JPS5951153A - Premixing device for gasious fuel - Google Patents
Premixing device for gasious fuelInfo
- Publication number
- JPS5951153A JPS5951153A JP57163541A JP16354182A JPS5951153A JP S5951153 A JPS5951153 A JP S5951153A JP 57163541 A JP57163541 A JP 57163541A JP 16354182 A JP16354182 A JP 16354182A JP S5951153 A JPS5951153 A JP S5951153A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- gas
- air
- combustion
- gas fuel
- 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
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02M—SUPPLYING COMBUSTION ENGINES IN GENERAL WITH COMBUSTIBLE MIXTURES OR CONSTITUENTS THEREOF
- F02M21/00—Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form
- F02M21/02—Apparatus for supplying engines with non-liquid fuels, e.g. gaseous fuels stored in liquid form for gaseous fuels
- F02M21/04—Gas-air mixing apparatus
- F02M21/042—Mixer comprising a plurality of bores or flow passages
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B43/00—Engines characterised by operating on gaseous fuels; Plants including such engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/10—Internal combustion engine [ICE] based vehicles
- Y02T10/30—Use of alternative fuels, e.g. biofuels
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Oil, Petroleum & Natural Gas (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Electrical Control Of Air Or Fuel Supplied To Internal-Combustion Engine (AREA)
Abstract
Description
【発明の詳細な説明】
〔発明の技術分野〕
本発明はガス燃料燃焼器の噴射ガス燃料と燃焼用空気を
混合１−るガス燃料予混合装置に係シ、特にガスタービ
ン等のリッチ・リーン型ガス燃料２段燃焼器の、旋回器
を備えたガス燃料予混合装置に関する。Detailed Description of the Invention [Technical Field of the Invention] The present invention relates to a gas fuel premixing device for mixing injected gas fuel and combustion air in a gas fuel combustor, and particularly relates to a gas fuel premixing device for mixing injection gas fuel and combustion air in a gas fuel combustor, and particularly relates to a gas fuel premixing device for mixing injected gas fuel and combustion air in a gas fuel combustor. The present invention relates to a gas fuel premixing device with a swirler for a two-stage gas fuel combustor.
最近、燃焼器等の排気中に含有する窒素酸化物の規制が
強化されている。そのため前記排気中に含有する窒素酸
化物の量が低減される燃焼技術の開発が要求されて込る
。Recently, regulations on nitrogen oxides contained in exhaust gas from combustors and the like have been tightened. Therefore, there is a need to develop a combustion technology that reduces the amount of nitrogen oxides contained in the exhaust gas.
一般に、燃焼器の窒素酸化物の発生反応はその燃焼温度
に対し指数関数的な関係があり、燃焼温度を下げること
によって窒素酸化物の発生反応を抑制し、排気中に含有
する窒素酸化物の量を低減させるようにしてｂる。Generally, the reaction of generating nitrogen oxides in a combustor has an exponential relationship with its combustion temperature, and by lowering the combustion temperature, the reaction of generating nitrogen oxides can be suppressed, and the b in order to reduce the amount.
そして、燃焼器内へ水または蒸気を噴射することＫよシ
燃焼温度を低下させて排気中に含有する窒素酸化物の量
を低減させることが行われているが、窒素酸化物の量を
低減させる能力には限界があり、また、ガスタービンの
効率が低下する欠点もあった。The amount of nitrogen oxides contained in the exhaust gas has been reduced by injecting water or steam into the combustor to lower the combustion temperature. There was a limit to the ability to do so, and there was also the drawback that the efficiency of the gas turbine was reduced.
そのため、燃焼器内に２箇所の燃焼室全形成した２段燃
焼器で燃料ｔ−１次燃焼および２次燃焼させ、燃焼温度
を低下させて排気中に含有する窒素酸化物の量を低減さ
せることが行われている。Therefore, in a two-stage combustor that has two combustion chambers in the combustor, primary combustion and secondary combustion of the fuel are performed to lower the combustion temperature and reduce the amount of nitrogen oxides contained in the exhaust gas. things are being done.
