JP2002243152A - Combustor for gas turbine - Google Patents
Combustor for gas turbineInfo
- Publication number
- JP2002243152A JP2002243152A JP2001043289A JP2001043289A JP2002243152A JP 2002243152 A JP2002243152 A JP 2002243152A JP 2001043289 A JP2001043289 A JP 2001043289A JP 2001043289 A JP2001043289 A JP 2001043289A JP 2002243152 A JP2002243152 A JP 2002243152A
- Authority
- JP
- Japan
- Prior art keywords
- inner cylinder
- compressed air
- hole
- gas turbine
- combustor
- 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 abstract description 33
- 238000002347 injection Methods 0.000 claims abstract description 17
- 239000007924 injection Substances 0.000 claims abstract description 17
- 238000002485 combustion reaction Methods 0.000 claims abstract description 13
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 239000000243 solution Substances 0.000 abstract 1
- 239000007789 gas Substances 0.000 description 13
- 238000010790 dilution Methods 0.000 description 5
- 239000012895 dilution Substances 0.000 description 5
- 239000000567 combustion gas Substances 0.000 description 4
- 239000000779 smoke Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000008030 elimination Effects 0.000 description 1
- 238000003379 elimination reaction Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000002093 peripheral effect Effects 0.000 description 1
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】本発明は、内筒と外筒の間に
環状の空気通路が形成され、この環状の空気通路に燃焼
用及び希釈用の圧縮空気が供給されるガスタービンの燃
焼器に関するものである。The present invention relates to a gas turbine combustor in which an annular air passage is formed between an inner cylinder and an outer cylinder, and compressed air for combustion and dilution is supplied to the annular air passage. It is about.
【０００２】[0002]
【従来の技術】図８は、従来の産業用として使用される
一般的なガスタービンの燃焼器２００の断面略図であ
る。また、図９は図８のIX−IX断面図である。図８に示
すように燃焼器２００は、大径の外筒９１の中に小径の
内筒９２が同芯に設けられており、外筒９１と内筒９２
の間には環状空気通路９５が形成されている。燃料噴射
装置９４により内筒９２の内部に燃料が供給され、ま
た、旋回羽根９９が設けてある空気流入口９８からは、
環状空気通路９５内の圧縮空気が旋回しながら流入する
ようになっている。2. Description of the Related Art FIG. 8 is a schematic sectional view of a conventional gas turbine combustor 200 used for industrial use. FIG. 9 is a sectional view taken along line IX-IX of FIG. As shown in FIG. 8, the combustor 200 includes a large-diameter outer cylinder 91 and a small-diameter inner cylinder 92 provided concentrically.
An annular air passage 95 is formed therebetween. The fuel is supplied to the inside of the inner cylinder 92 by the fuel injection device 94, and from the air inlet 98 provided with the swirling blade 99,
The compressed air in the annular air passage 95 flows in while turning.
【０００３】さらに内筒９２には燃焼用空気孔９６が設
けてあり、この燃焼用空気孔９６を介して環状空気通路
９５内の圧縮空気が内筒９２内に流入し、これが燃料噴
射装置９４から噴射された燃料及び空気流入口９８から
流入した圧縮空気（旋回流）と混合し、この混合気が点
火栓９３により点火されて着火し、内筒９２内で燃焼ガ
スが生成される。Further, a combustion air hole 96 is provided in the inner cylinder 92, and compressed air in the annular air passage 95 flows into the inner cylinder 92 through the combustion air hole 96, and this is injected into the fuel injection device 94. And the compressed air (swirl flow) flowing from the air inlet 98, and the mixture is ignited by an ignition plug 93 to ignite, and combustion gas is generated in the inner cylinder 92.
【０００４】ところで、燃焼用空気孔９６には図９に示
すような案内筒９９が設けてあり、この案内筒９９によ
り流入する圧縮空気は、矢印で示すように内筒９２の中
心方向へ進行する。この案内筒９９により、内筒９２の
中心には十分な空気が供給されるが、逆に内筒２の内壁
面近傍にはほとんど供給されない。これが原因で、内筒
９２内に温度分布が生じ、内壁面付近は中心部分と比較
して高温になり、ＮＯ Ｘが生じ易くなる。The combustion air holes 96 are shown in FIG.
