JP2000320837A - Gas turbine combustor - Google Patents
Gas turbine combustorInfo
- Publication number
- JP2000320837A JP2000320837A JP12556899A JP12556899A JP2000320837A JP 2000320837 A JP2000320837 A JP 2000320837A JP 12556899 A JP12556899 A JP 12556899A JP 12556899 A JP12556899 A JP 12556899A JP 2000320837 A JP2000320837 A JP 2000320837A
- Authority
- JP
- Japan
- Prior art keywords
- combustion cylinder
- gas turbine
- angle
- cooling fins
- 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
Abstract
Description
【発明の詳細な説明】DETAILED DESCRIPTION OF THE INVENTION
【０００１】[0001]
【発明の属する技術分野】本発明は、ガスタービン燃焼
器に係り、さらに詳細には燃焼筒（ライナ）の構造に関
する。The present invention relates to a gas turbine combustor, and more particularly, to a structure of a combustion cylinder (liner).
【０００２】[0002]
【従来の技術】産業用ガスタービンなどの燃焼器におい
ては、環境問題への配慮から、燃焼器内に生じる窒素酸
化物（ＮＯｘ）の排出量を低減することが求められてい
る。2. Description of the Related Art In a combustor such as an industrial gas turbine, it is required to reduce the amount of nitrogen oxide (NOx) generated in the combustor in consideration of environmental problems.
【０００３】ＮＯｘの低減は、燃料と空気を燃焼前に混
合して燃焼させる予混合燃焼を利用し、かつ燃料と空気
の混合比（燃空比）が理論混合比よりも小さい状態で燃
焼させることによって図られる。[0003] Reduction of NOx utilizes premixed combustion in which fuel and air are mixed and burned before combustion, and combustion is performed in a state where the mixture ratio of fuel and air (fuel-air ratio) is smaller than the stoichiometric mixture ratio. This is achieved by:
【０００４】一方、ガスタービンのさらなる高効率化の
ためには、燃焼ガスをより高温化する必要がある。現在
の高温ガスタービンでは、すでに１４００℃の燃焼ガス
が流れているが、さらに高温化の要求が強い。そのた
め、高温雰囲気にさらされる燃焼筒保護のために、燃焼
筒の冷却が非常に重要となっている。On the other hand, in order to further increase the efficiency of the gas turbine, it is necessary to raise the temperature of the combustion gas. In the current high-temperature gas turbine, a combustion gas of 1400 ° C. is already flowing, but there is a strong demand for a higher temperature. Therefore, cooling of the combustion cylinder is very important for protecting the combustion cylinder exposed to a high temperature atmosphere.
【０００５】燃焼筒の冷却には、従来、燃焼筒内壁に冷
却空気を吹き出させて、燃焼筒内壁を冷却空気の膜で覆
う膜冷却構造が多く用いられてきた。しかし、この冷却
方法では、燃焼筒の内側に冷却用空気を噴出させるため
燃焼ガスの高温化が図れず、しかも、燃焼用空気が減少
するために燃空比が増し、ＮＯｘ増加の原因となる。そ
のため対流冷却のみで所定の冷却性能を得る必要が生じ
た。Conventionally, a film cooling structure in which cooling air is blown to the inner wall of the combustion cylinder to cover the inner wall of the combustion cylinder with a film of cooling air has been often used for cooling the combustion cylinder. However, in this cooling method, the temperature of the combustion gas cannot be increased because the cooling air is jetted into the inside of the combustion cylinder, and the fuel air ratio increases due to the decrease in the combustion air, which causes an increase in NOx. . Therefore, it became necessary to obtain a predetermined cooling performance only by convection cooling.
【０００６】対流冷却を促進するために、例えば、燃焼
筒外側に金属繊維を設けてごみ詰まりを防ぎつつ冷却性
能向上を図る方法（特開平10−38277 号），らせん状の
リブを設けて振動を抑えつつ冷却性能の向上を図る方法
（特開平9−196377 号），尾筒内筒と尾筒外筒の間に冷
却フィンを設けて冷却性能の向上を図る方法（特開平8
−303781 号）などが開示されている。In order to promote convective cooling, for example, a method is provided in which metal fibers are provided outside the combustion cylinder to improve the cooling performance while preventing clogging of dust (Japanese Patent Laid-Open No. 10-38277). (Japanese Patent Application Laid-Open No. 9-196377) and a method of improving cooling performance by providing cooling fins between the transition piece inner cylinder and transition piece outer cylinder (JP-A-9-196377).