それは、前記２段燃焼器による燃料の２段燃焼では、理
論当量比に対して燃料過剰、即ちフューエル・リッチま
たは、空気過剰即ち、フューエル。In the two-stage combustion of fuel in the two-stage combustor, there is an excess of fuel, ie, fuel rich, or an excess of air, ie, fuel compared to the stoichiometric equivalence ratio.
リーンで燃焼させると、理論当量比での燃焼に比べて燃
焼温度が低下するからである。This is because lean combustion lowers the combustion temperature compared to combustion at a stoichiometric equivalent ratio.
前記２段燃焼器による２段燃焼には大きく分けて、リッ
チ・リーン型およびリーン・リーン型の２つがある。前
記リッチ・リーン型は第１段燃焼室ではフューエル・リ
ッチ、第２段燃焼室ではフューエル・リーンで燃焼させ
るものであり、前記リーン・リーン型Ｖｉ第１段、第２
段燃焼室でともにフューエル・リーンで燃焼させるもの
である。The two-stage combustion by the two-stage combustor can be roughly divided into two types: rich-lean type and lean-lean type. The rich-lean type burns fuel rich in the first stage combustion chamber and fuel lean in the second stage combustion chamber, and the lean-lean type Vi first stage and second stage
Both are fuel-lean combustion in staged combustion chambers.
第１図は、ガスタービンのリッチ・リーン型２段燃焼器
１の断面図を示すものであυ、燃焼器外筒２の端部の側
板３には燃料供給管４が接続されたガス燃料予混介装＃
５が取付けられている。FIG. 1 shows a cross-sectional view of a rich-lean two-stage combustor 1 of a gas turbine, in which a fuel supply pipe 4 is connected to a side plate 3 at the end of a combustor outer cylinder 2. Premix #
5 is installed.
また、前記燃焼器外筒２の内壁との間に環状の空間６ｆ
ｆ：置して第１段燃焼室７および第２段燃焼室８が設け
られている。そして前記第１段燃焼室７は前記ガス燃料
予混合装置５に接続され、さらに、前記第１段燃ｌ！ｉ
＠室７は、第２段燃焼用空気入孔９を有する縮流部１０
全通して第２段燃焼室８に接続されている。この第２段
燃焼室８は希釈空気流入孔１１が設けられ、トランジシ
ョン・ピース１２に接続されている。Further, an annular space 6f is formed between the inner wall of the combustor outer cylinder 2 and the inner wall of the combustor outer cylinder 2.
f: A first stage combustion chamber 7 and a second stage combustion chamber 8 are provided. The first stage combustion chamber 7 is connected to the gas fuel premixing device 5, and the first stage combustion chamber 7 is further connected to the first stage combustion chamber 7. i
@ Chamber 7 is a contraction part 10 having air inlet holes 9 for second stage combustion.
It is connected to the second stage combustion chamber 8 throughout. This second stage combustion chamber 8 is provided with a dilution air inlet 11 and connected to a transition piece 12 .
前記の２段燃焼器１において、圧縮機から送られた空気
１３は前記燃焼器外筒２と前記第１段燃焼室７および第
２段燃焼室８との間の前記環状の壁間６を流れる。In the two-stage combustor 1, the air 13 sent from the compressor passes through the annular wall space 6 between the combustor outer cylinder 2 and the first-stage combustion chamber 7 and second-stage combustion chamber 8. flows.
そｉ−て、前記燃料供給管４から供給されるガス燃料と
ともに前記空気１３は前記ガス燃料予混合装置５を；ｊ
ｆ３ して混合され前記第１段燃焼室７内に流入する。Then, the air 13 together with the gas fuel supplied from the fuel supply pipe 4 passes through the gas fuel premixing device 5;
f3 and are mixed and flow into the first stage combustion chamber 7.
