JPH05280710A - Gas turbine combustion apparatus - Google Patents
Gas turbine combustion apparatusInfo
- Publication number
- JPH05280710A JPH05280710A JP546392A JP546392A JPH05280710A JP H05280710 A JPH05280710 A JP H05280710A JP 546392 A JP546392 A JP 546392A JP 546392 A JP546392 A JP 546392A JP H05280710 A JPH05280710 A JP H05280710A
- Authority
- JP
- Japan
- Prior art keywords
- combustion
- fuel
- stage
- premixed
- chamber
- 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.)
- Granted
Links
Landscapes
- Spray-Type Burners (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明はガスタビーン燃焼器にお
ける希薄予混合気形成装置に関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a lean premixed gas forming apparatus for a gas tabine combustor.
【０００２】[0002]
【従来の技術】希薄予混合燃焼を主体とするガスタービ
ン燃焼器の一例は特開昭62−13932 号公報に示されてお
り、その概略図を図３に示した。第１段燃焼室７では第
１燃料ノズル９から供給された燃料が拡散燃焼し、起動
から１００％負荷まで常時燃焼する。一方、第２段燃焼
室８では第２燃料ノズル１０から供給された燃料が予混
合室４において空気と予混合した後に供給され、燃焼す
る。この第２段燃焼は予混合燃焼であり、燃料希薄状態
で燃焼するとＮＯｘ生成は少ないが、燃料がわずかに濃
くなると拡散燃焼よりもＮＯｘ生成が多くなる特性を有
する。そこで、燃料希薄状態に保ち、安定燃焼させるた
めに空気調節弁５を設け、ガスタービン負荷の高い状態
で使用している。2. Description of the Related Art An example of a gas turbine combustor mainly composed of lean premixed combustion is shown in JP-A-62-13932, and its schematic diagram is shown in FIG. In the first-stage combustion chamber 7, the fuel supplied from the first fuel nozzle 9 is diffusively combusted, and is constantly combusted from startup to 100% load. On the other hand, in the second-stage combustion chamber 8, the fuel supplied from the second fuel nozzle 10 is premixed with air in the premix chamber 4 and then supplied and burned. The second-stage combustion is a premixed combustion and has a characteristic that NOx generation is small when the fuel is burned in a lean fuel state, but NOx generation is larger when the fuel is slightly richer than the diffusion combustion. Therefore, in order to keep the fuel lean and to perform stable combustion, the air control valve 5 is provided and used under a high gas turbine load.
【０００３】[0003]
【発明が解決しようとする課題】上記従来技術はガスタ
ービン低負荷時に第１段燃焼室のみで燃焼するため、燃
焼器供給空気の５０％程度を消費し、第２段燃焼室へ供
給する空気が５０％以下となるため、ガスタービン１０
０％負荷近傍で第２段燃焼負薄予混合燃焼する燃料割合
を十分に大きくすることができない。その結果、第１段
拡散燃焼によって生成するＮＯｘが多く、全体として十
分ＮＯｘの低い燃焼を実現できない。In the above-mentioned prior art, since the combustion occurs only in the first-stage combustion chamber when the load of the gas turbine is low, about 50% of the air supplied to the combustor is consumed and the air supplied to the second-stage combustion chamber is consumed. Is 50% or less, the gas turbine 10
It is not possible to sufficiently increase the fuel ratio of the second-stage combustion thin lean premix combustion near the 0% load. As a result, a large amount of NOx is generated by the first-stage diffusion combustion, and it is not possible to realize combustion with sufficiently low NOx as a whole.
【０００４】本発明の目的は、第１段拡散燃焼割合を少
なくし、第２段燃料希薄予混合燃焼割合を多くすること
によりＮＯｘ排出濃度を低減する燃料希薄予混合気形成
方法を提供することにある。An object of the present invention is to provide a method for forming a lean fuel premixture which reduces the NOx emission concentration by decreasing the first stage diffusion combustion ratio and increasing the second stage fuel lean premixed combustion ratio. It is in.
【０００５】[0005]
【課題を解決するための手段】上記目的を達成するため
に、本発明は燃焼空気全体通路に相当する内筒と外筒と
によって構成される通路に燃焼噴射口を設け、第１段燃
焼室の第１燃料ノズルと第２段燃焼室の第２燃料ノズル
とは別系統の燃料供給系統を設け、ガスタービン負荷に
応じて燃料流量配分を制御できるようにした。In order to achieve the above object, the present invention provides a combustion injection port in a passage constituted by an inner cylinder and an outer cylinder corresponding to a combustion air whole passage, and a first stage combustion chamber. The first fuel nozzle and the second fuel nozzle of the second-stage combustion chamber are provided with a separate fuel supply system so that the fuel flow rate distribution can be controlled according to the gas turbine load.