No. -303781).
【０００７】[0007]
【発明が解決しようとする課題】本発明は上記の事情に
鑑みてなされたものであり、燃焼筒の冷却性能を向上さ
せて燃焼ガスの高温化を図ることにより、ガスタービン
全体の効率を向上させるとともに、燃空比を小さく抑え
ることにより、低公害のガスタービンを実現することで
ある。SUMMARY OF THE INVENTION The present invention has been made in view of the above circumstances, and improves the efficiency of a gas turbine as a whole by improving the cooling performance of a combustion cylinder to increase the temperature of combustion gas. Another object of the present invention is to realize a low-pollution gas turbine by suppressing the fuel-air ratio.
【０００８】[0008]
【課題を解決するための手段】燃焼筒の内側には、高温
の燃焼ガスが流れている。燃焼筒の外側には、低温の圧
縮空気が流れている。燃焼筒の壁温を低温に抑えるに
は、燃焼筒外側の熱伝達率をできるだけ向上させて、圧
縮空気の温度に近づけることが有効である。A high-temperature combustion gas flows inside the combustion cylinder. Outside the combustion tube, low-temperature compressed air flows. In order to suppress the wall temperature of the combustion cylinder to a low temperature, it is effective to improve the heat transfer coefficient outside the combustion cylinder as much as possible to approach the temperature of the compressed air.
【０００９】燃焼筒外側の圧縮空気は、秒速１０ｍ／ｓ
程度のかなり早い速度で流れているので、熱伝達率を向
上させるためには、燃焼筒外表面に冷却フィンを設け、
この冷却フィンによって流れに縦渦を発生させ、空気流
路内の攪拌混合を図ることが有効である。[0009] The compressed air outside the combustion cylinder is 10 m / s per second.
Since it is flowing at a considerably high speed, to improve the heat transfer coefficient, cooling fins are provided on the outer surface of the combustion cylinder,
It is effective to generate vertical vortices in the flow by the cooling fins and to stir and mix in the air flow path.
【００１０】本発明の第１の特徴は、燃焼筒外表面の展
開図において、空気流入方向に対し、迎え角γをなす断
続した冷却フィンを、燃焼筒外表面に設けたことであ
る。迎え角γが３０〜６０度の範囲にある時、冷却フィ
ン下流に生じる縦渦が最も強くなり、燃焼筒外表面の熱
伝達が向上し、その結果燃焼筒の外壁温度が低く抑えら
れる。A first feature of the present invention is that, in a developed view of the outer surface of the combustion cylinder, intermittent cooling fins forming an angle of attack γ with respect to the air inflow direction are provided on the outer surface of the combustion cylinder. When the angle of attack γ is in the range of 30 to 60 degrees, the longitudinal vortex generated downstream of the cooling fins is the strongest, heat transfer on the outer surface of the combustion cylinder is improved, and as a result, the temperature of the outer wall of the combustion cylinder is kept low.
【００１１】本発明の第２の特徴は、燃焼筒の軸を含む
縦断面において、空気流入方向に対し、迎え角βをなす
断続した冷却フィンを、燃焼筒外表面に設けたことであ
る。迎え角βが３０度以上９０度未満の時、冷却フィン
下流に生じる縦渦が最も強くなり、燃焼筒外表面の熱伝
達率が向上し、その結果燃焼筒の外壁温度を低く抑える
ことができる。A second feature of the present invention is that intermittent cooling fins having an angle of attack β with respect to the air inflow direction are provided on the outer surface of the combustion cylinder in a longitudinal section including the axis of the combustion cylinder. When the angle of attack β is 30 degrees or more and less than 90 degrees, the longitudinal vortex generated downstream of the cooling fins is the strongest, the heat transfer coefficient on the outer surface of the combustion cylinder is improved, and as a result, the outer wall temperature of the combustion cylinder can be kept low. .