Such a guide cylinder 99 is provided.
The compressed air flowing into the inner cylinder 92 as shown by the arrow
Proceed in the direction of the heart. The guide cylinder 99 allows the inner cylinder 92
Although sufficient air is supplied to the center,
It is hardly supplied near the surface. Due to this, the inner cylinder
Temperature distribution occurs inside 92, near the inner wall compared to the center
High temperature, NO XTends to occur.
【０００５】[0005]
【発明が解決しようとする課題】そこで、本発明では、
内筒内の温度分布を解消し、ＮＯＸが生じにくくなるガ
スタービンの燃焼器を提供することを課題としている。Therefore, in the present invention,
An object of the present invention is to provide a gas turbine combustor in which the temperature distribution in the inner cylinder is eliminated and NO X is less likely to be generated.
【０００６】[0006]
【課題を解決するための手段】上記課題を解決するため
請求項１の発明では、圧縮空気を通過させる環状空気通
路を形成する外筒と内筒とを備え、前記内筒の一端に燃
料噴射装置が設置されて燃料が内筒内に噴射され、かつ
前記燃料噴射装置の周囲から圧縮空気が旋回しながら内
筒内へ流入する空気流入口を内筒に備えたガスタービン
の燃焼器において、前記内筒の円筒側壁に孔を設け、前
記孔から内筒内に流入した燃焼用の圧縮空気が内筒の中
心軸を避けて進行するように前記孔にガイド部材を設け
た。請求項２の発明では請求項１の発明において、前記
孔から流入した圧縮空気が、前記空気流入口から流入し
た圧縮空気の旋回方向と同方向に旋回するように前記孔
にガイド部材を設けた。請求項３の発明では請求項１又
は請求項２の発明において、ガイド部材を設けた前記孔
を円周上に３箇所以上設け、かつ流入する圧縮空気が内
筒の中心方向と４０度以上の角度で流入するようにし
た。請求項４の発明では請求項１又は請求項２の発明に
おいて、圧縮空気が内筒の内壁面に沿って旋回するよう
に前記ガイド部材を設けた。請求項５の発明では、圧縮
空気を通過させる環状空気通路を形成する外筒と内筒と
を備え、前記内筒の一端に燃料噴射装置が設置されて燃
料が内筒内に噴射され、かつ前記燃料噴射装置の周囲か
ら圧縮空気が旋回しながら内筒内へ流入する空気流入口
を内筒に備えたガスタービンの燃焼器において、環状空
気通路の終端又は終端近傍に整流部材を設け、圧縮空気
が前記空気流入口から内筒内に円周上均一に流入するよ
うにした。請求項６の発明では請求項５の発明におい
て、前記整流部材を環状板で形成し、環状板により前記
環状空気通路の幅が上流側から下流側へ徐々に狭くなる
ようにした。According to a first aspect of the present invention, there is provided an outer cylinder and an inner cylinder which form an annular air passage through which compressed air passes, and fuel injection is provided at one end of the inner cylinder. In a combustor of a gas turbine provided with an air inlet in which the device is installed, fuel is injected into the inner cylinder, and the compressed air swirls from around the fuel injection device and flows into the inner cylinder, A hole is provided in the cylindrical side wall of the inner cylinder, and a guide member is provided in the hole so that the compressed air for combustion flowing into the inner cylinder from the hole advances while avoiding the central axis of the inner cylinder. According to a second aspect of the present invention, in the first aspect, a guide member is provided in the hole such that the compressed air flowing from the hole turns in the same direction as the turning direction of the compressed air flowing from the air inlet. . According to a third aspect of the present invention, in the first or second aspect of the present invention, the holes provided with the guide members are provided at three or more locations on the circumference, and the inflow of compressed air is at least 40 degrees with respect to the center direction of the inner cylinder. It was made to flow at an angle. According to a fourth aspect of the present invention, in the first or second aspect of the invention, the guide member is provided so that the compressed air turns along the inner wall surface of the inner cylinder. According to the invention of claim 5, there is provided an outer cylinder and an inner cylinder that form an annular air passage through which the compressed air passes, and a fuel injection device is provided at one end of the inner cylinder to inject fuel into the inner cylinder, and In a gas turbine combustor having an air inlet in the inner cylinder through which compressed air swirls from the periphery of the fuel injection device and flows into the inner cylinder, a rectifying member is provided at or near the end of the annular air passage, and a compression member is provided. Air was allowed to flow uniformly around the circumference from the air inlet into the inner cylinder. According to a sixth aspect of the present invention, in the fifth aspect of the invention, the rectifying member is formed of an annular plate, and the width of the annular air passage is gradually reduced from the upstream side to the downstream side by the annular plate.
