JPH07332671A - Pre-evaporizing premixing combustor - Google Patents

Pre-evaporizing premixing combustor

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Publication number
JPH07332671A
JPH07332671A JP15175494A JP15175494A JPH07332671A JP H07332671 A JPH07332671 A JP H07332671A JP 15175494 A JP15175494 A JP 15175494A JP 15175494 A JP15175494 A JP 15175494A JP H07332671 A JPH07332671 A JP H07332671A
Authority
JP
Japan
Prior art keywords
passage
fuel
evaporation
mixing
fuel injection
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
Application number
JP15175494A
Other languages
Japanese (ja)
Other versions
JP2666117B2 (en
Inventor
Yoichiro Okubo
陽一郎 大久保
Yoshihiro Nomura
佳洋 野村
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
NIPPON JIDOSHA KENKYUSHO
SEKIYU SANGYO KASSEIKA CENTER
Japan Petroleum Energy Center JPEC
Original Assignee
NIPPON JIDOSHA KENKYUSHO
SEKIYU SANGYO KASSEIKA CENTER
Petroleum Energy Center PEC
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Filing date
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Application filed by NIPPON JIDOSHA KENKYUSHO, SEKIYU SANGYO KASSEIKA CENTER, Petroleum Energy Center PEC filed Critical NIPPON JIDOSHA KENKYUSHO
Priority to JP15175494A priority Critical patent/JP2666117B2/en
Publication of JPH07332671A publication Critical patent/JPH07332671A/en
Application granted granted Critical
Publication of JP2666117B2 publication Critical patent/JP2666117B2/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Abstract

PURPOSE:To facilitate the operation of a gas turbine by expanding an operation condition range wherein flames in a combustion chamber are stabilized by a method wherein the evaporizing and mixing of a liquid fuel which are sufficient for a sudden change of the fuel injection quantity are ensured in a required wide fuel flow rate range, and at the same time, the fuel concentration and speed distribution of a premixed gas which is introduced to a combustion chamber are uniformed. CONSTITUTION:This combustor is equipped with a pre-evaporizing premixing passage 21 wherein a fuel which is jetted from a fuel injection valve 20 is mixed with air for combustion while evaporizing the fuel, and a combustion chamber 6 which is connected to the downstream side of the pre-evaporizing premixing passage. Then, at an upstream side of the pre- evaporizing premixing passage 21, a rotating device 23 which imparts a rotational speed to the air for combustion is provided. Then, the fuel injection valve 20 is arranged at the axial center area of the pre-evaporizing premixing passage 21. Then, on the outer peripheral of the fuel injection valve 20, the pre-evaporizing premixing passage 21 consisting of first, second and third annular passages 19a, 19b, 19c is arranged into an annular axially symmetrical form. Then, a fuel is jetted into the pre-evaporizing premixing passage from the fuel injection valve 20 with a plurality of fuel injection holes 28 which are provided on the internal wall of the annular pre-evaporizing premixing passage.

Description

【発明の詳細な説明】Detailed Description of the Invention

【０００１】[0001]

【産業上の利用分野】本発明は、主としてガスタービン
に用いられる予蒸発予混合燃焼器に関するものである。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a pre-evaporative pre-mixing combustor mainly used in a gas turbine.

【０００２】[0002]

【従来の技術】従来の予蒸発予混合燃焼器は図８で示す
ように、プライマリ燃料噴射弁１４から噴射した燃料を
スワーラ１３によって渦流を生成し予蒸発予混合管１２
を介して導入する旋回室４と、この旋回室４と環状流路
形成部材５（オリフィス）によるスロート部１１を介し
て連通する燃焼室６と、前記旋回室４内を貫通する保炎
器３を介して配置され、前記燃焼室６内に燃料を噴射す
るセカンダリ燃料噴射弁２とを備えている。2. Description of the Related Art As shown in FIG. 8, a conventional pre-evaporation pre-mixing combustor generates swirl flow of fuel injected from a primary fuel injection valve 14 by a swirler 13 to generate a pre-evaporation pre-mixing tube 12.
A swirl chamber 4 introduced through the swirl chamber 4, a combustion chamber 6 communicating with the swirl chamber 4 through a throat portion 11 formed by an annular flow path forming member 5 (orifice), and a flame stabilizer 3 penetrating the swirl chamber 4 And a secondary fuel injection valve 2 for injecting fuel into the combustion chamber 6.

【０００３】前記燃焼室６にはエクステンションライナ
７およびゾーンセパレータ８を介して希釈ライナー９が
結合されている。前記保炎器３，旋回室４，環状流路形
成部材５，燃焼室６，エクステンションライナ７，ゾー
ンセパレータ８および希釈ライナー９はすべてセラミッ
クであり、ボルト等により締め付け結合ができないた
め、これらを積み重ねて支持部材１０で支持している。
１は前記支持部材１０等を保持する燃焼器キャップであ
り、図略のエンジン本体に固着されている。１８は点火
栓であり、着火の時のみ燃焼室６内に前進して侵入し、
着火後は後退して燃焼室６外に待機する。A dilution liner 9 is connected to the combustion chamber 6 via an extension liner 7 and a zone separator 8. The flame stabilizer 3, the swirl chamber 4, the annular flow path forming member 5, the combustion chamber 6, the extension liner 7, the zone separator 8 and the dilution liner 9 are all made of ceramic and cannot be fastened together by bolts or the like. Are supported by the support member 10.
Reference numeral 1 denotes a combustor cap that holds the support member 10 and the like, and is fixed to an unillustrated engine body. Reference numeral 18 is a spark plug, which advances and enters the combustion chamber 6 only at the time of ignition,
After ignition, the vehicle retreats and stands by outside the combustion chamber 6.

【０００４】前記の構成よりなるガスタービンの予混合
燃焼器は、始動時に前記点火栓１８を燃焼室６内に前進
して侵入させ、セカンダリ燃料噴射弁２によって燃焼室
６内に燃料を噴射して着火する。この着火後に燃料噴射
はプライマリ燃料噴射弁１４に切替えられ、点火栓１８
は後退して燃焼室６外に位置させ、点火栓１８を高熱に
さらされないようにする。In the premixed combustor of the gas turbine having the above-mentioned structure, the spark plug 18 is advanced and penetrates into the combustion chamber 6 at the time of starting, and the secondary fuel injection valve 2 injects fuel into the combustion chamber 6. To ignite. After this ignition, the fuel injection is switched to the primary fuel injection valve 14, and the spark plug 18
Is retracted and positioned outside the combustion chamber 6 so that the spark plug 18 is not exposed to high heat.