【００１２】本発明の第３の特徴は、第１の特徴と第２
の特徴を併せ持ったものである。すなわち、燃焼筒外表
面の展開図において、空気流入方向に対し、迎え角γを
なし、燃焼筒の軸を含む縦断面において、空気流入方向
に対し、迎え角βをなす断続した冷却フィンを燃焼筒外
表面に設けたことを特徴とする。このような構造にする
と、２つの効果が重なり合って、さらに縦渦が強くな
り、燃焼筒外表面の熱伝達率が向上し、その結果燃焼筒
の外壁温度が低くなる。A third feature of the present invention is the first feature and the second feature.
It has the characteristics of That is, in the developed view of the outer surface of the combustion cylinder, an intermittent cooling fin that forms an attack angle γ with respect to the air inflow direction and forms an attack angle β with respect to the air inflow direction in a longitudinal section including the axis of the combustion cylinder in the air inflow direction. It is provided on the outer surface of the cylinder. With such a structure, the two effects overlap, the longitudinal vortex is further increased, and the heat transfer coefficient on the outer surface of the combustion cylinder is improved. As a result, the temperature of the outer wall of the combustion cylinder is reduced.
【００１３】第４の特徴は、第１項から第３項で述べた
冷却フィンを、尾筒（トランジションピース）外表面に
設けたことである。A fourth feature is that the cooling fins described in the first to third items are provided on the outer surface of a transition piece (transition piece).
【００１４】第５の特徴は、燃焼筒外表面の外側に同心
円筒状に位置する燃焼器外周壁の内面に、迎え角γ，傾
斜角（１８０−β）の断続するフィンを設けたことであ
る。このフィンは、燃焼筒外表面の冷却フィン下流に生
じた縦渦を、燃焼筒外表面に近い位置に留め、燃焼筒外
表面の熱伝達率をさらに向上し、その結果燃焼筒の外壁
温度がさらに低くなるという効果をもたらす。The fifth feature is that intermittent fins having an attack angle γ and an inclination angle (180-β) are provided on the inner surface of the outer peripheral wall of the combustor which is located concentrically outside the outer surface of the combustion cylinder. is there. This fin keeps the vertical vortex generated downstream of the cooling fin on the outer surface of the combustion cylinder at a position close to the outer surface of the combustion cylinder, further improving the heat transfer coefficient on the outer surface of the combustion cylinder, and as a result, the outer wall temperature of the combustion cylinder decreases. This has the effect of being even lower.
【００１５】これらの冷却フィンを有する燃焼筒は、遠
心鋳造法または巻フィン法により形成することができ
る。The combustion tube having these cooling fins can be formed by a centrifugal casting method or a wound fin method.
【００１６】[0016]
【発明の実施の形態】以下本発明の一実施例のガスター
ビン燃焼器について、図面を参照しながら説明する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A gas turbine combustor according to one embodiment of the present invention will be described below with reference to the drawings.
【００１７】図２は、発電用ガスタービンのシステム全
体図である。FIG. 2 is an overall system diagram of the gas turbine for power generation.
【００１８】空気は、圧縮機１で圧縮され、高圧の圧縮
空気６となって燃焼器２に送り込まれる。燃焼器は二重
円筒構造になっていて、内側にある燃焼筒の外側の環状
部に低温の圧縮空気６が流れ、燃焼筒を外側から冷却す
る構造になっている。この燃焼器２の左側の部分で、空
気６と燃料７が混合され、バーナにより燃焼して、高温
の燃焼ガス８となる。この高温の燃焼ガスは、燃焼筒の
内側を流れ、尾筒（トランジションピース）を経て、タ
ービン３に送り込まれ、タービンで膨張しながら、ター
ビンを回す。タービンと同軸に連結されている発電機４
が回転し、それによって発電される仕組みになってい
る。タービンで膨張した燃焼ガスは、排ガス９となって
放出される。The air is compressed by the compressor 1 and is sent to the combustor 2 as high-pressure compressed air 6. The combustor has a double-cylindrical structure, in which low-temperature compressed air 6 flows through the outer annular portion of the inner combustion cylinder to cool the combustion cylinder from the outside. In the left part of the combustor 2, the air 6 and the fuel 7 are mixed and burned by a burner to become a high-temperature combustion gas 8. This high-temperature combustion gas flows inside the combustion cylinder, is sent to the turbine 3 via a transition piece (transition piece), and turns the turbine while expanding with the turbine. Generator 4 coaxially connected to turbine
Rotates, and power is generated by it. The combustion gas expanded by the turbine is emitted as exhaust gas 9.