【０００７】[0007]
【発明の実施の形態】（請求項１〜３の発明の実施例）
図１は、請求項１〜３の発明を実施したガスタービン１
００の断面略図である。ガスタービン１００には燃焼器
５０が設けてある。燃焼器５０は、大径の外筒５，小径
の内筒６，燃料噴射装置１６及び点火栓１０等から構成
されている。DESCRIPTION OF THE PREFERRED EMBODIMENTS (Embodiments of Claims 1 to 3)
FIG. 1 shows a gas turbine 1 according to the first to third embodiments.
FIG. The gas turbine 100 is provided with a combustor 50. The combustor 50 includes a large-diameter outer cylinder 5, a small-diameter inner cylinder 6, a fuel injection device 16, an ignition plug 10, and the like.
【０００８】外筒５のフランジ部５ａがガスタービン１
００のハウジング３に対して円周上の複数箇所（例えば
８箇所・図１にはそのうちの２つのみ表示）にボルト１
５で固着されている。その内部には内筒６が配置されて
いる。内筒６は、スクロール１２，ノズルフランジ２
２，タービンシュラウド２３等を介してハウジング３に
固定されている。The flange portion 5 a of the outer cylinder 5 is
Bolts 1 at a plurality of locations on the circumference (for example, eight locations, only two of which are shown in FIG. 1) with respect to the housing 3
5 is fixed. The inner cylinder 6 is arranged inside the inside. The inner cylinder 6 includes the scroll 12 and the nozzle flange 2
2, is fixed to the housing 3 via a turbine shroud 23 and the like.
【０００９】外筒５と内筒６の間には環状空気通路１１
が形成されている。内筒６の一端には燃料供給通路９を
介して供給される燃料を内筒６内に噴射させる燃料噴射
弁１６が設けてある。また、燃料噴射弁１６の周囲の内
筒６には、旋回羽根１を備えた環状の空気流入口２が設
けてある。さらに内筒６には、燃焼用の空気を内筒６内
に流入させる孔１８と、希釈用の空気を内筒６内に流入
させる希釈孔８とが設けてある。孔１８には筒状のガイ
ド部材７が設けてある。An annular air passage 11 is provided between the outer cylinder 5 and the inner cylinder 6.
Are formed. At one end of the inner cylinder 6, a fuel injection valve 16 for injecting fuel supplied through the fuel supply passage 9 into the inner cylinder 6 is provided. Further, the inner cylinder 6 around the fuel injection valve 16 is provided with an annular air inlet 2 provided with the swirling blade 1. Further, the inner cylinder 6 is provided with a hole 18 for allowing combustion air to flow into the inner cylinder 6 and a dilution hole 8 for allowing dilution air to flow into the inner cylinder 6. The cylindrical guide member 7 is provided in the hole 18.
【００１０】ガスタービン１００（図１）では、図示し
ないコンプレッサから環状空気通路１１へ圧縮空気が供
給され、圧縮空気は、空気流２０，２１として環状空気
通路１１内を進行する。空気流入口２を通過した圧縮空
気は、旋回羽根１により旋回流を形成しながら内筒６内
に流入する。In the gas turbine 100 (FIG. 1), compressed air is supplied from a compressor (not shown) to the annular air passage 11, and the compressed air travels in the annular air passage 11 as airflows 20 and 21. The compressed air that has passed through the air inlet 2 flows into the inner cylinder 6 while forming a swirling flow by the swirling blades 1.