【０００６】[0006]
【作用】内筒と外筒とによって構成される通路に設けた
第３燃料ノズルは燃焼空気全体に燃料を供給し、混合気
形成位置状態での不燃燃料希薄混合気をつくる。この混
合気の一部は第１段燃焼室にはいり、第１燃料ノズルか
ら噴射される燃料の拡散燃焼用空気として使われると同
時に、拡散燃焼によって生成した高温ガスにより、予混
合燃焼も進行する。この際に第１段燃焼室に供給される
燃料は一部分が予混合燃焼するので残りの拡散燃焼する
燃料は従来よりも少なくなる。全体混合気の残りは第２
段燃焼室の予混合室に供給され、第２燃料ノズルから追
加された燃料と混合した後に第２段燃焼室で希薄予混合
燃焼する。この際に第２燃料ノズルから供給される燃料
は従来よりも少ない。The third fuel nozzle provided in the passage constituted by the inner cylinder and the outer cylinder supplies the fuel to the entire combustion air to form a lean mixture of non-combustible fuel in the mixture forming position. Part of this air-fuel mixture enters the first-stage combustion chamber and is used as diffusion combustion air for the fuel injected from the first fuel nozzle, and at the same time, premixed combustion also progresses due to the high-temperature gas produced by diffusion combustion. .. At this time, a part of the fuel supplied to the first-stage combustion chamber undergoes premixed combustion, so that the remaining amount of diffusion-combusted fuel becomes smaller than in the conventional case. The rest of the overall mixture is second
It is supplied to the premixing chamber of the staged combustion chamber and mixed with the fuel added from the second fuel nozzle, and then lean premixed combustion is performed in the stage 2 combustion chamber. At this time, the amount of fuel supplied from the second fuel nozzle is smaller than in the conventional case.
【０００７】[0007]
【実施例】以下、本発明の一実施例を図１，図２により
説明する。円筒状の第１段燃焼室７は側面及び上流端面
に空気孔及び冷却孔を有する第１段内筒３によって形成
され、その上流端には燃料を噴射する単一又は複数個の
第１燃料ノズル９を有する。第１段燃焼室７の下流には
第２段内筒２によって形成される第２段燃焼室８を設け
ており、この燃焼室へは第１段燃焼室７の外周に設けた
予混合室４を通して燃料と空気の予混合気を供給する。
予混合室４には燃料を供給する第２燃料ノズル１０を設
け、入口部には空気流量を制御するための空気調節弁５
を設けている。予混合室４出口には予混合燃焼を安定化
するための保炎器６を設けている。第２段燃焼室２の外
周には第３燃料ノズル１１を設け、燃料用空気全体に燃
料を供給する。これらの各要素を収納する圧力容器が外
筒１である。３種類の燃料ノズルへは各々が燃料流量調
節弁１４，１６，１８を有する燃料供給管１３，１５，
１７を有する。図示しない圧縮機からの空気は外周１と
第２段内筒２とで形成される環状通路１２を矢印１９の
方向に流れ、第１段燃焼室７では拡散燃焼単独又は拡散
と予混合燃焼の組み合せによって燃焼ガスを生成し、第
２段燃焼室８では予混合燃焼によって燃焼ガスを生成す
る。燃焼ガスは矢印２０の方向に流れ、尾筒を介してタ
ービン静翼，動翼へと流れて行く。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described below with reference to FIGS. The cylindrical first-stage combustion chamber 7 is formed by the first-stage inner cylinder 3 having air holes and cooling holes on the side surface and the upstream end surface, and the upstream end thereof has a single or a plurality of first fuels for injecting fuel. It has a nozzle 9. A second-stage combustion chamber 8 formed by the second-stage inner cylinder 2 is provided downstream of the first-stage combustion chamber 7, and a pre-mixing chamber provided on the outer periphery of the first-stage combustion chamber 7 is connected to this combustion chamber. A premixture of fuel and air is supplied through 4.
The premixing chamber 4 is provided with a second fuel nozzle 10 for supplying fuel, and an air control valve 5 for controlling an air flow rate is provided at an inlet portion.