【０００５】前記プライマリ燃料噴射弁１４から噴射さ
れる燃料はスワーラ１３によって渦流を生成し予蒸発予
混合管１２を介して旋回室４に導入され、スロート部１
１を通過して燃焼室６内に入り、この燃焼室６内で燃焼
する。エンジンが低負荷の場合は前記プライマリ燃料噴
射弁１４からの燃料噴射であるが、エンジンの負荷が上
がり、ある一定以上の高負荷になった場合は、プライマ
リ燃料噴射弁１４とセカンダリ燃料噴射弁２とによって
燃料噴射を行うよう制御される。上記従来の予蒸発予混
合燃焼器では、未燃ガスやＮＯｘ等の有害ガスを低減す
ることを主眼にしている。また、二酸化炭素の排出を低
減するためにガスタービンの燃料消費量を低減すること
も重要な技術課題で、例えば文献（アメリカ機械学会論
文 ９３−ＧＴ−６３）にあるように高効率な自動車用
ガスタービンの研究開発を進めている。The fuel injected from the primary fuel injection valve 14 generates a vortex flow by the swirler 13 and is introduced into the swirl chamber 4 through the pre-evaporation premixing pipe 12 and the throat section 1
1 to enter the combustion chamber 6 and burn in the combustion chamber 6. When the load of the engine is low, the fuel is injected from the primary fuel injection valve 14. However, when the load of the engine is increased and the load is higher than a certain level, the primary fuel injection valve 14 and the secondary fuel injection valve 2 And are controlled to perform fuel injection. The above-mentioned conventional pre-evaporation pre-mixing combustor aims to reduce harmful gases such as unburned gas and NOx. Further, reducing the fuel consumption of the gas turbine in order to reduce the emission of carbon dioxide is also an important technical subject. For example, as shown in the literature (American Society of Mechanical Engineers article 93-GT-63), it is highly efficient for automobiles. We are researching and developing gas turbines.

【０００６】この研究等では、燃料消費量の少ない１０
０ｋｗ級のガスタービンを開発しており、その燃焼器で
は燃焼すべき液体燃料の噴射流量が最低で毎秒０．２グ
ラム以下となり、非常に少量である。一方、最大噴射量
が毎秒９グラムも要求されるため、燃料噴射弁のターン
ダウン比は４５以上が要求されることになり、広い流量
範囲にわたって良好な微粒化特性が要求される。In this research, the fuel consumption is low.
We are developing a 0kw class gas turbine, and the combustor has an injection flow rate of liquid fuel to be combusted of at least 0.2 grams per second, which is a very small amount. On the other hand, since the maximum injection amount is required to be 9 grams per second, the turndown ratio of the fuel injection valve is required to be 45 or more, and good atomization characteristics are required over a wide flow rate range.

【０００７】そこで、前記図８に示すように、最小燃料
流量の毎秒０．２グラム以下を実現するために単噴孔の
気流噴射弁で液体燃料を噴霧状にして燃焼器側方の一方
向から供給すると共に、予蒸発予混合部で燃料噴霧を予
め蒸発させつつ燃焼用空気と十分に混合させた後に燃焼
室に供給する予蒸発予混合燃焼器が開発されている。こ
の燃焼器では空気過剰の希薄燃焼をさせて主にＮＯｘ排
出を抑制しつつ高い燃焼効率を達成している。Therefore, as shown in FIG. 8, in order to realize a minimum fuel flow rate of 0.2 g / sec or less, liquid fuel is atomized by an air flow injection valve having a single injection hole and is directed in one direction on the side of the combustor. A pre-evaporative premixing combustor has been developed in which the fuel spray is pre-evaporated in the pre-evaporation pre-mixing section and sufficiently mixed with combustion air before being supplied to the combustion chamber. This combustor achieves high combustion efficiency while suppressing lean NOx emissions by performing lean combustion with excess air.

【０００８】また、ガスタービン用燃焼器の蓋部回りの
小型，単純化を目的として、燃料噴射弁をアクチュエー
タにより軸回りに回転させることにより、前記燃料噴射
弁の突起部に係合するスワーラ本体及び爪部を介して希
釈用空気量制御用円筒も一体に軸回りに回転させ、蒸発
用空気導入孔とスワール生成孔との重合開口面積及び希
釈用空気導入孔の重合開口面積を可変に制御して空燃比
一定の燃焼をおこなわせるようにした燃焼器が特開平４
−２４４５１２号で提供されている。For the purpose of downsizing and simplifying the circumference of the lid of the gas turbine combustor, the swirler main body which engages with the projection of the fuel injection valve by rotating the fuel injection valve around the axis by an actuator. Also, the cylinder for controlling the amount of dilution air is integrally rotated around the axis via the claws to variably control the polymerization opening area of the evaporation air introduction hole and the swirl generation hole and the polymerization opening area of the dilution air introduction hole. A combustor configured to perform combustion with a constant air-fuel ratio is disclosed in Japanese Unexamined Patent Publication
No. 244,512.

【０００９】[0009]

【発明が解決しようとする課題】前記従来技術の前者の
予蒸発予混合燃焼器では、軽油や灯油等の比較的蒸発し
にくい液体燃料を完全に蒸発・混合するためには十分に
長い蒸発・混合距離を燃焼室の上流通路に設ける必要が
ある。このため、燃焼器全体の構造寸法が大きくなりコ
ンパクトなガスタービンには採用できない不具合があ
る。また、蒸発・混合距離が長いと予蒸発予混合通路内
で着火したり火炎が壁近傍を伝播したりする不具合があ
り、実用化が困難であった。In the former pre-evaporative pre-mixing combustor of the above-mentioned prior art, it is necessary to evaporate and mix a liquid fuel such as light oil or kerosene that is relatively hard to evaporate sufficiently long. It is necessary to provide a mixing distance in the upstream passage of the combustion chamber. For this reason, the structural size of the entire combustor becomes large, and there is a problem that it cannot be used in a compact gas turbine. Further, if the evaporation / mixing distance is long, there is a problem that ignition occurs in the pre-evaporation pre-mixing passage or the flame propagates in the vicinity of the wall, which makes practical application difficult.

【００１０】さらに、前記従来の予蒸発予混合燃焼器で
は、要求される燃焼器の作動条件が時間経過とともに大
きく変化するため、液体燃料を完全蒸発させつつ燃焼用
空気と完全な予混合をすることが技術的に困難であっ
た。例えば、燃焼器の全平均空燃比は７５から４５０
に、燃焼器入口の空気温度は９００℃から１１００℃に
も変化する。このため、エンジン作動条件により燃焼室
に導入される予蒸発予混合気の状況は大きく変化してし
まう。Further, in the above-mentioned conventional pre-evaporative pre-mixing combustor, the required operating conditions of the combustor change greatly with the passage of time, so that the liquid fuel is completely vaporized and completely pre-mixed with the combustion air. Was technically difficult. For example, the overall average air-fuel ratio of the combustor is 75 to 450.
In addition, the air temperature at the combustor inlet varies from 900 ° C to 1100 ° C. For this reason, the condition of the pre-evaporated pre-mixture introduced into the combustion chamber changes greatly depending on the engine operating conditions.

【００１１】さらに、予蒸発予混合部から燃焼室に流入
する予混合気の燃料濃度と流入速度が空間的にも時間的
にも不均一を生じている。例えば、文献（平成５年度ガ
スタービン秋季講演会論文集Ａ−１４，Ａ−１５あるい
はＡ−１６）にあるように、予蒸発予混合通路出口のス
ロート部で壁面近傍に燃料噴霧が片寄り、しかもその領
域の流速が遅いため、特に予蒸発予混合部の温度、圧力
が高い場合、容易に燃焼室内の火炎が予蒸発予混合部の
上流に逆火して、上流の構造部品を熱損傷する不具合が
ある。Further, the fuel concentration and the inflow velocity of the premixed gas flowing into the combustion chamber from the preevaporative premixing section are nonuniform both spatially and temporally. For example, as described in the literature (Abstracts of Gas Turbine Autumn Meeting 1993, A-14, A-15 or A-16), the fuel spray is biased near the wall surface at the throat of the pre-evaporation premixing passage, Moreover, since the flow velocity in that region is slow, especially when the temperature and pressure in the pre-evaporation pre-mixing section are high, the flame in the combustion chamber easily flashes back to the upstream side of the pre-evaporation pre-mixing section, causing thermal damage to the upstream structural parts. There is a problem to do.