【００１１】また、同時に燃料が燃料噴射弁１６から噴
射され、内筒６内では空気の旋回流に燃料が混合する。
さらに孔１８から内筒６内に圧縮空気が流入する。孔１
８から内筒６内に流入した圧縮空気は、ガイド部材７に
沿って進み、旋回流と合流する。At the same time, fuel is injected from the fuel injection valve 16, and the fuel mixes with the swirling air flow in the inner cylinder 6.
Further, compressed air flows into the inner cylinder 6 from the hole 18. Hole 1
The compressed air that has flowed into the inner cylinder 6 from 8 advances along the guide member 7 and merges with the swirling flow.
【００１２】そして、点火栓１０により着火されて燃焼
ガスが発生する。燃焼ガスは、内筒６内を進み、希釈孔
８から流入した空気により希釈され、スクロール１２を
介してノズル１３からタービン１４に向かって噴射さ
れ、タービン１４を駆動（軸２５を中心に回転）させ
る。その後、燃焼ガスは排気ガスとして排気通路４を介
して排出される。Then, the fuel is ignited by the ignition plug 10 to generate combustion gas. The combustion gas advances in the inner cylinder 6, is diluted by the air flowing from the dilution hole 8, is injected from the nozzle 13 toward the turbine 14 through the scroll 12, and drives the turbine 14 (rotates around the shaft 25). Let it. Thereafter, the combustion gas is exhausted as exhaust gas through the exhaust passage 4.
【００１３】図１のII−II断面図である図２に示すよう
に、ガイド部材７は、圧縮空気の進行方向が内筒６の中
心方向と４５度の角度を形成するように設けてある。ま
た、孔１８から内筒６の中へ流入する圧縮空気の向き
は、図１に示す空気流入口２から流入した圧縮空気の旋
回方向（旋回流）に追従する向きに設定されている。As shown in FIG. 2 which is a sectional view taken along the line II-II of FIG. 1, the guide member 7 is provided such that the traveling direction of the compressed air forms an angle of 45 degrees with the center direction of the inner cylinder 6. . The direction of the compressed air flowing into the inner cylinder 6 from the hole 18 is set to follow the swirling direction (swirl flow) of the compressed air flowing from the air inlet 2 shown in FIG.
【００１４】このように、ガイド部材７を孔１８に設け
ることにより、孔１８から流入する空気流が内筒６内の
旋回流を乱すことがないため、空気が局所的に対流する
ことがなく、内筒６内の温度分布をほぼ均一にすること
ができる。Since the guide member 7 is provided in the hole 18 as described above, the air flow flowing from the hole 18 does not disturb the swirling flow in the inner cylinder 6, so that the air does not locally convect. The temperature distribution in the inner cylinder 6 can be made substantially uniform.
【００１５】図５は、請求項３の発明を実施した際にお
ける空燃比とＮＯＸ濃度の関係を示すグラフである。ま
た、図６は、請求項３の発明を実施した際における空燃
比と燃焼効率の関係を示すグラフである。さらに、図７
は、請求項３の発明を実施した際における空燃比と排気
煙の関係を示すグラフである。[0015] Figure 5 is a graph showing the relationship between the air-fuel ratio and the NO X concentration at time of implementing the present invention according to claim 3. FIG. 6 is a graph showing the relationship between the air-fuel ratio and the combustion efficiency when the invention of claim 3 is implemented. Further, FIG.
7 is a graph showing the relationship between the air-fuel ratio and the exhaust smoke when the invention of claim 3 is implemented.
【００１６】図５〜７からわかるように、孔１８に図２
に示すガイド部材７を設けることにより、従来よりも発
生するＮＯＸ量を低減することができ、また、燃焼効率
を向上させることができ、さらに排気煙を良好にするこ
とができる。As can be seen from FIGS.