このとき、前記第１段燃焼室７では、前記ガス燃料予混
合装置５全通して流入する１次燃焼用空気１４のみのフ
ューエル・リッチで燃焼させる。At this time, in the first-stage combustion chamber 7, combustion is performed in a fuel-rich manner using only the primary combustion air 14 that flows through the entire gas-fuel premixing device 5.
つぎに、前記縮流部１０では、前記第１段燃焼￥７内で
の未燃焼燃料を含む燃焼ガス１５の流速を増大させて前
記第２段燃焼用空気流入口９から２次燃焼用空気１６を
流入させて混合させる。それによりて、急激に７ユーエ
ル・υ−ンの状態にし、第２段燃焼室８で燃焼させる。Next, in the flow contraction section 10, the flow velocity of the combustion gas 15 containing unburned fuel in the first stage combustion ¥7 is increased, and the second combustion air is supplied from the second stage combustion air inlet 9. 16 is introduced and mixed. As a result, the fuel is suddenly brought into a state of 7 yuel/υ-n, and is combusted in the second stage combustion chamber 8.
この燃焼ガス１７に前記希釈空気流入孔１１から希釈空
気１８を流入させて混合し、所定温度の燃焼ガス１９に
して前記トランジション・ピース１２に送り出される。Dilution air 18 is introduced into the combustion gas 17 through the dilution air inflow hole 11 and mixed with the combustion gas 17 to form a combustion gas 19 at a predetermined temperature and sent to the transition piece 12 .
従来のリッチ・リーン型ガス燃料２段燃焼器のｍ１段燃
焼室へ燃料供給管からガス燃料を流入させる旋回器を備
えたガス燃料予混合装置は第２図および第３図におりて
、ガス燃料２１ヲ供給する燃料供給管４と旋回器２２と
前記燃焼器外筒２の側板３へ数句けるための取付７ラン
ジ囚とからなり、前記旋回器２２はガス燃料噴射孔２４
が設けられた内輪５と、旋回羽根２６と、前記第１段燃
焼室７の壁との嵌合部２７を有する前記旋回器２２の外
輪あとから形成されている。A gas fuel premixing device equipped with a swirler that allows gas fuel to flow into the m1 stage combustion chamber of a conventional rich-lean type gas fuel two-stage combustor from a fuel supply pipe is shown in Figures 2 and 3. It consists of a fuel supply pipe 4 for supplying fuel 21, a swirler 22, and a mounting 7 lunge for connecting the side plate 3 of the combustor outer cylinder 2, and the swirler 22 is connected to the gas fuel injection hole 24.
The inner ring 5 is formed from the outer ring of the swirler 22, which has an inner ring 5 provided with a swirler, a swirler vane 26, and a fitting portion 27 with the wall of the first stage combustion chamber 7.
したがって、前記ガス燃料供給管４から供給されるガス
燃料２１は前記旋回器２２の内輪部に設けられたＭ’ｉ
Ｊ記ガス燃Ｎ：＝’）噴射ロスから、前記旋回羽根部の
間に噴出される。この噴出されたガス燃料穴は前記圧縮
機から送られて流入した１次燃焼用空気１４と旋回羽根
あの間で攪拌混合され、フューエル・リッチの燃料・空
気混合気３０となる。そして、前記燃料・空気混合負加
は旋回方向速度成分金持ち、旋回羽根後流に循環流れを
形成して第１段燃焼室７に流入する。Therefore, the gas fuel 21 supplied from the gas fuel supply pipe 4 is
J gas fuel N:=') is ejected between the swirling vanes due to injection loss. This ejected gas fuel hole is agitated and mixed between the swirling vanes and the primary combustion air 14 that has flowed in from the compressor to form a fuel-rich fuel/air mixture 30. The fuel/air mixture has a velocity component in the swirling direction, and forms a circulating flow behind the swirling blades, and flows into the first stage combustion chamber 7.