【００１２】または、予混合気の周方向に濃度の不均一
が発生して、スロート部の円周上のある領域では希薄に
なりすぎてしまうために火炎が燃焼室内に保持しきれな
くなって吹き飛ぶこともある。例え、予混合気の空気過
剰率が一定になるように可変機構を駆使して燃焼用空気
量を噴射燃料に対応するよう制御して火炎安定性を確保
しようとしても、予混合気の時間的・空間的な変化と不
均一のために燃焼室内に火炎を安定に保持させることが
困難であった。結果として、従来の予蒸発予混合燃焼器
では、高効率ガスタービンの運転ができない条件があっ
た。また、火炎が安定な従来の噴霧燃焼器では目標とす
る排気清浄化（例えば自動車の長期排気規制値）を達成
することが不可能に近い状況である。[0012] Alternatively, the non-uniformity of the concentration occurs in the circumferential direction of the premixed gas, and it becomes too lean in a certain area on the circumference of the throat portion, so that the flame cannot be held in the combustion chamber and blows off. Sometimes. For example, even if an attempt is made to ensure flame stability by controlling the amount of combustion air to correspond to the injected fuel by making full use of a variable mechanism so that the excess air ratio of the premixture becomes constant,・ It was difficult to keep the flame stable in the combustion chamber due to spatial variation and non-uniformity. As a result, in the conventional pre-evaporative pre-mixing combustor, there was a condition that the high-efficiency gas turbine could not be operated. Further, it is almost impossible to achieve the target exhaust gas purification (for example, the long-term exhaust gas regulation value of an automobile) with the conventional spray combustor with stable flame.

【００１３】比較的短い寸法あるいはコンパクトな構造
で、十分な予混合と予蒸発を達成して、均一な燃料・空
気混合気を形成させるためには、前記従来技術の後者の
燃焼器（特開平４−２４４５１２号）のように単に予蒸
発予混合通路に燃料を噴射するだけでは、旋回流が強い
と壁面に燃料が集中して燃料濃度の不均一が形成され、
十分に均一な予混合気を生成させることができず、低Ｎ
Ｏｘ燃焼を達成することができない。また、ストレート
な環状の前記予蒸発予混合通路では、通路内に２次流れ
や剥離領域が形成されて、この領域に燃料が滞留してし
まうため、この領域に火炎が形成される不具合がある。In order to achieve sufficient premixing and preevaporation with a relatively short size or compact structure to form a uniform fuel-air mixture, the latter combustor of the above-mentioned prior art (Japanese Patent Laid-Open No. Hei 10 (1999) -264242). No. 4-244512), if the fuel is simply injected into the pre-evaporation pre-mixing passage, if the swirl flow is strong, the fuel is concentrated on the wall surface and the fuel concentration becomes non-uniform.
It is not possible to generate a sufficiently uniform premixed gas, and low N
Ox combustion cannot be achieved. Further, in the straight annular pre-evaporation pre-mixing passage, a secondary flow or a separation region is formed in the passage, and fuel accumulates in this region, so that a flame is formed in this region. .

【００１４】本発明の目的は、要求される広い燃料流量
範囲（ターンダウン比４５以上）で、急峻な燃料噴射量
の変化に対しても十分な液体燃料の蒸発と混合を確保す
ると共に、予蒸発予混合通路のスロート部から燃焼室に
導入される予混合気の燃料濃度と速度分布の均一化を図
り、燃焼室内の火炎が安定になる作動条件範囲を拡大し
てガスタービンの運転を容易にすると同時に排気清浄化
を実現する予蒸発予混合燃焼器を提供することである。The object of the present invention is to ensure sufficient vaporization and mixing of liquid fuel even in the case of a sharp change in the fuel injection amount within a required wide fuel flow rate range (turndown ratio 45 or more), and Easier operation of the gas turbine by expanding the operating condition range in which the flame in the combustion chamber is stabilized by making the fuel concentration and velocity distribution of the premixed gas introduced into the combustion chamber from the throat of the evaporation premixing passage uniform. It is an object of the present invention to provide a pre-evaporation pre-mixing combustor that realizes exhaust gas cleaning at the same time.

【００１５】[0015]

【課題を解決するための手段】上記の目的を達成するた
めの本発明の特徴とする構成は、燃料噴射弁と、前記燃
料噴射弁から噴射した燃料を蒸発させつつ、燃焼用空気
と混合する予蒸発予混合通路とを備え、前記予蒸発予混
合通路の下流に燃焼室を連接する予蒸発予混合燃焼器で
あって、前記予蒸発予混合通路の上流には燃焼用空気に
旋回速度を付与する旋回装置を設け、前記燃料噴射弁を
前記予蒸発予混合通路の軸中心領域に配置すると共に、
その外周に前記予蒸発予混合通路を環状の軸対称形状に
配置し、前記旋回装置に連接した前記予蒸発予混合通路
を、旋回速度を付与した燃焼用空気を軸中心方向に流す
第１環状通路部と、その下流に徐々に通路面積を減少さ
せつつ軸中心に向かう半径方向から前記燃焼室の軸方向
に空気を転向させる第２環状通路部および軸方向に混合
気を流す第３環状通路部とを備え、前記環状の予蒸発予
混合通路の内壁に設けた複数の燃料噴射孔を持つ前記燃
料噴射弁から燃料を前記予蒸発予混合通路内に噴射する
構造である。SUMMARY OF THE INVENTION In order to achieve the above-mentioned object, a feature of the present invention is that a fuel injection valve and fuel injected from the fuel injection valve are vaporized and mixed with combustion air. A pre-evaporation pre-mixing passage, wherein the pre-evaporation pre-mixing passage is connected to a combustion chamber downstream of the pre-evaporation pre-mixing passage. A swirl device for imparting is provided, and the fuel injection valve is arranged in the axial center region of the pre-evaporation premixing passage,
A first annular shape in which the pre-evaporation pre-mixing passage is arranged in an annular axisymmetrical shape on the outer periphery thereof, and combustion air having a swirling velocity is caused to flow in the axial center direction through the pre-evaporation pre-mixing passage connected to the swirling device. A passage portion, a second annular passage portion for diverting air in the axial direction of the combustion chamber from the radial direction toward the axial center while gradually reducing the passage area downstream thereof, and a third annular passage for flowing the air-fuel mixture in the axial direction. And a fuel injection valve having a plurality of fuel injection holes provided in the inner wall of the annular pre-evaporation pre-mixing passage, the fuel is injected into the pre-evaporation pre-mixing passage.

【００１６】また、前記予蒸発予混合通路の中央領域に
環状のルーバを設けると共に、前記燃料噴射弁の燃料噴
射孔を前記ルーバの表面に対向する位置に配置し、前記
ルーバの片方の表面に沿っては燃焼用空気が流れて前記
ルーバの後端縁で燃料空気混合気流と空気流が合流する
ように配置して、前記ルーバの後端縁が前記予蒸発予混
合通路の出口より上流位置にある構成にすることであ
る。Further, an annular louver is provided in the central region of the pre-evaporative premixing passage, and the fuel injection hole of the fuel injection valve is arranged at a position facing the surface of the louver, and one surface of the louver is provided. Combustion air flows along the louver so that the fuel-air mixture flow and the air flow merge at the rear edge of the louver, and the rear edge of the louver is located upstream of the outlet of the pre-evaporation premix passage. The configuration is in.