Is provided. A flame stabilizer 6 for stabilizing premixed combustion is provided at the outlet of the premixing chamber 4. A third fuel nozzle 11 is provided on the outer periphery of the second-stage combustion chamber 2 to supply the fuel to the entire fuel air. The pressure vessel that accommodates each of these elements is the outer cylinder 1. Fuel supply pipes 13, 15, each having fuel flow rate control valves 14, 16, 18 for the three types of fuel nozzles,
Have 17. Air from a compressor (not shown) flows in the direction of arrow 19 through the annular passage 12 formed by the outer periphery 1 and the second-stage inner cylinder 2, and in the first-stage combustion chamber 7, diffusion combustion alone or diffusion and premixed combustion occurs. Combustion gas is generated by the combination, and combustion gas is generated by premixed combustion in the second stage combustion chamber 8. The combustion gas flows in the direction of arrow 20, and flows to the turbine vanes and moving blades via the transition piece.
【０００８】このガスタービン燃焼器では図２のガスタ
ービン負荷Ａ以下では第１段燃焼室７のみで燃焼し、第
１燃料ノズル９から燃料Ｆ1 を供給する拡散燃焼であ
る。ガスタービン負荷がＡ以上になると、第２段燃焼室
８の予混合室４へ第２燃料ノズル１０から燃料Ｆ2 を供
給し、又、第３燃料ノズル１１から燃焼用空気全体に燃
料Ｆ3 を供給する。この結果、ガスタービン負荷１００
％ではＦ1 が第１燃料ノズルから供給されて第１段燃焼
室７で拡散燃焼する。第３燃料ノズル１１から供給され
たＦ3 のうちでＤＥは第１段燃焼室７に予混合気として
供給され、その一部はＦ1 が拡散燃焼する際に同時に燃
焼し、残りは拡散燃焼の下流で予混合燃焼する。Ｆ3 の
残りのＥＦは予混合気として予混合室４に供給され、第
２燃料ノズル１０からの燃料Ｆ2 が追加されることによ
り、保炎器６で保炎可能な予混合気となって第２段燃焼
室８で予混合燃焼する。本実施例によれば第１段燃焼室
７でのＮＯｘ生成の多い拡散燃焼割合が図２のＤＥの一
部分に相当する分だけ減少することによってＮＯｘ生成
を減少できるとともに、第２段燃焼室８へ供給する予混
合気形成が、図２のＥＦがまず環状通路１２で行なわ
れ、次に図２のＦ2 が予混合室４で追加されて行なわれ
る二段階方式となるので、均一な予混気を形成しやすく
なり、これもＮＯｘ生成を減少できる。In this gas turbine combustor, under the gas turbine load A of FIG. 2 or less, combustion is performed only in the first-stage combustion chamber 7, and the fuel F 1 is supplied from the first fuel nozzle 9 to perform diffusion combustion. When the gas turbine load becomes equal to or higher than A, to the premix chamber 4 of the second stage combustion chamber 8 of the fuel F 2 supplied from the second fuel nozzle 10, also the fuel F 3 across the combustion air from the third fuel nozzle 11 To supply. As a result, the gas turbine load 100
%, F 1 is supplied from the first fuel nozzle and diffuse-combusted in the first-stage combustion chamber 7. Of F 3 supplied from the third fuel nozzle 11, DE is supplied to the first-stage combustion chamber 7 as a premixed gas, part of which is burned at the same time when F 1 is diffused, and the rest is diffused. Premixed combustion downstream of the. The remaining EF of F 3 is supplied to the premixing chamber 4 as a premixed gas, and the fuel F 2 from the second fuel nozzle 10 is added, so that the flame stabilizer 6 can hold the flame. Premixed combustion in the second-stage combustion chamber 8. According to the present embodiment, the diffusion combustion ratio in the first-stage combustion chamber 7 that produces a large amount of NOx is reduced by an amount corresponding to a part of DE in FIG. 2 is performed in the annular passage 12 first, and then F 2 in FIG. 2 is additionally added in the premixing chamber 4 to form a premixed mixture. Mixtures are more likely to form, which can also reduce NOx production.