By providing the guide member 7 described above, the amount of NO X generated can be reduced as compared with the conventional case, the combustion efficiency can be improved, and the exhaust smoke can be further improved.
【００１７】（請求項４の発明の実施例）図３は、図２
においてガイド部材７をガイド部材７ａに置き換えた燃
焼器５１の横断面図である。ガイド部材７ａは、図２に
示すガイド部材７のうち、壁面対向部２７（図２）を取
り除いたものである。(Embodiment of the Invention of Claim 4) FIG.
5 is a cross-sectional view of the combustor 51 in which the guide member 7 is replaced with a guide member 7a. The guide member 7a is obtained by removing the wall facing portion 27 (FIG. 2) from the guide member 7 shown in FIG.
【００１８】ガイド部材７ａに示すように、壁面対向部
２７をなくすことにより、孔１８から内筒６内に流入し
た圧縮空気は、内筒６の内壁面に沿って進み易くなり、
内筒６の内壁面を冷却することができる。As shown in the guide member 7a, the elimination of the wall surface facing portion 27 makes it easier for the compressed air flowing into the inner cylinder 6 from the hole 18 to proceed along the inner wall surface of the inner cylinder 6,
The inner wall surface of the inner cylinder 6 can be cooled.
【００１９】（請求項５，６の発明の実施例）図４は、
請求項５及び請求項６の発明を実施した燃焼器５２の縦
断正面略図である。燃焼器５２の構成は、環状空気通路
１１の終端付近に整流板３０が設けてある点のみが燃焼
器５０（図１）の構成と異なっており、その他の構成は
燃焼器５０の構成と同じである。(Embodiments of Claims 5 and 6) FIG.
It is the longitudinal front schematic diagram of the combustor 52 which implemented the invention of Claim 5 and Claim 6. The configuration of the combustor 52 differs from the configuration of the combustor 50 (FIG. 1) only in that a straightening plate 30 is provided near the end of the annular air passage 11, and the other configuration is the same as the configuration of the combustor 50. It is.
【００２０】整流板３０はテーパ形状を呈しており、環
状空気通路１１の通路幅を上流側から下流側へ徐々に狭
めている。圧縮空気は図示しないコンプレッサから環状
空気通路１１に供給されるが、環状空気通路１１内のコ
ンプレッサに近い側（空気流２０側）と、遠い側（空気
流２１側）との間には圧力差が生じている。つまり、近
い側の方が遠い側よりも圧力が高くなっている。The current plate 30 has a tapered shape, and the width of the annular air passage 11 is gradually reduced from the upstream side to the downstream side. The compressed air is supplied from a compressor (not shown) to the annular air passage 11, and the pressure difference between the side (air flow 20 side) close to the compressor and the far side (air flow 21 side) in the annular air passage 11. Has occurred. That is, the pressure is higher on the near side than on the far side.
【００２１】そのため、空気流入口２から内筒６内に流
入する圧縮空気は円周上均一ではなく、偏りが生じる。
整流板３０は、圧力が高い側の通路幅が圧力が低い側よ
りも狭くなるように設定されている。そのため、整流板
３０を通過した圧縮空気の量は、円周上均一に矯正され
ており、圧縮空気は空気流入口２から内筒６内に円周上
均一に流入する。As a result, the compressed air flowing into the inner cylinder 6 from the air inlet 2 is not uniform on the circumference but is biased.
The current plate 30 is set such that the passage width on the high pressure side is narrower than that on the low pressure side. Therefore, the amount of the compressed air that has passed through the flow straightening plate 30 is uniformly corrected on the circumference, and the compressed air flows uniformly from the air inlet 2 into the inner cylinder 6 on the circumference.
【００２２】整流板３０は、空気流入口２の開口面積よ
りも小さくならないように環状空気通路１１を絞る。空
気流入口２の開口面積を例えば２０００ｍｍ２程度とす
ると、整流板の最も通路幅の狭いところの通路総面積
は、例えば４０００ｍｍ２程度に設定する。The current plate 30 narrows the annular air passage 11 so as not to be smaller than the opening area of the air inlet 2. Assuming that the opening area of the air inlet 2 is, for example, about 2000 mm 2, the total passage area of the straightening plate where the passage width is narrowest is set to, for example, about 4000 mm 2 .
