The utility model content
The purpose of this utility model is to form a large amount of carbon deposits at the fuel nozzle end face after gas-turbine combustion chamber works long hours, and the spy provides a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine.
The utility model provides a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine, it is characterized in that: the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine comprises nozzle body 1, air calotte 2, center cyclone 3, heat insulation loop 4, jet pipe 5, fuel nozzle ports 6, liquid fuel inlet 7, center air intlet 8;
Wherein: nozzle body 1 inner hollow, the inside is equipped with the jet pipe 5 of hollow, the heat insulation loop 4 of hollow is installed in the inside of jet pipe 5, center cyclone 3 is installed in the inside of heat insulation loop 4, fuel nozzle ports 6 is positioned at the front end of jet pipe 5, air calotte 2 covers on the front end of nozzle body 1, the axis normal of the axis of liquid fuel inlet 7 and jet pipe 5, and center air intlet 8 is positioned at the rear end of jet pipe 5.
Described center cyclone 3 is vane type or oblique hole type structure, and the number of blade or hole count scope are 3～10.
Described center cyclone 3 is prismatic blade or twisted blade, and the eddy flow direction is identical or opposite to the air cyclone direction with the nozzle external shaft, and deflection angle is 0 °～80 °.
The center air produces rotation through center air cyclone 3 back, after flowing out from nozzle face, presses close to nozzle face and outwards expands, and near the high-temperature fuel gas can the purge nozzle end face is realized the cooling to nozzle face, effectively suppresses carbon deposit and forms.Simultaneously, the center rotational flow air can play the effect of assisted atomization in spout place and liquid fuel generation shear action;
The outside air calotte 2 that increases of nozzle can form the cooling protection air film at the nozzle face place, prevent that carbon deposit from forming.
Advantage of the present utility model:
Anti-carbon deposit liquid fuel nozzle described in the utility model can be applied on the gas-turbine combustion chamber of combusting liquid fuel.Owing to adopt corresponding technical measures nozzle is carried out cooling protection; can effectively prevent to form carbon deposit at nozzle face; can not form a large amount of carbon distributions and influence fuel injection characteristic because of working long hours; can improve the service life of gas-turbine combustion chamber and turbine part greatly; effectively reduce the operation and maintenance cost of gas turbine, have better market prospect.
Description of drawings
Below in conjunction with drawings and the embodiments the utility model is described in further detail:
Fig. 1 is the anti-carbon deposit liquid fuel nozzle that is used for gas turbine.
The specific embodiment
Present embodiment provides a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine, it is characterized in that: the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine comprises nozzle body 1, air calotte 2, center cyclone 3, heat insulation loop 4, jet pipe 5, fuel nozzle ports 6, liquid fuel inlet 7, center air intlet 8;
Wherein: nozzle body 1 inner hollow, the inside is equipped with the jet pipe 5 of hollow, the heat insulation loop 4 of hollow is installed in the inside of jet pipe 5, center cyclone 3 is installed in the inside of heat insulation loop 4, fuel nozzle ports 6 is positioned at the front end of jet pipe 5, air calotte 2 covers on the front end of nozzle body 1, the axis normal of the axis of liquid fuel inlet 7 and jet pipe 5, and center air intlet 8 is positioned at the rear end of jet pipe 5.
Described center cyclone 3 is a leaf structure, and the number of blade is 5.
Described center cyclone 3 is a prismatic blade, and the eddy flow direction is identical to the air cyclone direction with the nozzle external shaft, and deflection angle is 57 °.
Carbon trumpet is to cause owing to nozzle face is overheated, prevents that therefore the effective way of carbon trumpet from being to adopt adequate measures that nozzle is cooled off clearly to blow.
The center air produces rotation through center air cyclone 3 back, after flowing out from nozzle face, presses close to nozzle face and outwards expands, and near the high-temperature fuel gas can the purge nozzle end face is realized the cooling to nozzle face, effectively suppresses carbon deposit and forms;
The outside air calotte 2 that increases of nozzle, tighten up at the place at corresponding fuel orifice, can form the cooling protection air film at the nozzle face place, prevents that carbon deposit from forming.
Present embodiment provides a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine, it is characterized in that: the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine comprises nozzle body 1, air calotte 2, center cyclone 3, heat insulation loop 4, jet pipe 5, fuel nozzle ports 6, liquid fuel inlet 7, center air intlet 8;
Wherein: nozzle body 1 inner hollow, the inside is equipped with the jet pipe 5 of hollow, the heat insulation loop 4 of hollow is installed in the inside of jet pipe 5, center cyclone 3 is installed in the inside of heat insulation loop 4, fuel nozzle ports 6 is positioned at the front end of jet pipe 5, air calotte 2 covers on the front end of nozzle body 1, and the angle of the folded acute angle of axis of the axis of liquid fuel inlet 7 and jet pipe 5 is 15 °, and center air intlet 8 is positioned at the rear end of jet pipe 5.
Described center cyclone 3 is a leaf structure, and the number of blade is 6.
Described center cyclone 3 is a twisted blade, and the eddy flow direction is opposite to the air cyclone direction with the nozzle external shaft, and deflection angle is 80 °.
Carbon trumpet is to cause owing to nozzle face is overheated, prevents that therefore the effective way of carbon trumpet from being to adopt adequate measures that nozzle is cooled off clearly to blow.