【００１７】さらに、前記予蒸発予混合通路の通路面積
を上流から漸次減少させると共に、前記燃焼室の直前で
通路面積が最小となるスロート部を配置する構造であ
る。Furthermore, the passage area of the pre-evaporation premix passage is gradually reduced from the upstream side, and the throat portion having the minimum passage area is arranged immediately before the combustion chamber.

【００１８】また、通路面積を漸次減少させる前記予蒸
発予混合通路が、前記燃焼室にラッパ状に開口する構造
である。Also, the pre-evaporation pre-mixing passage for gradually reducing the passage area is structured to open like a trumpet in the combustion chamber.

【００１９】さらには、前記旋回装置の上流には燃焼用
空気の流量を調整する開口絞り装置を配置し、燃焼用空
気流量に連動して旋回装置による燃焼用空気に付与する
旋回速度を可変にする機構を備えた構成である。Further, an aperture throttle device for adjusting the flow rate of the combustion air is arranged upstream of the swirl device, and the swirl speed given to the combustion air by the swirl device is variable in association with the flow rate of the combustion air. It is a structure provided with a mechanism.

【００２０】[0020]

【作用】上記の構成により、燃料分散と微粒化および噴
霧蒸発を促進し、著しく短い予蒸発予混合通路で一様で
均一な予混合気を形成して燃焼させることができ、逆火
や自着火に起因する火炎不安定を改善し、可燃範囲を広
く確保して高効率ガスタービンの運転を可能にする。With the above structure, fuel dispersion, atomization, and spray evaporation can be promoted, and a uniform and uniform premixed gas can be formed and burned in a remarkably short pre-evaporative pre-mixing passage. It improves flame instability due to ignition, secures a wide flammable range, and enables high-efficiency gas turbine operation.

【００２１】[0021]

【実施例】以下本発明の実施例を図面に基づいて説明す
る。図１において、６は燃焼室、７はエクステンション
ライナ、８はゾーンセパレータ、９は希釈ライナー、９
ａは希釈孔、９ｂは希釈混合室である。この希釈混合室
９ｂは燃焼室６からの燃焼ガスに希釈孔９ａを通して空
気を混合して燃焼器下流にある図略のガスタービンの耐
熱温度以下に温度を調節するものである。１０は前記燃
焼室６、エクステンションライナ７、ゾーンセパレータ
８、希釈ライナー９等を保持する支持部材である。１８
は着火の時のみ燃焼室６内に前進して侵入し、着火後は
後退して燃焼室６外に待機する点火栓である。Embodiments of the present invention will be described below with reference to the drawings. In FIG. 1, 6 is a combustion chamber, 7 is an extension liner, 8 is a zone separator, 9 is a dilution liner, 9
Reference numeral a is a dilution hole, and reference numeral 9b is a dilution mixing chamber. The dilution / mixing chamber 9b mixes the combustion gas from the combustion chamber 6 with air through the dilution hole 9a to adjust the temperature to a temperature not higher than the heat resistant temperature of a gas turbine (not shown) located downstream of the combustor. Reference numeral 10 is a support member that holds the combustion chamber 6, the extension liner 7, the zone separator 8, the dilution liner 9, and the like. 18
Is a spark plug that advances and enters the combustion chamber 6 only at the time of ignition, and moves backward after the ignition and waits outside the combustion chamber 6.

【００２２】前記燃焼室６の上方の軸中央には燃料噴射
弁２０が配置され、その先端部の外周には軸対称な環状
の予蒸発予混合通路２１を形成し、ブラフボディ２２に
より形成されるスロート部１１を介して燃焼室６に連通
している。A fuel injection valve 20 is arranged in the center of the shaft above the combustion chamber 6, and an axially symmetrical annular pre-evaporation premixing passage 21 is formed on the outer periphery of the tip end portion thereof, and is formed by a bluff body 22. It communicates with the combustion chamber 6 via a throat portion 11 which is provided.

【００２３】前記予蒸発予混合通路２１の上流には旋回
装置２３と、さらにその上流に燃焼用空気量を調節する
開口絞り装置２４を備えている。２５は旋回装置用可操
作軸であり、２６は開口絞り装置用操作軸である。前記
旋回装置２３は図４で示すように、円周上で多数に分割
された固定ブロック２３ｂと、この各固定ブロック２３
ｂ間で円周方向に回動可能であり、前記固定ブロック２
３ｂとによって空気導入スリット２３ｃを形成し、かつ
この空気導入スリット２３ｃの角度および開口絞りを前
記旋回装置用可操作軸２５、開口絞り装置用操作軸２６
で可変設定する可動ブロック２３ａとから構成されてい
る。A swirl device 23 is provided upstream of the pre-evaporative premixing passage 21, and an aperture throttle device 24 for adjusting the amount of combustion air is provided further upstream thereof. Reference numeral 25 is a swivel device operable shaft, and 26 is an aperture diaphragm device operating shaft. As shown in FIG. 4, the swivel device 23 includes a fixed block 23b which is divided into a plurality of pieces on the circumference and each fixed block 23b.
The fixing block 2 is rotatable in the circumferential direction between b and
3b forms an air introduction slit 23c, and the angle of the air introduction slit 23c and the aperture stop are set to the swivel device operable shaft 25 and the aperture diaphragm device operating shaft 26.
And a movable block 23a that is variably set by.

【００２４】前記旋回装置２３に連接した前記予蒸発予
混合通路２１は図２にも示すように、旋回速度を付与し
た燃焼用空気を軸中心方向に流す第１環状通路部１９ａ
と、その下流に徐々に通路面積を減少させつつ軸中心に
向かう半径方向から前記燃焼室６の軸方向に空気を転向
させる第２環状通路部１９ｂおよび軸方向に混合気を流
す第３環状通路部１９ｃとによって形成されている。As shown in FIG. 2, the pre-evaporation pre-mixing passage 21 connected to the swirl device 23 has a first annular passage portion 19a for flowing combustion air having a swirling velocity in the axial center direction.
And a second annular passage portion 19b for diverting air in the axial direction of the combustion chamber 6 from the radial direction toward the axial center while gradually reducing the passage area downstream thereof and a third annular passage for flowing the air-fuel mixture in the axial direction. And the portion 19c.

【００２５】そして、前記旋回装置２３の下流直後には
ルーバ２７が前記予蒸発予混合通路２１の中央に配置さ
れ、前記半径方向から軸方向流れに偏向される第２環状
通路部１９ｂの領域に前記燃料噴射弁２０の燃料噴射孔
２８が、円周上等分配位置に多数個（本実施例では４乃
至６個）が配置されている。この燃料噴射弁２０の燃料
噴射孔２８の噴射方向はルーバ２７の表面に対して噴霧
が衝突する関係位置に向けられている。Immediately downstream of the swirl device 23, a louver 27 is arranged in the center of the pre-evaporative pre-mixing passage 21 in the region of the second annular passage portion 19b deflected from the radial direction to the axial flow. A large number (four to six in this embodiment) of fuel injection holes 28 of the fuel injection valve 20 are arranged at equal distribution positions on the circumference. The injection direction of the fuel injection hole 28 of the fuel injection valve 20 is directed to a relative position where the spray collides with the surface of the louver 27.