前記のような燃料穴と空気１４を混合するガス燃料予混
介装＠５は、燃料の噴射から第１段燃焼室７へ燃料・空
気混合負加が流入するまでの燃料２９と空気１４の混合
が行われる区間が短かく形成されている。そのため、フ
ューエル・リッチの燃料・空気混合負加が十分均一な燃
料濃度分布になる１で予混合がなされなりで第１段燃焼
室７に流入する。The gas fuel premixing device @ 5 that mixes the fuel hole and air 14 as described above mixes the fuel 29 and air 14 from fuel injection until the fuel/air mixture flows into the first stage combustion chamber 7. The section where mixing is performed is short. Therefore, when the fuel-rich fuel/air mixture has a sufficiently uniform fuel concentration distribution, premixing is performed and the fuel flows into the first stage combustion chamber 7.
したがって、局所的に燃料濃度が理論当量比の領域が在
存し、燃焼温度が低下せず、前記排気中に含有する窒素
酸化物の量が低減されなめ欠点があった。Therefore, there exists a local region where the fuel concentration is at the stoichiometric equivalence ratio, and the combustion temperature does not decrease, resulting in a reduction in the amount of nitrogen oxides contained in the exhaust gas.
本発明は、前述した従来のものにおける欠点を除去し、
前記リッチ・リーン型ガス燃料２段燃焼器の排気中に含
有する窒素酸化物の量が低減されたガス燃料予混合装置
を提供することを目的とする。The present invention eliminates the drawbacks of the conventional ones mentioned above,
It is an object of the present invention to provide a gas fuel premixing device in which the amount of nitrogen oxides contained in the exhaust gas of the rich-lean type gas fuel two-stage combustor is reduced.
前述した目的は、本発明によれば、リッチ・リーン型ガ
ス燃料２段燃焼器の第１段燃焼室へ燃料供給管からガス
燃料を流入させる旋回器を備えたガス燃料予混合装置に
おりて、前記燃料供給管と前記旋回器との間に燃料・空
気予混合室を設け、この燃料・空気予混合室に多数の燃
料噴射孔を有する燃料噴射器を備えて、ガス燃料と燃焼
用空気の混合が十分均一になされるようにしたことによ
シ達成される。The above object, according to the present invention, provides a gas fuel premixing device equipped with a swirler that allows gas fuel to flow into the first stage combustion chamber of a rich-lean type gas fuel two-stage combustor from a fuel supply pipe. , a fuel/air premixing chamber is provided between the fuel supply pipe and the swirler, and the fuel/air premixing chamber is equipped with a fuel injector having a large number of fuel injection holes to inject gaseous fuel and combustion air. This is achieved by ensuring that the mixture is sufficiently uniform.
以下、本発明を図面に示す実施例により説明する。なお
、前述した従来のものと同一の構成については、図面中
に同一の符号を付し、その説明は省略する。The present invention will be explained below with reference to embodiments shown in the drawings. Note that the same components as those of the conventional device described above are denoted by the same reference numerals in the drawings, and the explanation thereof will be omitted.
本発明の一実施例によれば、第４図および第５図に示す
ように、前記燃料供給管４と前記旋回器〃との間に、燃
料・空気予混合室３１が設けられている。この予混合室
３１は前記燃料供給管４に近い側に第６図に示す導入旋
回羽根３２で区画された１次燃線用空気導入口３３を備
えている。そして、前記予混合室３１には、第７図に外
観を示すような多数の燃料噴射孔３４を有する球状の燃
料噴射器３５が備えられている。この燃料噴射器３５は
前記燃料供給管４に接続されている。According to one embodiment of the present invention, as shown in FIGS. 4 and 5, a fuel/air premixing chamber 31 is provided between the fuel supply pipe 4 and the swirler. This premixing chamber 31 is provided with a primary combustion line air inlet 33 partitioned by an inlet swirl vane 32 shown in FIG. 6 on the side closer to the fuel supply pipe 4. The premixing chamber 31 is equipped with a spherical fuel injector 35 having a large number of fuel injection holes 34 as shown in FIG. This fuel injector 35 is connected to the fuel supply pipe 4.