The center air produces rotation through center air cyclone 3 back, after flowing out from nozzle face, presses close to nozzle face and outwards expands, and near the high-temperature fuel gas can the purge nozzle end face is realized the cooling to nozzle face, effectively suppresses carbon deposit and forms;
The outside air calotte 2 that increases of nozzle, tighten up at the place at corresponding fuel orifice, can form the cooling protection air film at the nozzle face place, prevents that carbon deposit from forming.
Present embodiment provides a kind of anti-carbon deposit liquid fuel nozzle that is used for gas turbine, it is characterized in that: the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine comprises nozzle body 1, air calotte 2, center cyclone 3, heat insulation loop 4, jet pipe 5, fuel nozzle ports 6, liquid fuel inlet 7, center air intlet 8;
Wherein: nozzle body 1 inner hollow, the inside is equipped with the jet pipe 5 of hollow, the heat insulation loop 4 of hollow is installed in the inside of jet pipe 5, center cyclone 3 is installed in the inside of heat insulation loop 4, fuel nozzle ports 6 is positioned at the front end of jet pipe 5, air calotte 2 covers on the front end of nozzle body 1, and the angle of the folded acute angle of axis of the axis of liquid fuel inlet 7 and jet pipe 5 is 45 °, and center air intlet 8 is positioned at the rear end of jet pipe 5.
Described center cyclone 3 is the oblique hole type structure, and hole count is 10.
Carbon trumpet is to cause owing to nozzle face is overheated, prevents that therefore the effective way of carbon trumpet from being to adopt adequate measures that nozzle is cooled off clearly to blow.
The center air produces rotation through center air cyclone 3 back, after flowing out from nozzle face, presses close to nozzle face and outwards expands, and near the high-temperature fuel gas can the purge nozzle end face is realized the cooling to nozzle face, effectively suppresses carbon deposit and forms;
The outside air calotte 2 that increases of nozzle, tighten up at the place at corresponding fuel orifice, can form the cooling protection air film at the nozzle face place, prevents that carbon deposit from forming.
Claims (3)
1. anti-carbon deposit liquid fuel nozzle that is used for gas turbine, it is characterized in that: the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine comprises nozzle body (1), air calotte (2), center cyclone (3), heat insulation loop (4), jet pipe (5), fuel nozzle ports (6), liquid fuel inlet (7), center air intlet (8);
Wherein: nozzle body (1) inner hollow, the inside is equipped with the jet pipe (5) of hollow, the heat insulation loop of hollow (4) is installed in the inside of jet pipe (5), center cyclone (3) is installed in the inside of heat insulation loop (4), fuel nozzle ports (6) is positioned at the front end of jet pipe (5), air calotte (2) covers on the front end of nozzle body (1), the axis normal of the axis of liquid fuel inlet (7) and jet pipe (5), and center air intlet (8) is positioned at the rear end of jet pipe (5).
2. according to the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine of claim 1, it is characterized in that: described center cyclone (3) is vane type or oblique hole type structure, and the number of blade or hole count scope are 3～10.
3. according to the described anti-carbon deposit liquid fuel nozzle that is used for gas turbine of claim 2, it is characterized in that: described center cyclone (3) is prismatic blade or twisted blade, the eddy flow direction is identical or opposite to the air cyclone direction with the nozzle external shaft, and deflection angle is 0 °～80 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201791214U CN201697162U (en) | 2010-05-05 | 2010-05-05 | Carbon deposit prevention liquid fuel nozzle for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010201791214U CN201697162U (en) | 2010-05-05 | 2010-05-05 | Carbon deposit prevention liquid fuel nozzle for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201697162U true CN201697162U (en) | 2011-01-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010201791214U Expired - Fee Related CN201697162U (en) | 2010-05-05 | 2010-05-05 | Carbon deposit prevention liquid fuel nozzle for gas turbine |
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| CN (1) | CN201697162U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102563705A (en) * | 2012-02-15 | 2012-07-11 | 中国人民解放军国防科学技术大学 | Direct-flow fuel nozzle capable of preventing carbon deposit |
| CN109140501A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | The nozzle arrangements of the centrifugal band bilayer gas hood of the double spouts of double oil circuits |
| CN109140499A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | A kind of swirler for aeroengine combustor buring chamber-head portion |
| CN110617499A (en) * | 2019-09-19 | 2019-12-27 | 西安成立航空制造有限公司 | Protection method for carbon deposition of fuel nozzle |
| CN111520711A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Structure for improving carbon deposition of centrifugal nozzle |
-
2010
- 2010-05-05 CN CN2010201791214U patent/CN201697162U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102563705A (en) * | 2012-02-15 | 2012-07-11 | 中国人民解放军国防科学技术大学 | Direct-flow fuel nozzle capable of preventing carbon deposit |
| CN109140501A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | The nozzle arrangements of the centrifugal band bilayer gas hood of the double spouts of double oil circuits |
| CN109140499A (en) * | 2017-06-28 | 2019-01-04 | 中国航发贵阳发动机设计研究所 | A kind of swirler for aeroengine combustor buring chamber-head portion |
| CN110617499A (en) * | 2019-09-19 | 2019-12-27 | 西安成立航空制造有限公司 | Protection method for carbon deposition of fuel nozzle |
| CN111520711A (en) * | 2020-03-17 | 2020-08-11 | 西北工业大学 | Structure for improving carbon deposition of centrifugal nozzle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110105 Termination date: 20180505 |
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| CF01 | Termination of patent right due to non-payment of annual fee |