【００２６】前記旋回装置２３の下流直後に配置される
ルーバ２７は、その前端縁が図２の左断面図で示すよう
に旋回装置２３に当接させてもよいし、図２の右断面図
で示すように旋回装置２３と離間させてもよい。また、
ルーバ２７の後端縁は図２で示すように前記予蒸発予混
合通路２１の出口より上流に位置するよう配置される
が、図３で示すように燃料噴射弁２０の燃料噴射孔２８
から直接燃料を噴霧衝突させる配置ではなく、ルーバ２
７の後流の予蒸発予混合通路２１中に噴出させるように
配置してもよい。The louver 27 arranged immediately downstream of the swivel device 23 may have its front edge abutted against the swivel device 23 as shown in the left sectional view of FIG. 2, or the right sectional view of FIG. It may be separated from the turning device 23 as shown by. Also,
The rear edge of the louver 27 is arranged so as to be located upstream of the outlet of the pre-evaporative premixing passage 21 as shown in FIG. 2, but as shown in FIG. 3, the fuel injection hole 28 of the fuel injection valve 20.
Louver 2 instead of direct fuel spray collision
7 may be arranged so as to be ejected into the pre-evaporative pre-mixing passage 21 of the downstream side.

【００２７】前記したように予蒸発予混合通路２１の出
口のスロート部１１は燃焼室６の直前にあり、燃焼室軸
の中央領域には前記ブラフボディ２２を形成し、燃焼室
６内の火炎保持を容易にしている。また、ブラフボディ
２２の軸中心には燃料噴射弁２０の先端部が配置されて
いて、その燃料噴射孔は燃焼室６に直面している。As described above, the throat portion 11 at the outlet of the pre-evaporation pre-mixing passage 21 is located immediately before the combustion chamber 6, the bluff body 22 is formed in the central region of the combustion chamber shaft, and the flame inside the combustion chamber 6 is formed. It is easy to hold. Further, the tip of the fuel injection valve 20 is arranged at the axial center of the bluff body 22, and the fuel injection hole faces the combustion chamber 6.

【００２８】前記燃焼室６や予蒸発予混合通路２１を構
成する部品は窒化ケイ素や炭化ケイ素等の高耐熱セラミ
ックでであり、ボルト等により締め付け結合ができない
ため、これらを積み重ねて支持部材１０で支持し、セラ
ミックス製スプリング２９で押し付けている。The parts constituting the combustion chamber 6 and the pre-evaporation pre-mixing passage 21 are high heat-resistant ceramics such as silicon nitride and silicon carbide, which cannot be fastened together by bolts or the like. It is supported and pressed by a ceramic spring 29.

【００２９】前記の構成よりなる予蒸発予混合燃焼器に
おいて、燃焼用の空気は、セラミックガスタービンの主
要な構成部品である空気圧縮機で外気を吸引して圧縮し
た後に熱交換器に送られ、熱交換器では排気ガスの熱で
圧縮空気を加熱した後に燃焼器に供給される。燃焼器入
口における圧縮空気は、ガスタービン定格条件で５気
圧、約９００℃程度になる。空気温度については、部分
負荷条件の方が高く、約１１００℃に達する。このよう
な、高温に加熱された圧縮空気が希釈孔９ａと開口絞り
装置２４で最適に分配される。開口絞り装置２４を通過
した空気は燃焼に使用される。In the pre-evaporative pre-mixing combustor having the above structure, the air for combustion is sent to the heat exchanger after the outside air is sucked and compressed by the air compressor which is a main component of the ceramic gas turbine. In the heat exchanger, the compressed air is heated by the heat of the exhaust gas and then supplied to the combustor. The compressed air at the combustor inlet has a pressure of 5 atm and a temperature of about 900 ° C. under the gas turbine rated conditions. Regarding the air temperature, the partial load condition is higher, reaching about 1100 ° C. Such compressed air heated to a high temperature is optimally distributed by the dilution hole 9a and the aperture restrictor 24. The air that has passed through the aperture restrictor 24 is used for combustion.

【００３０】この燃焼用空気は、開口絞り装置２４を軸
方向から流入して一旦半径方向に偏向されて、旋回装置
２３に導かれ、ここを通過する間に旋回速度が付与され
る。この旋回装置２３は図４で示すように、固定ブロッ
ク２３ｂに対し接触及び離間移動する可動ブロック２３
ａを有し、この可動ブロック２３ａを移動操作すること
により空気導入スリット２３ｃは図４（Ａ）では０°、
図４（Ｂ）では５°、図４（Ｃ）では１０°のようにス
ワーラ設定角が可変調節制御される。This combustion air flows into the aperture throttle device 24 from the axial direction, is once deflected in the radial direction, is guided to the swivel device 23, and is swirled at a swirling speed while passing therethrough. As shown in FIG. 4, the swivel device 23 is a movable block 23 that moves in contact with and away from the fixed block 23b.
4A, the movable block 23a is moved to move the air introduction slit 23c to 0 ° in FIG.
The swirler setting angle is variably adjusted and controlled to be 5 ° in FIG. 4 (B) and 10 ° in FIG. 4 (C).

【００３１】旋回装置２３を出た旋回空気は、ルーバ２
７によって２分割された予蒸発予混合通路２１におい
て、ルーバ２７に沿って第１環状通路部１９ａで軸中心
に向かう半径方向に導かれ、徐々に半径方向から軸方向
に第２環状通路部１９ｂで偏向され、さらに、第３環状
通路部１９ｃでは燃料噴射弁２０の外周を旋回しつつ略
軸方向に向かう流れとなる。The swirling air exiting the swirling device 23 is supplied to the louver 2.
In the pre-evaporation premixing passage 21 divided into two by 7, the first annular passage portion 19a is guided in the radial direction toward the axial center along the louver 27, and gradually from the radial direction to the second annular passage portion 19b. In the third annular passage portion 19c, the flow is swirled around the outer periphery of the fuel injection valve 20 and flows substantially in the axial direction.

【００３２】前記スワーラ設定角が各位置に設定された
旋回装置２３を通過して、予蒸発予混合通路２１内を流
れる旋回空気の流動状況は図５（Ａ），（Ｂ），（Ｃ）
で示すように、空気導入スリット２３ｃの直後には後流
渦があるが、第２環状通路部１９ｂでは十分に安定した
旋回流が形成されて剥離等の２次流はない。このよう
に、安定した気流領域を形成するために第１環状通路部
１９ａが必須である。The flow conditions of the swirling air flowing through the pre-evaporation pre-mixing passage 21 after passing through the swirling device 23 in which the swirler set angle is set at each position are shown in FIGS. 5 (A), (B) and (C).
As shown by, although there is a wake vortex immediately after the air introduction slit 23c, a sufficiently stable swirl flow is formed in the second annular passage portion 19b and there is no secondary flow such as separation. As described above, the first annular passage portion 19a is essential to form a stable airflow region.