このように構成されたガス燃料予混合装置５によれば、
前記燃料供給管４から前記球状の燃料噴射器３５へ送ら
れたガス燃料２１は多数の前記燃料噴射孔３４から前記
燃料・空気予混合室３１内に噴射される。この噴射され
たガス燃料３６は、前記予混合室３１の全体にわたり放
射状に噴射されるので、前記１次燃焼用空気１４との混
合が促進される。甘た前記１次燃焼用空気１４は前記導
入旋回羽根３２によって旋回方向速度成分を持つので、
燃料・空気混合気は前記予混合室３１で滞溜する時間が
長くなり燃料３１と空気１４の予混合はさらに促進され
る。そして、十分混合させた後に、このフューエル・リ
ッチの燃料・空気混合気（資）は旋回器２２の旋回羽根
２６でさらに十分均一になるように攪拌混合させ第１段
燃焼室７へ流入させる。According to the gas fuel premixing device 5 configured in this way,
The gaseous fuel 21 sent from the fuel supply pipe 4 to the spherical fuel injector 35 is injected into the fuel/air premixing chamber 31 from the plurality of fuel injection holes 34. Since the injected gas fuel 36 is radially injected throughout the premixing chamber 31, mixing with the primary combustion air 14 is promoted. Since the sweet primary combustion air 14 has a velocity component in the swirling direction due to the introduction swirling vane 32,
The fuel/air mixture stays in the premixing chamber 31 for a longer time, and the premixing of the fuel 31 and the air 14 is further promoted. After sufficient mixing, this fuel-rich fuel/air mixture is stirred and mixed by the swirling blades 26 of the swirler 22 so as to be sufficiently uniform, and then flows into the first stage combustion chamber 7.
したがって、第１段燃焼室７におけるフューエル・リッ
チの燃料・空気混合気１５は十分均一な燃料濃度分布に
なるので、燃焼温度が低下し、排気中に含有する窒素酸
化物の量が低減される。Therefore, the fuel-rich fuel/air mixture 15 in the first stage combustion chamber 7 has a sufficiently uniform fuel concentration distribution, which lowers the combustion temperature and reduces the amount of nitrogen oxides contained in the exhaust gas. .
なお、前記燃料噴射器あけ前記一実施例の球状のものに
限定されることなく第８図に示す円環状のもの等種々の
変形が可能である。It should be noted that the fuel injector opening is not limited to the spherical shape of the above embodiment, but can be modified in various ways, such as an annular shape as shown in FIG.
以上胛、明したように本発明のガス燃料予混合装置は、
リッチ・リーン型ガス燃料２段燃焼器の第１段燃焼室へ
燃料供給管からガス燃料を流入させる旋回器を備えたガ
ス燃料予混合装置において、前記燃料供給管と前記旋回
器との間に燃料・空気予混合室を設け、この燃料・空気
予混合室に多数の燃料噴射孔を有する燃料噴射器を備え
たので、前記リッチ・リーン型ガス燃料２段燃焼器の排
気中に含有する窒素酸化物の量が低減される効果がある
。As explained above, the gas fuel premixing device of the present invention includes:
In a gas fuel premixing device equipped with a swirler that causes gas fuel to flow into the first stage combustion chamber of a rich-lean type gas fuel two-stage combustor from a fuel supply pipe, there is provided a gas fuel premixing device between the fuel supply pipe and the swirler. Since a fuel/air premixing chamber is provided and a fuel injector having a large number of fuel injection holes is provided in the fuel/air premixing chamber, nitrogen contained in the exhaust gas of the rich/lean type gas fuel two-stage combustor is This has the effect of reducing the amount of oxides.