【００１９】本発明は、このシステムの中のガスタービ
ン燃焼器２に関するものである。燃焼器の一実施例を図
３に示す。The present invention relates to the gas turbine combustor 2 in this system. One embodiment of the combustor is shown in FIG.
【００２０】燃焼器は、燃焼器外筒２１と燃焼筒（ライ
ナ）２２の二重円筒構造になっている。圧縮された空気
６は、燃焼筒外側の環状流路を、図３では右から左に流
れる。左端からは燃料７が送り込まれ、ここで空気６と
混合され、バーナ２４，２５で点火される。高温となっ
た燃焼ガス８は、燃焼筒の中を左から右に流れる。つま
り、外側の圧縮空気６と内側の燃焼ガスとは、対向して
流れる構造になっている。圧縮空気の温度は、約３８０
℃、燃焼ガスの温度は約１４００℃である。従って、燃
焼筒２２は、内側から加熱され、外側から冷却されてい
る。燃焼ガス８は、尾筒２３を経て、タービンに送り込
まれる。本実施例の寸法について記すと、燃焼筒２２の
外径は３６０mm、長さは８８０mm、燃焼筒の板厚は１.
５７mm である。燃焼器外筒２１の内径は４６０mmなの
で、環状流路の高さＨは、５０mmである。The combustor has a double cylindrical structure of a combustor outer cylinder 21 and a combustion cylinder (liner) 22. The compressed air 6 flows through the annular flow path outside the combustion cylinder from right to left in FIG. Fuel 7 is fed in from the left end, where it is mixed with air 6 and ignited by burners 24 and 25. The hot combustion gas 8 flows from left to right in the combustion tube. That is, the outer compressed air 6 and the inner combustion gas have a structure in which they flow in opposition to each other. The temperature of the compressed air is about 380
° C and the temperature of the combustion gas is about 1400 ° C. Therefore, the combustion cylinder 22 is heated from the inside and cooled from the outside. The combustion gas 8 is sent to the turbine via the transition piece 23. Describing the dimensions of this embodiment, the outer diameter of the combustion cylinder 22 is 360 mm, the length is 880 mm, and the thickness of the combustion cylinder is 1.
57 mm. Since the inner diameter of the combustor outer cylinder 21 is 460 mm, the height H of the annular flow path is 50 mm.
【００２１】燃焼筒２２の外表面には、伝熱面積を拡大
し、熱伝達率を促進させるために、冷却フィン２６が設
けられている。冷却フィンの一実施例を図１により説明
する。Cooling fins 26 are provided on the outer surface of the combustion tube 22 in order to enlarge the heat transfer area and promote the heat transfer coefficient. One embodiment of the cooling fin will be described with reference to FIG.
【００２２】図１は燃焼筒２２の斜視図である。FIG. 1 is a perspective view of the combustion tube 22.
【００２３】圧縮空気６は、燃焼器外筒２１と燃焼筒２
２との間の環状流路を、右から左に流れる。一方、高温
の燃焼ガス８は、燃焼筒２２の内部を、左から右へ流れ
る。The compressed air 6 is supplied to the combustor outer cylinder 21 and the combustion cylinder 2
2 from right to left. On the other hand, the high-temperature combustion gas 8 flows inside the combustion tube 22 from left to right.
【００２４】燃焼筒２２の外表面には、冷却フィン２６
が設けられている。この冷却フィンは断続していて、そ
の高さは環状流路の高さＨよりは小さい。冷却フィン２
６の特徴は、空気の流入方向に対してγの迎え角とβの
傾斜角を有していることである。Cooling fins 26 are provided on the outer surface of the combustion cylinder 22.
Is provided. These cooling fins are intermittent and their height is smaller than the height H of the annular channel. Cooling fin 2
The feature of No. 6 is that it has an attack angle of γ and an inclination angle of β with respect to the inflow direction of air.