【００３３】一方、燃料噴射弁２０の燃料噴射孔２８か
ら噴射された燃料噴霧はルーバ２７の表面に衝突して、
噴霧と空気が共にルーバ２７の表面に沿って流れる。ル
ーバ２７の後端縁は第３環状通路部１９ｃまで延在して
おり、一方の空気流と、もう一方の噴霧混合気流とが第
３環状通路部１９ｃの上部で合流すると共に、さらに、
噴霧の蒸発と混合が予蒸発予混合通路２１の出口のスロ
ート部１１までの間に促進される。On the other hand, the fuel spray injected from the fuel injection hole 28 of the fuel injection valve 20 collides with the surface of the louver 27,
Both the spray and the air flow along the surface of the louver 27. The rear end edge of the louver 27 extends to the third annular passage portion 19c, and one air flow and the other spray mixed air flow merge at the upper portion of the third annular passage portion 19c, and further,
Evaporation and mixing of the spray is promoted up to the throat portion 11 at the exit of the pre-evaporation pre-mixing passage 21.

【００３４】第３環状通路部１９ｃ内の旋回流のため
に、内側の通路内壁には燃料噴霧が到達しにくく、一
方、第３環状通路部１９ｃの外側の通路と内壁にはルー
バ２７からの空気が層状に流れるため、燃料濃度が比較
的低くなる。すなわち、第３環状通路部１９ｃの両通路
内壁近傍の燃料濃度が低くなり、スロート部１１の内外
両壁間の空間では、予混合気の速度と濃度が略一様にな
る。Due to the swirling flow in the third annular passage portion 19c, it is difficult for the fuel spray to reach the inner wall of the inner passage. On the other hand, the outer passage and the inner wall of the third annular passage portion 19c are diverged from the louver 27. Since the air flows in layers, the fuel concentration becomes relatively low. That is, the fuel concentration near the inner walls of both passages of the third annular passage portion 19c becomes low, and the velocity and concentration of the premixed air become substantially uniform in the space between the inner and outer walls of the throat portion 11.

【００３５】前記多数の燃料噴射孔２８から噴射した燃
料がルーバ２７の表面で分散されると共に、旋回流で撹
拌されるために円周方向にも予混合気の濃度と速度が均
一になり、図６及び図７で示すように、スロート部１１
における燃料蒸気濃度と速度の分布が均一化される。Since the fuel injected from the large number of fuel injection holes 28 is dispersed on the surface of the louver 27 and is agitated by the swirling flow, the concentration and speed of the premixed gas become uniform in the circumferential direction. As shown in FIGS. 6 and 7, the throat portion 11
The distribution of fuel vapor concentration and velocity in is uniformed.

【００３６】また、予混合気の燃焼室６への流入速度が
スロート部１１で最大になるために燃焼室６内に形成さ
れる火炎は予蒸発予混合通路２１に伝播しないし、予蒸
発予混合通路２１内の流れがスムースで安定していて、
予混合気の滞在時間が短いため、予蒸発予混合通路２１
内では自着火が発生しない。Further, since the inflow velocity of the premixed gas into the combustion chamber 6 becomes maximum at the throat portion 11, the flame formed in the combustion chamber 6 does not propagate to the preevaporation premixing passage 21 and the preevaporation premixing passage 21 does not propagate. The flow in the mixing passage 21 is smooth and stable,
Since the stay time of the premixed gas is short, the preevaporation premixing passage 21
No self-ignition occurs inside.

【００３７】予混合気は旋回しながらスロート部１１か
ら燃焼室６に流入して、ブラフボディ２２と気流の旋回
作用により燃焼室６内には適度な循環領域が軸中央領域
に形成され、この渦で火炎が安定に保持される。また、
予混合気の燃焼室６への流入が軸対称であるため、作動
条件の変動によって影響されにくく、比較的火炎安定性
が高まる。The premixed gas flows into the combustion chamber 6 from the throat portion 11 while swirling, and an appropriate circulation region is formed in the combustion chamber 6 in the axial center region by the swirling action of the bluff body 22 and the air flow. The vortex keeps the flame stable. Also,
Since the inflow of the premixed gas into the combustion chamber 6 is axisymmetric, it is less affected by fluctuations in operating conditions, and flame stability is relatively enhanced.

【００３８】尚、ガスタービン始動時には熱交換器によ
る空気加熱がないため、燃焼器入口空気温度は低い。こ
のため、４００℃程度以上に温度が上昇するまではブラ
フボディ２２軸中心に配置した燃料噴射弁２０で燃料を
噴霧して、着火と起動等をする。Since the air is not heated by the heat exchanger when the gas turbine is started, the air temperature at the combustor inlet is low. Therefore, until the temperature rises to about 400 ° C. or higher, fuel is sprayed by the fuel injection valve 20 arranged at the axis of the bluff body 22 to ignite and start.

【００３９】本実施例では、噴射燃料流量に対応して、
燃焼用空気流量を開口絞り装置２４で調節し、それに連
動して旋回装置２３で旋回速度の強さを制御する。この
開口絞り装置２４と旋回装置２３は電気式あるいは油圧
アクチュエータで制御される構成である。In this embodiment, according to the injected fuel flow rate,
The flow rate of combustion air is adjusted by the aperture throttle device 24, and in conjunction with this, the swirl device 23 controls the strength of the swirl speed. The aperture stop device 24 and the turning device 23 are controlled by an electric or hydraulic actuator.

【００４０】[0040]

【発明の効果】以上のように本発明によると、燃焼用空
気が旋回装置で旋回速度を持って予蒸発予混合通路を通
過し、その領域に液体燃料を複数の燃料噴射孔から噴霧
供給するため燃料分散が一様になり、燃料噴霧が予蒸発
予混合通路を旋回するため噴霧の飛翔距離が延び、軸方
向距離を比較的短くしても十分な噴霧蒸発を達成するこ
とができる。As described above, according to the present invention, the combustion air passes through the pre-evaporation pre-mixing passage at the swirling device at a swirling speed, and liquid fuel is sprayed and supplied to the region through a plurality of fuel injection holes. Therefore, the fuel dispersion becomes uniform, the fuel spray swirls in the pre-evaporation pre-mixing passage, the flight distance of the spray is extended, and sufficient spray evaporation can be achieved even if the axial distance is relatively short.

【００４１】燃料噴射弁の外周に軸対称形状の環状予蒸
発予混合通路を形成することで燃焼器の全長が短縮さ
れ、かつ空間的な予混合気濃度と速度分布の均一化が得
られ、火炎安定性を向上し、燃焼室内温度分布が一様に
なり、その結果として、セラミックで構成する部品が単
純な形状となると共に、温度分布の一様化により耐久信
頼性が著しく向上する。By forming the axisymmetric annular pre-evaporation pre-mixing passage on the outer circumference of the fuel injection valve, the total length of the combustor is shortened, and the spatial pre-mixture concentration and velocity distribution are made uniform. The flame stability is improved and the temperature distribution in the combustion chamber is made uniform. As a result, the parts made of ceramics have a simple shape, and the uniform temperature distribution significantly improves the durability and reliability.