第１図はガスタービン等のリッチ・リーン２！！１．２
段燃焼器の縦断面図、第２図は従来のガス燃料予混合装
置の縦断面図、第３図は第２図の中の旋回器のみのＡ−
Ａ方向の正面図、第４図は本発明のガス燃料予混合装置
の一実施例の縦断面図、第５図は第４図の中の旋回器の
みのＢ−Ｂ方向の正面図、第６図は第４図のＣ−Ｃ断面
図、第７図は本発明のガス燃料予混合装置の燃料噴射器
の一実施例の側面図、第８図は本発明のガス燃料予混合
装置の燃料噴射器の他の実施例の側面図である。
１・・・リッチ・リーン型２段燃焼器、２・・・燃焼器
外筒、３・・・側板、４・・・燃料供給管、５・・・ガ
ス燃料予混合装置、６・・・環状の空間、７・・・第１
段燃焼室、８・・・第２段燃焼室、９・・・第２段燃焼
用空気流入孔、１０・・・縮流部、１１・・・希釈空気
流入孔、１２・・・トランジション・ピース、１３・・
・空気、′１４・・・１次燃焼用空気、１５・・・燃焼
ガス、１６・・・２次燃焼用空気、１７・・・燃焼ガス
、１８・・・希釈空気、１９・・・所定温度の燃焼ガス
、加・・・点火器、２１・・・ガス燃料、２２・・・旋
回器、ｎ・・・取付フランジ、冴・・・ガス燃料噴射孔
、５・・・内輪、２６・・・旋回羽根、２７・・・嵌合
部、公・・・外輪、２９・・・ガス燃料、３０・・・燃
料・空気混合気、３１・・・燃料・空気予混合室、３２
・・・導入旋回羽根、３３・・・空気導入口、３４・・
・燃料噴射孔、あ・・・燃料噴射器、３６・・・ガス燃
料、３７・・・予混合室壁。
出願人代理人 猪 股 清
第１図
第２図
第３図
７
第４図
＄６図
２Figure 1 shows Rich Lean 2 for gas turbines, etc. ! 1.2
A vertical cross-sectional view of a stage combustor, FIG. 2 is a vertical cross-sectional view of a conventional gas fuel premixing device, and FIG. 3 is a vertical cross-sectional view of a conventional gas fuel premixing device.
4 is a longitudinal sectional view of one embodiment of the gas fuel premixing device of the present invention; FIG. 5 is a front view of only the swirler in FIG. 4 in the BB direction; 6 is a sectional view taken along the line C-C in FIG. 4, FIG. 7 is a side view of an embodiment of the fuel injector of the gas fuel premixing device of the present invention, and FIG. 8 is a cross-sectional view of the gas fuel premixing device of the present invention. FIG. 3 is a side view of another embodiment of a fuel injector. DESCRIPTION OF SYMBOLS 1...Rich-lean type two-stage combustor, 2...Combustor outer cylinder, 3...Side plate, 4...Fuel supply pipe, 5...Gas fuel premixing device, 6... Annular space, 7...1st
Stage combustion chamber, 8... Second stage combustion chamber, 9... Second stage combustion air inflow hole, 10... Contraction section, 11... Dilution air inflow hole, 12... Transition. Peace, 13...
・Air, '14... Air for primary combustion, 15... Combustion gas, 16... Air for secondary combustion, 17... Combustion gas, 18... Dilution air, 19... Predetermined Combustion gas of temperature, addition...Igniter, 21...Gas fuel, 22...Swivel, n...Mounting flange, Sae...Gas fuel injection hole, 5...Inner ring, 26... ...Swirling vane, 27... Fitting part, public... Outer ring, 29... Gas fuel, 30... Fuel/air mixture, 31... Fuel/air premixing chamber, 32
...Introduction swirl vane, 33...Air introduction port, 34...