【００２３】整流板３０の代わりに、例えば孔を開けた
整流板を環状空気通路１１に備えてもよい。この場合、
同じ大きさの孔を圧力が高い側には少なく、圧力が低い
側には多くなるように設けると、円周上均一な量の空気
流に整流することができる。Instead of the rectifying plate 30, a rectifying plate having holes, for example, may be provided in the annular air passage 11. in this case,
By providing holes of the same size with fewer holes on the high pressure side and more holes on the low pressure side, it is possible to rectify a uniform amount of air flow on the circumference.
【００２４】図２，図３のガイド部材７，７ａに加え、
さらに整流板３０を設けると、ＮＯ Ｘ発生量をさらに減
少させることができ、また、燃焼効率をさらに向上させ
ることができる。また、排気煙も良好になる。In addition to the guide members 7 and 7a shown in FIGS.
When the current plate 30 is further provided, NO XFurther reduction of generation
And further improve combustion efficiency.
Can be Also, the exhaust smoke becomes better.
【００２５】[0025]
【発明の効果】請求項１の発明では、内筒６の円筒側壁
に設けた孔１８にガイド部材７を設け、孔１８から内筒
６内に流入する空気流の進行方向を内筒６の中心軸を避
けるようにしたので、空気が内筒６内の周辺領域へ供給
され易くなり、内筒６内の部分的な温度差が縮小し、Ｎ
ＯＸの発生量を抑制することができる。According to the first aspect of the present invention, the guide member 7 is provided in the hole 18 provided on the cylindrical side wall of the inner cylinder 6, and the traveling direction of the air flow flowing into the inner cylinder 6 from the hole 18 is controlled by Since the center axis is avoided, the air is easily supplied to the peripheral area in the inner cylinder 6, the partial temperature difference in the inner cylinder 6 is reduced, and N
The generation amount of O X can be suppressed.
【００２６】請求項２の発明では、空気流入口２から流
入した空気の旋回流と同方向に旋回するように孔１８に
ガイド部材７を設けたので、請求項１の発明の効果に加
え、内筒６内における旋回流の流れをより促進すること
ができ、それによって保炎性が向上し失火しにくくなる
ので、ガスタービン１００の運転性能を向上させること
ができる。According to the second aspect of the present invention, the guide member 7 is provided in the hole 18 so as to swirl in the same direction as the swirling flow of the air flowing from the air inflow port 2. The flow of the swirling flow in the inner cylinder 6 can be further promoted, thereby improving the flame holding property and making it difficult to cause a misfire, so that the operation performance of the gas turbine 100 can be improved.
【００２７】請求項３の発明では、孔１８を円周上３箇
所以上に設け、かつ、圧縮空気が内筒６の中心方向と４
０度以上の角度で流入するようにしたので、請求項１，
２の発明により得られる効果をさらに高めることができ
る。According to the third aspect of the present invention, the holes 18 are provided at three or more locations on the circumference, and the compressed air is
The inflow is made at an angle of 0 degree or more.
The effect obtained by the second invention can be further enhanced.
【００２８】請求項４の発明では、孔１８から内筒６内
に流入した空気流を内筒６の内壁面に沿って旋回するよ
うにガイド部材７ａを設けたので、請求項１，２の発明
の効果に加え、内筒６の円筒側壁の温度を低減すること
ができ、内筒６の安全性を向上させることができる。According to the fourth aspect of the present invention, the guide member 7a is provided so that the air flow flowing into the inner cylinder 6 from the hole 18 turns along the inner wall surface of the inner cylinder 6. In addition to the effects of the invention, the temperature of the cylindrical side wall of the inner cylinder 6 can be reduced, and the safety of the inner cylinder 6 can be improved.