【００４２】燃焼用空気を旋回装置で旋回速度を付与し
た後に、軸対称形状の環状予蒸発予混合通路の第１環状
通路部の外周から軸中心方向に向かって流すことによ
り、流路面積の減少に伴い安定で一様な旋回空気流が生
成され、その後、さらに流路面積を半径方向に狭めると
共に、半径方向流に転向させる第２環状通路部及び第３
環状通路部を連接し、予蒸発通路軸中央に燃料噴射弁を
配置することにより、環状予蒸発予混合通路内の流れを
剥離や逆流等の２次流れのないスムースで安定な自由渦
的な旋回流にすることができる。After the swirling speed is given to the combustion air by the swirling device, the combustion air is caused to flow from the outer periphery of the first annular passage portion of the annular pre-evaporative premixing passage having the axisymmetric shape toward the axial center direction, whereby the flow passage area is reduced. A stable and uniform swirling airflow is generated with the decrease, and thereafter, the flow passage area is further narrowed in the radial direction, and the second annular passage portion and the third annular passage portion are turned to the radial flow.
By connecting the annular passages and arranging the fuel injection valve in the center of the pre-evaporation passage axis, the flow in the annular pre-evaporation pre-mixing passage is smooth and stable without any secondary flow such as separation or backflow. It can be swirling.

【００４３】この安定な渦流が形成されている第２環状
通路部あるいは第３環状通路部の軸中央に配置した燃料
噴射弁の複数の燃料噴射孔から液体燃料を噴射させる
と、渦流のせん断力により液体燃料の微粒化が促進され
ると共に、遠心力により大きな燃料噴霧ほど外周方向に
分散されやすく、最大粒径の噴霧は環状予蒸発予混合通
路の外側壁面に集中して、その領域で蒸発が促進される
効果がある。このため、通過時間が数ｍｍ秒と短い予蒸
発予混合通路距離であっても十分な予蒸発予混合が得ら
れる。When liquid fuel is injected from a plurality of fuel injection holes of the fuel injection valve arranged in the axial center of the second annular passage portion or the third annular passage portion where the stable vortex is formed, the shear force of the vortex is generated. The atomization of the liquid fuel is promoted by the centrifugal force, and the larger the fuel spray is, the more easily it is dispersed in the outer peripheral direction by the centrifugal force. Has the effect of being promoted. Therefore, sufficient pre-evaporative pre-mixing can be obtained even with a short pre-evaporative pre-mixing passage distance of several mm seconds.

【００４４】軸対称形状の環状予蒸発予混合通路内の中
央領域にルーバを設け、このルーバの表面に対向する位
置に燃料噴射孔を配置して燃料噴霧を衝突させることに
より、燃料噴霧の分散と微粒化が著しく促進され、ま
た、ルーバの片方の表面に沿っては燃焼用空気が流れて
ルーバの後端縁で燃料空気予混合と空気流が合流するよ
うルーバの後端縁が第３環状通路部に位置された構成に
より、燃焼用空気が２分割され、環状通路の外側内壁面
に空気流が形成されて、この領域に燃料噴霧が集中して
濃度が平均より高くなりすぎるのを防止することができ
る。また、ルーバの両表面の速度差で空気流に乱れが生
成され、その領域に燃料噴霧を噴射することで噴霧の蒸
発と混合が促進される。A louver is provided in the central area of the annular pre-evaporation premixing passage having an axially symmetrical shape, and fuel injection holes are arranged at positions facing the surface of the louver to collide the fuel spray with each other, thereby dispersing the fuel spray. And the rear edge of the louver has a third edge so that the combustion air flows along one surface of the louver and the fuel-air premixing and the air flow merge at the rear edge of the louver. Due to the configuration located in the annular passage portion, the combustion air is divided into two, an air flow is formed on the outer inner wall surface of the annular passage, and the fuel spray is concentrated in this region and the concentration becomes too high than the average. Can be prevented. Further, turbulence is generated in the air flow due to the speed difference between the two surfaces of the louver, and the fuel spray is injected into the area, whereby evaporation and mixing of the spray are promoted.

【００４５】上記の効果によって、従来の予蒸発予混合
燃焼器で必要とされていた噴霧蒸発時間の短縮と十分な
予蒸発予混合性能が実現でき、通路距離を著しく短小化
すると共に、予蒸発予混合通路への逆火や自着火が抑止
できる。Due to the above effects, the spray evaporation time and the sufficient pre-evaporation pre-mixing performance required in the conventional pre-evaporation pre-mixing combustor can be realized, and the passage distance can be remarkably shortened and the pre-evaporation can be performed. It is possible to suppress backfire and self-ignition to the premix passage.

【００４６】予蒸発予混合通路の通路面積を漸次減少さ
せることで予混合気を加速すると共に、予蒸発予混合通
路のスロート部、すなわち、燃焼室流入部の直前で最小
面積にすることで、予蒸発予混合通路内の流れの剥離を
防止し、燃焼室内の火炎が予蒸発予混合通路に伝播した
り、剥離領域で混合気が自着火したりする逆火を抑止す
る。By gradually reducing the passage area of the pre-evaporation pre-mixing passage to accelerate the pre-mixed gas, and at the minimum area immediately before the throat portion of the pre-evaporation pre-mixing passage, that is, the combustion chamber inflow portion, The separation of the flow in the pre-evaporation pre-mixing passage is prevented, and the backfire in which the flame in the combustion chamber propagates to the pre-evaporation pre-mixing passage and the air-fuel mixture self-ignites in the separation region is suppressed.

【００４７】予蒸発予混合通路の第３環状通路部をラッ
パ状に開口することにより、燃焼室に混合気が流入した
時に比較的大きな循環渦領域が燃焼室中央領域に形成さ
れるため、火炎を燃焼室内に安定に形成することができ
る。By opening the third annular passage portion of the pre-evaporation pre-mixing passage in the shape of a trumpet, a relatively large circulation vortex region is formed in the central region of the combustion chamber when the air-fuel mixture flows into the combustion chamber. Can be stably formed in the combustion chamber.

【００４８】旋回装置の上流に燃焼用空気の流量を調節
する開口絞り装置を配置し、空気流量に連動して旋回装
置による燃焼用空気に付与する旋回速度を可変にする機
構を備えているため、燃焼用空気を絞り制御することに
より旋回装置で予混合気の旋回強さ（旋回速度）を最適
に制御させて火炎の安定を確保することができる。An aperture throttle device for adjusting the flow rate of combustion air is arranged upstream of the swirl device, and a mechanism for varying the swirl speed given to the combustion air by the swirl device in association with the air flow rate is provided. By controlling the combustion air by throttling, the swirl device can optimally control the swirl strength (swirl speed) of the premixed air to ensure the stability of the flame.

【図面の簡単な説明】[Brief description of drawings]

【図１】本発明による予蒸発予混合燃焼器の断面図FIG. 1 is a cross-sectional view of a pre-evaporative premix combustor according to the present invention.

【図２】本発明の要部拡大断面図FIG. 2 is an enlarged sectional view of an essential part of the present invention.

【図３】本発明の他の実施例による予蒸発予混合燃焼器
の断面図FIG. 3 is a cross-sectional view of a pre-evaporative pre-mix combustor according to another embodiment of the present invention.

【図４】旋回装置の空気導入スリットの各設定角状態を
示す断面図FIG. 4 is a cross-sectional view showing each set angle state of the air introduction slit of the turning device.

【図５】旋回装置作動時における予蒸発予混合通路内の
速度分布図FIG. 5 is a velocity distribution diagram in the pre-evaporation pre-mixing passage when the swivel device is operating.