【０００９】別の実施例を図４により説明する。第３燃
料ノズル１１を予混合室４の入口と第１段内筒３との中
間に設けており、第１段燃焼室７へ供給する空気全体に
燃料を供給する。本実施例によれば、第３燃料ノズル１
１から供給した燃料Ｆ3 の一部が第１燃料ノズル９から
供給した燃料Ｆ1 が拡散燃焼する際に同時に燃焼する
が、残りの負薄予混合燃焼するので、ＮＯｘの生成を減
少できる。Another embodiment will be described with reference to FIG. A third fuel nozzle 11 is provided in the middle of the inlet of the premix chamber 4 and the first stage inner cylinder 3 to supply fuel to the entire air supplied to the first stage combustion chamber 7. According to this embodiment, the third fuel nozzle 1
A part of the fuel F 3 supplied from No. 1 burns at the same time when the fuel F 1 supplied from the first fuel nozzle 9 diffuses and burns, but the remaining thin lean premixed combustion causes NOx generation to be reduced.
【００１０】[0010]
【発明の効果】本発明によれば、第１段燃焼室において
拡散燃焼と予混合燃焼の組み合せ燃焼が可能になり、Ｎ
Ｏｘ生成の少ない予混合燃焼が加わったことにより、従
来の拡散燃焼単独の場合よりもＮＯｘ生成を減少でき
る。また、本発明を第２段燃焼室供給空気に適用した場
合には、予混合過程が２段になることによって混合気の
濃度均一性が向上し、ＮＯｘ生成を減少できる。According to the present invention, combined combustion of diffusion combustion and premixed combustion is possible in the first stage combustion chamber, and N
The addition of premixed combustion, which produces less Ox, can reduce NOx production more than the conventional diffusion combustion alone. Further, when the present invention is applied to the second stage combustion chamber supply air, the concentration uniformity of the air-fuel mixture is improved by the premixing process having two stages, and NOx generation can be reduced.
【図１】本発明の一実施例の燃焼器部の断面図。FIG. 1 is a sectional view of a combustor portion according to an embodiment of the present invention.
【図２】ガスタービン負荷変化に対する２種類の燃料ノ
ズルへ供給する燃料流量割合を示した燃料分配説明図。FIG. 2 is a fuel distribution explanatory view showing a fuel flow rate ratio to be supplied to two types of fuel nozzles with respect to a gas turbine load change.
【図３】従来発明の燃焼器部の断面図。FIG. 3 is a sectional view of a combustor unit according to the conventional invention.
【図４】本発明の他の実施例の燃焼器部断面図。FIG. 4 is a sectional view of a combustor portion of another embodiment of the present invention.
２…第２段内筒、３…第１段内筒、４…予混合室、９…
第１燃料ノズル、１０…第２燃料ノズル、１１…第３燃
料ノズル。2 ... 2nd stage inner cylinder, 3 ... 1st stage inner cylinder, 4 ... premix chamber, 9 ...
1st fuel nozzle, 10 ... 2nd fuel nozzle, 11 ... 3rd fuel nozzle.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 林 則行 茨城県土浦市神立町502番地 株式会社日 立製作所機械研究所内 (72)発明者 岩井 一躬 茨城県土浦市神立町502番地 株式会社日 立製作所機械研究所内 ─────────────────────────────────────────────────── ─── Continuation of the front page (72) Noriyuki Hayashi, Noriyuki Hayashi, 502 Jinritsu-cho, Tsuchiura-shi, Ibaraki Machinery Research Institute, Hiritsu Manufacturing Co., Ltd. Machinery Research Laboratory
Claims (1)
又は予混合室を経て燃料を供給する燃料ノズルと、これ
らを収納する外筒より成るガスタービン燃焼器におい
て、前記内筒及び前記予混合室と前記外筒とによって形
成される空間に燃料供給部材を設け、前記燃料供給部材
から燃焼器全体燃料供給量の一部を供給し、内筒外部条
件における不燃希薄混合気を形成することを特徴とする
ガスタービン燃焼器。1. A gas turbine combustor comprising an inner cylinder forming a combustion chamber, a fuel nozzle for supplying fuel to the inner cylinder directly or via a premixing chamber, and an outer cylinder accommodating the fuel nozzle and the inner cylinder. And a fuel supply member is provided in a space formed by the premix chamber and the outer cylinder, and a part of the fuel supply amount of the entire combustor is supplied from the fuel supply member to generate a non-combustible lean air-fuel mixture in the condition outside the inner cylinder. A gas turbine combustor characterized by being formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4005463A JP2743675B2 (en) | 1992-01-16 | 1992-01-16 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP4005463A JP2743675B2 (en) | 1992-01-16 | 1992-01-16 | Gas turbine combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH05280710A true JPH05280710A (en) | 1993-10-26 |
| JP2743675B2 JP2743675B2 (en) | 1998-04-22 |
Family
ID=11611928
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP4005463A Expired - Lifetime JP2743675B2 (en) | 1992-01-16 | 1992-01-16 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2743675B2 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005345095A (en) * | 2004-06-04 | 2005-12-15 | General Electric Co <Ge> | Method and device for for low-emission gas turbine power generation |