【００２９】請求項５の発明では、環状空気通路１１の
終端近傍に整流部材を設けたので、空気流入口２から流
入する空気量を円周上均一にすることができ、保炎性能
や燃焼効率を向上させることができる。また、内筒６内
における空燃比の部分的な差異を解消することができ、
発生するＮＯＸ量を低減することができる。According to the fifth aspect of the present invention, since the rectifying member is provided near the end of the annular air passage 11, the amount of air flowing from the air inlet 2 can be made uniform around the circumference, and the flame holding performance and combustion can be improved. Efficiency can be improved. Further, a partial difference in the air-fuel ratio in the inner cylinder 6 can be eliminated,
The generated NO X amount can be reduced.
【００３０】請求項６の発明では、整流部材を環状板
（整流板３０）で形成したので、簡単に整流部材を形成
することができ、環状空気通路１１の通路幅を容易に設
定することができる。According to the sixth aspect of the present invention, since the rectifying member is formed by the annular plate (rectifying plate 30), the rectifying member can be easily formed, and the passage width of the annular air passage 11 can be easily set. it can.
【図１】 請求項１の発明を実施した燃焼器を備えたガ
スタービンの断面略図である。FIG. 1 is a schematic sectional view of a gas turbine including a combustor embodying the invention of claim 1;
【図２】 図１のII−II断面図である。FIG. 2 is a sectional view taken along line II-II of FIG.
【図３】 請求項４の発明を実施した燃焼器の図２に対
応する横断面図である。FIG. 3 is a cross-sectional view corresponding to FIG. 2 of the combustor embodying the invention of claim 4;
【図４】 請求項５及び請求項６の発明を実施した燃焼
器の縦断正面略図である。FIG. 4 is a schematic longitudinal sectional front view of a combustor embodying the invention of claim 5 and claim 6;
【図５】 空燃比と発生するＮＯＸ量の関係を示すグラ
フである。FIG. 5 is a graph showing a relationship between an air-fuel ratio and a generated NO X amount.
【図６】 空燃比と燃焼効率の関係を示すグラフであ
る。FIG. 6 is a graph showing a relationship between an air-fuel ratio and combustion efficiency.
【図７】 空燃比と発生する排気煙量の関係を示すグラ
フである。FIG. 7 is a graph showing the relationship between the air-fuel ratio and the amount of generated exhaust smoke.
【図８】 従来の産業用として使用される一般的なガス
タービンの燃焼器の断面略図である。FIG. 8 is a schematic cross-sectional view of a conventional gas turbine combustor used for industrial use.
【図９】 図８のIX−IX断面図である。FIG. 9 is a sectional view taken along line IX-IX of FIG.
１ 旋回羽根 ２ 空気流入口 ３ ハウジング ５ 外筒 ６ 内筒 ７，７ａ ガイド部材 ８ 希釈孔 １０ 点火栓 １１ 環状通路 １２ スクロール １６ 燃料噴射弁 １８ 孔 ３０ 整流板 ５０〜５２ 燃焼器 １００ ガスタービン REFERENCE SIGNS LIST 1 swirl vane 2 air inlet 3 housing 5 outer cylinder 6 inner cylinder 7, 7a guide member 8 dilution hole 10 ignition plug 11 annular passage 12 scroll 16 fuel injection valve 18 hole 30 straightening plate 50-52 combustor 100 gas turbine
Claims (6)
成する外筒と内筒とを備え、前記内筒の一端に燃料噴射
装置が設置されて燃料が内筒内に噴射され、かつ前記燃
料噴射装置の周囲から圧縮空気が旋回しながら内筒内へ
流入する空気流入口を内筒に備えたガスタービンの燃焼
器において、 前記内筒の円筒側壁に孔を設け、前記孔から内筒内に流
入した燃焼用の圧縮空気が内筒の中心軸を避けて進行す
るように前記孔にガイド部材を設けたことを特徴とする
ガスタービンの燃焼器。1. An inner cylinder having an outer cylinder defining an annular air passage through which compressed air passes, and a fuel injection device is provided at one end of the inner cylinder to inject fuel into the inner cylinder, and In a gas turbine combustor having an inner cylinder with an air inlet through which compressed air swirls from the periphery of the injection device and flows into the inner cylinder, a hole is provided in a cylindrical side wall of the inner cylinder, and a hole is formed in the inner cylinder from the hole. A gas turbine combustor characterized in that a guide member is provided in the hole so that the compressed air for combustion flowing into the hole advances while avoiding the central axis of the inner cylinder.