【図６】予蒸発予混合通路内の燃料濃度分布図FIG. 6 is a fuel concentration distribution map in the pre-evaporation pre-mixing passage.

【図７】予蒸発予混合通路内の速度分布図FIG. 7 Velocity distribution map in pre-evaporation pre-mixing passage

【図８】従来の予蒸発予混合燃焼器の断面図FIG. 8 is a sectional view of a conventional pre-evaporation pre-mixing combustor.

【符号の説明】[Explanation of symbols]

６ 燃焼室 ７ エクステンションライナ ８ ゾーンセパレータ ９ 希釈ライナー １０ 支持部材 １１ スロート部 １９ａ 第１環状通路部 １９ｂ 第２環状通路部 １９ｃ 第３環状通路部 ２０ 燃料噴射弁 ２１ 予蒸発予混合通路 ２２ ブラフボディ ２３ 旋回装置 ２３ａ 可動ブロック ２３ｂ 固定ブロック ２３ｃ 空気導入スリット ２４ 開口絞り装置 ２５ 旋回装置用操作軸 ２６ 開口絞り装置用操作軸 ２７ ルーバ ２８ 燃料噴射孔 6 Combustion Chamber 7 Extension Liner 8 Zone Separator 9 Dilution Liner 10 Supporting Member 11 Throat 19a First Annular Passage 19b Second Annular Passage 19c Third Annular Passage 20 Fuel Injection Valve 21 Pre-evaporation Premixing Passage 22 Bluff Body 23 Swivel device 23a Movable block 23b Fixed block 23c Air introduction slit 24 Aperture throttle device 25 Swivel device operation shaft 26 Aperture throttle device operation shaft 27 Louver 28 Fuel injection hole

Claims (5)

【特許請求の範囲】[Claims] 【請求項１】 燃料噴射弁と、前記燃料噴射弁から噴射
した燃料を蒸発させつつ、燃焼用空気と混合する予蒸発
予混合通路とを備え、前記予蒸発予混合通路の下流に燃
焼室を連接する予蒸発予混合燃焼器であって、前記予蒸
発予混合通路の上流には燃焼用空気に旋回速度を付与す
る旋回装置を設け、前記燃料噴射弁を前記予蒸発予混合
通路の軸中心領域に配置すると共に、その外周に前記予
蒸発予混合通路を環状の軸対称形状に配置し、前記旋回
装置に連接した前記予蒸発予混合通路を、旋回速度を付
与した燃焼用空気を軸中心方向に流す第１環状通路部
と、その下流に徐々に通路面積を減少させつつ軸中心に
向かう半径方向から前記燃焼室の軸方向に空気を転向さ
せる第２環状通路部および軸方向に混合気を流す第３環
状通路部とを備え、前記環状の予蒸発予混合通路の内壁
に設けた複数の燃料噴射孔を持つ前記燃料噴射弁から燃
料を前記予蒸発予混合通路内に噴射する構成にしたこと
を特徴とする予蒸発予混合燃焼器。1. A fuel injection valve and a pre-evaporation pre-mixing passage that mixes with fuel air while evaporating the fuel injected from the fuel injection valve, and a combustion chamber is provided downstream of the pre-evaporation pre-mixing passage. A pre-evaporation pre-mixing combustor connected to the pre-evaporation pre-mixing passage, wherein a swirl device is provided upstream of the pre-evaporation pre-mixing passage to impart a swirling speed to the combustion air. The pre-evaporation pre-mixing passage is arranged in an area, and the pre-evaporation pre-mixing passage is arranged in an annular axisymmetric shape on the outer periphery thereof, and the pre-evaporation pre-mixing passage connected to the swirl device is centered on the combustion air having a swirling speed A first annular passage portion that flows in the direction, a second annular passage portion that diverts air in the axial direction of the combustion chamber from the radial direction toward the axial center while gradually reducing the passage area downstream thereof, and the air-fuel mixture in the axial direction. And a third annular passage portion through which the Pre-evaporation pre-mixing combustion characterized in that fuel is injected into the pre-evaporation pre-mixing passage from the fuel injection valve having a plurality of fuel injection holes provided in the inner wall of the annular pre-evaporation pre-mixing passage. vessel. 【請求項２】 前記予蒸発予混合通路の中央領域に環状
のルーバを設けると共に、前記燃料噴射弁の燃料噴射孔
を前記ルーバの表面に対向する位置に配置し、前記ルー
バの片方の表面に沿っては燃焼用空気が流れて前記ルー
バの後端縁で燃料空気混合気流と空気流が合流するよう
に配置して、前記ルーバの後端縁が前記予蒸発予混合通
路の出口より上流位置にある構成を特徴とする前記請求
項１記載の予蒸発予混合燃焼器。2. An annular louver is provided in a central region of the pre-evaporative premixing passage, and fuel injection holes of the fuel injection valve are arranged at positions facing the surface of the louver, and one surface of the louver is provided. Combustion air flows along the louver so that the fuel-air mixture flow and the air flow merge at the rear edge of the louver, and the rear edge of the louver is located upstream of the outlet of the pre-evaporation premix passage. The pre-evaporative premix combustor according to claim 1, characterized in that 【請求項３】 前記予蒸発予混合通路の通路面積を上流
から漸次減少させると共に、前記燃焼室の直前で通路面
積が最小となるスロート部を配置することを特徴とする
前記請求項１または２記載の少なくともいずれかの予蒸
発予混合燃焼器。3. The throat portion having a minimum passage area immediately before the combustion chamber is arranged while the passage area of the pre-evaporative premix passage is gradually reduced from the upstream side. Prevaporized premixed combustor according to at least one of the claims. 【請求項４】 通路面積を漸次減少させる前記予蒸発予
混合通路が、前記燃焼室にラッパ状に開口することを特
徴とする前記請求項１，２ないし３記載の少なくともい
ずれかの予蒸発予混合燃焼器。4. The pre-evaporation pre-mixing passage according to claim 1, wherein the pre-evaporation pre-mixing passage for gradually reducing the passage area opens into the combustion chamber in a trumpet shape. Mixed combustor. 【請求項５】 前記旋回装置の上流には燃焼用空気の流
量を調整する開口絞り装置を配置し、燃焼用空気流量に
連動して旋回装置による燃焼用空気に付与する旋回速度
を可変にする機構を備えたことを特徴とする前記請求項
１，２，３，ないし４記載の少なくともいずれかの予蒸
発予混合燃焼器。5. An aperture throttle device for adjusting a flow rate of combustion air is arranged upstream of the swirl device, and a swirl speed given to the combustion air by the swirl device is variable in association with a flow rate of the combustion air. The pre-evaporative pre-mixing combustor according to any one of claims 1, 2, 3, and 4, further comprising a mechanism.
JP15175494A 1994-06-10 1994-06-10 Pre-evaporation premix combustor Expired - Fee Related JP2666117B2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP15175494A JP2666117B2 (en) 1994-06-10 1994-06-10 Pre-evaporation premix combustor

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP15175494A JP2666117B2 (en) 1994-06-10 1994-06-10 Pre-evaporation premix combustor

Publications (2)

Publication Number Publication Date
JPH07332671A true JPH07332671A (en) 1995-12-22
JP2666117B2 JP2666117B2 (en) 1997-10-22

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ID=15525569

Family Applications (1)

Application Number Title Priority Date Filing Date
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Country Link
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