・Fuel injection hole, ah...fuel injector, 36...gas fuel, 37...premixing chamber wall. Applicant's agent Kiyoshi Inomata Figure 1 Figure 2 Figure 3 Figure 7 Figure 4 $6 Figure 2
Claims (1)
燃料供給管からガス燃料を流入させる旋回器を備えたガ
ス燃料予混合装置におりて、前記燃料供給管と前記旋回
器との間に燃料空気予混合室を設け、この燃料空気予混
合室に多数の燃料噴射孔を有する燃料噴射器を備えたこ
とを特徴とするガス燃料予混合装置。In a gas fuel premixing device equipped with a swirler that allows gas fuel to flow into the first stage combustion chamber of a rich-lean type gas fuel two-stage combustor from a fuel supply pipe, the fuel supply pipe and the swirler are connected to each other. A gas-fuel premixing device characterized in that a fuel-air premixing chamber is provided between the fuel and air premixing chambers, and the fuel-air premixing chamber is equipped with a fuel injector having a large number of fuel injection holes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57163541A JPS5951153A (en) | 1982-09-20 | 1982-09-20 | Premixing device for gasious fuel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP57163541A JPS5951153A (en) | 1982-09-20 | 1982-09-20 | Premixing device for gasious fuel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS5951153A true JPS5951153A (en) | 1984-03-24 |
Family
ID=15775840
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP57163541A Pending JPS5951153A (en) | 1982-09-20 | 1982-09-20 | Premixing device for gasious fuel |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5951153A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008096041A (en) * | 2006-10-13 | 2008-04-24 | Hitachi Ltd | Combustor, fuel nozzle for combustor, and fuel supply method of combustor |
| KR20180087234A (en) | 2016-11-21 | 2018-08-01 | 닛토덴코 가부시키가이샤 | Adhesive sheet |
| KR20180087232A (en) | 2016-11-21 | 2018-08-01 | 닛토덴코 가부시키가이샤 | Adhesive sheet |
-
1982
- 1982-09-20 JP JP57163541A patent/JPS5951153A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2008096041A (en) * | 2006-10-13 | 2008-04-24 | Hitachi Ltd | Combustor, fuel nozzle for combustor, and fuel supply method of combustor |
| KR20180087234A (en) | 2016-11-21 | 2018-08-01 | 닛토덴코 가부시키가이샤 | Adhesive sheet |
| KR20180087232A (en) | 2016-11-21 | 2018-08-01 | 닛토덴코 가부시키가이샤 | Adhesive sheet |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6038861A (en) | Main stage fuel mixer with premixing transition for dry low Nox (DLN) combustors | |
| US7171813B2 (en) | Fuel injection nozzle for gas turbine combustor, gas turbine combustor, and gas turbine | |
| US7669421B2 (en) | Combustor of gas turbine with concentric swirler vanes | |
| US6993916B2 (en) | Burner tube and method for mixing air and gas in a gas turbine engine | |
| US7966820B2 (en) | Method and apparatus for combusting fuel within a gas turbine engine | |
| US5894720A (en) | Low emissions combustion system for a gas turbine engine employing flame stabilization within the injector tube | |
| US6736338B2 (en) | Methods and apparatus for decreasing combustor emissions | |
| JP2004132692A (en) | Hybrid swirler | |
| JP2004184072A (en) | Method for reducing emission from gas turbine engine combustor and its device | |
| JP2004534197A (en) | Premixing chamber for turbine combustor | |
| US6286300B1 (en) | Combustor with fuel preparation chambers | |
| JPS59202324A (en) | Low nox combustor of gas turbine | |
| JPH07332621A (en) | Swirl burner for gas turbine combustion device | |
| JPS5951153A (en) | Premixing device for gasious fuel | |
| JP3454441B2 (en) | Method and apparatus for low nitrogen oxide combustion combustion | |
| EP1243854A1 (en) | Fuel injector | |
| GB2097113A (en) | Low NOx combustor | |
| JP3174638B2 (en) | Premix structure of gas turbine combustor | |
| JPH09170716A (en) | Fuel premixing device and gas turbine combustion device | |
| RU2212005C2 (en) | Gas turbine combustion chamber | |
| JP2005076989A (en) | Low nox injection valve for liquid fuel, and fuel injection method therefor | |
| JPH0117061B2 (en) | ||
| JPH08285225A (en) | Method and device for nitrogen oxide low generating combustion | |
| JPH1030821A (en) | Combustor of gas turbine | |
| JPH08145309A (en) | Method and device for combustion reduced in generation of nitrogen oxide |