【００２５】図４は、燃焼筒２２の外表面の展開図であ
る。FIG. 4 is a developed view of the outer surface of the combustion cylinder 22.
【００２６】各冷却フィン２６は、圧縮空気６の流入方
向に対して迎え角γをなしている。迎え角γを有するフ
ィンの下流には図５に示すような渦が生じ、この渦によ
って、熱伝達率が向上する。最適な迎え角γについて、
要素実験をしたところ図６に示すような結果が得られ
た。本実験のレイノルズ数Ｒｅは、約４０００である。
すなわち、迎え角γが４５度付近で、熱伝達率の無次元
数であるヌッセルト数が最大値をとる。圧力損失や製作
誤差を考慮にいれると、迎え角γは３０から６０度の範
囲とするのが好適である。Each cooling fin 26 forms an angle of attack γ with respect to the inflow direction of the compressed air 6. A vortex as shown in FIG. 5 is generated downstream of the fin having the angle of attack γ, and the vortex improves the heat transfer coefficient. For the optimal angle of attack γ,
As a result of an element experiment, a result as shown in FIG. 6 was obtained. The Reynolds number Re of this experiment is about 4000.
That is, when the angle of attack γ is around 45 degrees, the Nusselt number, which is a dimensionless number of the heat transfer coefficient, takes the maximum value. In consideration of pressure loss and manufacturing error, the angle of attack γ is preferably in the range of 30 to 60 degrees.
【００２７】図７は、図１の燃焼筒２２の中心軸を含む
縦断面で見た環状流路である。FIG. 7 is an annular flow path viewed in a longitudinal section including the central axis of the combustion cylinder 22 of FIG.
【００２８】空気６は左から環状流路内を流れ、燃焼ガ
ス７は燃焼筒２２の内側を右から左へ流れている。燃焼
筒２２の外表面に設けられた冷却フィン２６は、空気流
入方向に対して、傾斜角βだけ上流側に傾いている。図
７に示すように、傾斜角βが９０度より小さいと、冷却
フィン下流側の渦は、環状流路の中央より燃焼筒２２に
近い部分に形成され、燃焼筒外表面の熱伝達を促進する
のに有効であることが判明した。The air 6 flows through the annular flow path from the left, and the combustion gas 7 flows inside the combustion tube 22 from the right to the left. The cooling fins 26 provided on the outer surface of the combustion tube 22 are inclined upstream by an inclination angle β with respect to the air inflow direction. As shown in FIG. 7, when the inclination angle β is smaller than 90 degrees, the vortex on the downstream side of the cooling fin is formed in a portion closer to the combustion cylinder 22 than the center of the annular flow path, and promotes heat transfer on the outer surface of the combustion cylinder. Turned out to be effective.
【００２９】図８は、レイノルズ数Ｒｅが約４０００の
時の要素実験結果で、傾斜角βが６０度付近で、ヌッセ
ルト数が最大となることを示している。やはり、圧力損
失や製作誤差などを考慮すると、傾斜角βは、３０から
９０度未満が好適である。FIG. 8 is a result of an element experiment when the Reynolds number Re is about 4000, and shows that the Nusselt number becomes maximum when the inclination angle β is around 60 degrees. Again, in consideration of pressure loss, manufacturing error, and the like, the inclination angle β is preferably 30 to less than 90 degrees.
【００３０】以上は、冷却フィンを燃焼筒外表面に設け
る場合について述べてきたが、燃焼筒２２とタービン３
を接続する尾筒（トランジションピース）２３の外表面
にも、本発明の冷却フィン２６を適用することができ
る。The case where cooling fins are provided on the outer surface of the combustion cylinder has been described above.
The cooling fins 26 of the present invention can also be applied to the outer surface of the transition piece 23 (transition piece) connecting the cooling fins 26.
【００３１】他の実施例について、次に述べる。Another embodiment will be described below.
【００３２】図９は、図４に対応するもので、燃焼筒２
２の外表面の展開図である。FIG. 9 corresponds to FIG.
2 is a development view of the outer surface of FIG.
