JPS6216738U - - Google Patents
Info
- Publication number
- JPS6216738U JPS6216738U JP10694585U JP10694585U JPS6216738U JP S6216738 U JPS6216738 U JP S6216738U JP 10694585 U JP10694585 U JP 10694585U JP 10694585 U JP10694585 U JP 10694585U JP S6216738 U JPS6216738 U JP S6216738U
- Authority
- JP
- Japan
- Prior art keywords
- atomizing air
- gas turbine
- fuel
- ignition
- acceleration
- 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.)
- Pending
Links
- 239000000446 fuel Substances 0.000 claims description 17
- 230000001133 acceleration Effects 0.000 claims 3
- 238000002485 combustion reaction Methods 0.000 claims 2
- 238000010926 purge Methods 0.000 claims 1
- 238000005507 spraying Methods 0.000 claims 1
- 239000007921 spray Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 4
- 239000002245 particle Substances 0.000 description 2
- 239000000498 cooling water Substances 0.000 description 1
Landscapes
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Description
第１図は、本考案の一実施例を示した燃料噴霧
空気系統図、第２図は、本考案の実施例における
ガスタービン運転モードに対する燃料噴霧液滴の
平均粒径の変化を示した線図、第３図は、圧力噴
霧型燃料ノズルを有する多筒型ガスタービンの燃
料系統図、第４図は、２重オリフイス圧力噴霧型
燃料ノズルの断面図、第５図は、２重オリフイス
圧力噴霧型燃料ノズルの供給圧力に対する流量と
噴射される液滴の平均粒径を示した線図、第６図
は、噴霧更気型燃料ノズルを有する多筒型ガスタ
ービンの燃料及び噴霧空気系統図、第７図は、噴
霧空気型燃料ノズルの断面図である。
１……燃焼器、３……逆止弁、６……燃料ポン
プ、７……補機駆動装置、３０……噴霧空気型燃
料ノズル、３１……噴霧マニホールド、３２……
主空気圧縮機、３３……空気フイルター、３４…
…噴霧空気冷却器、３５……バイパス弁、３６…
…冷却水ポンプ、３７……ラジエタフアン、３８
……ラジエタ、４６……空気フイルタ、４８……
オリフイス。
Fig. 1 is a fuel spray air system diagram showing an embodiment of the present invention, and Fig. 2 is a line showing changes in the average particle size of fuel spray droplets with respect to the gas turbine operation mode in the embodiment of the present invention. Fig. 3 is a fuel system diagram of a multi-tube gas turbine having a pressure spray type fuel nozzle, Fig. 4 is a sectional view of a double orifice pressure spray type fuel nozzle, and Fig. 5 is a double orifice pressure spray type fuel nozzle. A line diagram showing the flow rate and the average particle size of the injected droplets with respect to the supply pressure of the spray type fuel nozzle, and Fig. 6 is a fuel and spray air system diagram of a multi-tube gas turbine having a spray clearer type fuel nozzle. , FIG. 7 is a cross-sectional view of an atomizing air type fuel nozzle. DESCRIPTION OF SYMBOLS 1...Combustor, 3...Check valve, 6...Fuel pump, 7...Auxiliary drive device, 30...Atomizing air type fuel nozzle, 31...Atomizing manifold, 32...
Main air compressor, 33... Air filter, 34...
...Atomizing air cooler, 35...Bypass valve, 36...
...Cooling water pump, 37...Radiator fan, 38
...Radiator, 46...Air filter, 48...
Orifice.
Claims (1)
ガスタービン運転に必要な噴霧空気を供給する噴
霧空気圧縮機と制御弁から成る噴霧空気系統と噴
霧空気遮断後、噴霧空気型燃料ノズルの噴霧空気
通路部をパージする２系統によつて、着火から加
速時までを噴霧空気によつて燃料を噴霧させ、着
火から加速時までの燃焼安定性を確保し、噴霧空
気遮断後圧力噴霧によつて燃焼を継続させること
によつて、ガスタービン全運転範囲で噴霧空気を
必要としないことを特徴とするガスタービン燃料
噴霧空気制御装置。 The atomizing air system consists of an atomizing air type fuel nozzle, an atomizing air compressor that supplies the atomizing air necessary for gas turbine operation from ignition to acceleration, and a control valve, and an atomizing air passage of the atomizing air type fuel nozzle after the atomizing air is shut off. By using two systems to purge the fuel, the fuel is atomized by atomizing air from ignition to acceleration, ensuring combustion stability from ignition to acceleration, and after the atomizing air is shut off, combustion is carried out by pressure spraying. A gas turbine fuel atomizing air control device characterized in that, by continuous operation, atomizing air is not required throughout the entire operating range of the gas turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10694585U JPS6216738U (en) | 1985-07-15 | 1985-07-15 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP10694585U JPS6216738U (en) | 1985-07-15 | 1985-07-15 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS6216738U true JPS6216738U (en) | 1987-01-31 |
Family
ID=30982772
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP10694585U Pending JPS6216738U (en) | 1985-07-15 | 1985-07-15 |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS6216738U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001241333A (en) * | 2000-02-29 | 2001-09-07 | General Electric Co <Ge> | Dual orifice bypass system for binary fuel gas turbine |
-
1985
- 1985-07-15 JP JP10694585U patent/JPS6216738U/ja active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001241333A (en) * | 2000-02-29 | 2001-09-07 | General Electric Co <Ge> | Dual orifice bypass system for binary fuel gas turbine |
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