| JP2016114329A (en) * | 2014-12-17 | 2016-06-23 | 三菱日立パワーシステムズ株式会社 | Operational method for gas burning burner and gas burning burner |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59101551A (en) * | 1982-11-08 | 1984-06-12 | シーメンス、アクチエンゲゼルシヤフト | Pre-mixing burner assembled with diffusion burner for gas turbine combustion chamber |
| JPS6213932A (en) * | 1985-07-10 | 1987-01-22 | Hitachi Ltd | Combustor for gas turbine |
| JPH0250026A (en) * | 1988-08-08 | 1990-02-20 | Hitachi Ltd | Gas turbine combustor and its operation method |
-
1992
- 1992-01-16 JP JP4005463A patent/JP2743675B2/en not_active Expired - Lifetime
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS59101551A (en) * | 1982-11-08 | 1984-06-12 | シーメンス、アクチエンゲゼルシヤフト | Pre-mixing burner assembled with diffusion burner for gas turbine combustion chamber |
| JPS6213932A (en) * | 1985-07-10 | 1987-01-22 | Hitachi Ltd | Combustor for gas turbine |
| JPH0250026A (en) * | 1988-08-08 | 1990-02-20 | Hitachi Ltd | Gas turbine combustor and its operation method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2005345095A (en) * | 2004-06-04 | 2005-12-15 | General Electric Co <Ge> | Method and device for for low-emission gas turbine power generation |
| JP2016114329A (en) * | 2014-12-17 | 2016-06-23 | 三菱日立パワーシステムズ株式会社 | Operational method for gas burning burner and gas burning burner |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2743675B2 (en) | 1998-04-22 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| KR100246266B1 (en) | Apparatus for reducing fuel/air concentration oscillation in gas turbine combustors | |
| US5201181A (en) | Combustor and method of operating same | |
| US6915636B2 (en) | Dual fuel fin mixer secondary fuel nozzle | |
| JP4220558B2 (en) | Combustion device for gas turbine engine | |
| US6722132B2 (en) | Fully premixed secondary fuel nozzle with improved stability and dual fuel capability | |
| KR950001074A (en) | Gas turbine burner | |
| US20100319353A1 (en) | Multiple Fuel Circuits for Syngas/NG DLN in a Premixed Nozzle | |
| JPH01114623A (en) | Gas turbine combustor | |
| JPH06193841A (en) | Gas operation type premix burner | |
| JPH05203148A (en) | Gas turbine combustion apparatus and its control method | |
| JPH0579631A (en) | Combustion device facility | |
| US6874323B2 (en) | Low emissions hydrogen blended pilot | |
| JP2865684B2 (en) | Gas turbine combustor | |
| JPH08135970A (en) | Gas turbine combustor | |
| JP2005265232A (en) | Gas turbine combustor | |
| JP2010054087A (en) | Gas turbine combustor and operating method of gas turbine combustor | |
| WO1998025084A1 (en) | DIFFUSION AND PREMIX PILOT BURNER FOR LOW NOx COMBUSTOR | |
| JPH05280710A (en) | Gas turbine combustion apparatus | |
| JPH0115775B2 (en) | ||
| JPS6277520A (en) | Low nox gas turbine combustor | |
| JP3174638B2 (en) | Premix structure of gas turbine combustor | |
| JPH0443726Y2 (en) | ||
| JP3482718B2 (en) | Gas turbine combustor | |
| JPH06213456A (en) | Combustion device for gas turbine and its fuel control device | |
| JPH08261468A (en) | Gas turbine combustor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Year of fee payment: 10 Free format text: PAYMENT UNTIL: 20080206 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090206 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20090206 Year of fee payment: 11 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20100206 Year of fee payment: 12 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Year of fee payment: 12 Free format text: PAYMENT UNTIL: 20100206 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Year of fee payment: 13 Free format text: PAYMENT UNTIL: 20110206 |
|
| FPAY | Renewal fee payment (prs date is renewal date of database) |
Free format text: PAYMENT UNTIL: 20120206 Year of fee payment: 14 |
|
| EXPY | Cancellation because of completion of term |