気流入口から流入した圧縮空気の旋回方向と同方向に旋
回するように前記孔にガイド部材を設けた請求項１に記
載のガスタービンの燃焼器。2. The gas turbine according to claim 1, wherein a guide member is provided in the hole so that the compressed air flowing from the hole turns in the same direction as the turning direction of the compressed air flowing from the air inlet. Combustor.
箇所以上設け、かつ流入する圧縮空気が内筒の中心方向
と４０度以上の角度で流入するようにした請求項１又は
請求項２に記載のガスタービンの燃焼器。3. The hole provided with a guide member is formed on the circumference of
The gas turbine combustor according to claim 1 or 2, wherein the compressed air is provided at more than one location, and the inflowing compressed air flows at an angle of 40 degrees or more with respect to the center direction of the inner cylinder.
るように前記ガイド部材を設けた請求項１又は請求項２
に記載のガスタービンの燃焼器。4. The guide member according to claim 1, wherein the guide member is provided so that compressed air turns along the inner wall surface of the inner cylinder.
A combustor for a gas turbine according to claim 1.
成する外筒と内筒とを備え、前記内筒の一端に燃料噴射
装置が設置されて燃料が内筒内に噴射され、かつ前記燃
料噴射装置の周囲から圧縮空気が旋回しながら内筒内へ
流入する空気流入口を内筒に備えたガスタービンの燃焼
器において、 前記環状空気通路の終端又は終端近傍に整流部材を設
け、圧縮空気が前記空気流入口から内筒内に円周上均一
に流入するようにしたことを特徴とするガスタービンの
燃焼器。5. An inner cylinder having an outer cylinder forming an annular air passage through which compressed air passes, and a fuel injection device is provided at one end of the inner cylinder to inject fuel into the inner cylinder, and In a gas turbine combustor provided with an air inlet in the inner cylinder through which compressed air swirls from the periphery of the injection device and flows into the inner cylinder, a rectifying member is provided at or near the end of the annular air passage, and compressed air is provided. Wherein the gas flows uniformly into the inner cylinder from the air inlet into the inner cylinder.
により前記環状空気通路の幅が上流側から下流側へ徐々
に狭くなるようにした請求項５に記載のガスタービンの
燃焼器。6. The gas turbine combustor according to claim 5, wherein the rectifying member is formed of an annular plate, and the annular plate gradually narrows the width of the annular air passage from an upstream side to a downstream side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001043289A JP2002243152A (en) | 2001-02-20 | 2001-02-20 | Combustor for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP2001043289A JP2002243152A (en) | 2001-02-20 | 2001-02-20 | Combustor for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2002243152A true JP2002243152A (en) | 2002-08-28 |
Family
ID=18905479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP2001043289A Pending JP2002243152A (en) | 2001-02-20 | 2001-02-20 | Combustor for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2002243152A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007232347A (en) * | 2006-02-27 | 2007-09-13 | Mitsubishi Heavy Ind Ltd | Combustor |
| KR20170127916A (en) * | 2016-05-13 | 2017-11-22 | 한화테크윈 주식회사 | Combustor |
-
2001
- 2001-02-20 JP JP2001043289A patent/JP2002243152A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2007232347A (en) * | 2006-02-27 | 2007-09-13 | Mitsubishi Heavy Ind Ltd | Combustor |
| KR20170127916A (en) * | 2016-05-13 | 2017-11-22 | 한화테크윈 주식회사 | Combustor |
| KR102116099B1 (en) | 2016-05-13 | 2020-05-27 | 한화에어로스페이스 주식회사 | Combustor |
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