【００３３】迎え角γは、必ずしも一方向ではなく、交
互に変化させても良い。図９は、１列目と３列目の冷却
フィン２６は、迎え角がγであるが、２列目の冷却フィ
ン２６の迎え角は−γとなっている。このように配置す
ると、圧縮空気６が蛇行して流れ、高い熱伝達率が得ら
れる。The angle of attack γ is not necessarily in one direction but may be changed alternately. In FIG. 9, the angle of attack of the cooling fins 26 in the first and third rows is γ, but the angle of attack of the cooling fins 26 in the second row is −γ. With this arrangement, the compressed air 6 flows in a meandering manner, and a high heat transfer coefficient is obtained.
【００３４】図１０は、図１に対応するもので、燃焼筒
２２の斜視図である。FIG. 10 corresponds to FIG. 1 and is a perspective view of the combustion tube 22.
【００３５】本図の特徴は、燃焼器外筒２１の内側にガ
イドフィン２７が設けられていることである。このガイ
ドフィン２７は、図１１に示すように、空気６の流入方
向に対して（１８０−β）の傾斜角をもっており、冷却
フィン２６の下流側にできる渦をさらに燃焼筒２２の外
表面近くに押し付ける効果がある。図１２には、ガイド
フィン２７だけで、環状流路の流れを燃焼筒２２の近く
で増速させ、熱伝達率を向上させる効果を示している。The feature of this figure is that a guide fin 27 is provided inside the outer cylinder 21 of the combustor. As shown in FIG. 11, the guide fin 27 has an inclination angle of (180-β) with respect to the inflow direction of the air 6, and further generates a vortex formed downstream of the cooling fin 26 near the outer surface of the combustion cylinder 22. It has the effect of pressing. FIG. 12 shows the effect of increasing the heat transfer coefficient near the combustion cylinder 22 by using the guide fins 27 alone to improve the heat transfer coefficient.
【００３６】図１３は、図１に対応するもので、製作法
の違いを示す図である。図１３において、燃焼筒２２外
表面の冷却フィンは、帯状の金属板に切り目を入れ、一
つおきに切り起こしたものを巻くことによって冷却フィ
ン２６を形成したものである。これに対し、図１のもの
は、遠心鋳造法によって形成するのが良いと考えられ
る。FIG. 13 corresponds to FIG. 1 and shows a difference in the manufacturing method. In FIG. 13, the cooling fins on the outer surface of the combustion cylinder 22 are formed by forming cuts in a band-shaped metal plate and winding the cut and raised portions every other to form the cooling fins 26. On the other hand, it is considered that the structure shown in FIG. 1 is preferably formed by centrifugal casting.
【００３７】図１４は、図１３に対応する燃焼筒２２の
斜視図で、燃焼器外筒２１の内面にガイドフィン２７を
設けたものである。図１４のガイドフィンは、図１０の
ガイドフィンと異なり、迎え角γを有しながらも、輪状
に配置されている。ガイドフィン２７は、比較的低温で
あり、下流側に渦を発生させる必要はないので、形状に
こだわらず、製作しやすい方法を用いれば良い。FIG. 14 is a perspective view of the combustion cylinder 22 corresponding to FIG. 13, in which a guide fin 27 is provided on the inner surface of the outer cylinder 21 of the combustor. The guide fin of FIG. 14 is different from the guide fin of FIG. 10 in that it has an attack angle γ and is arranged in a ring shape. Since the guide fin 27 has a relatively low temperature and does not need to generate a vortex on the downstream side, a method that can be easily manufactured regardless of the shape may be used.
【００３８】[0038]
【発明の効果】以上述べてきたように、本発明によれ
ば、燃焼筒２２の外表面の熱伝達率が向上し、その結果
燃焼筒２２の壁温が低く抑えられるので、燃焼ガス８の
温度を更に高温にすることができ、ガスタービン全体の
効率を向上させることができる。As described above, according to the present invention, the heat transfer coefficient of the outer surface of the combustion tube 22 is improved, and as a result, the wall temperature of the combustion tube 22 is kept low. The temperature can be further increased, and the efficiency of the entire gas turbine can be improved.
【００３９】また、圧縮空気６を途中で燃焼筒２２内部
へ吹き出して、燃焼筒２２内部を冷却する必要がなくな
るので、燃空比を小さくすることができ、その結果ＮＯ
ｘが減って、排ガス９をクリーンに保つことができる。Further, since it is not necessary to blow the compressed air 6 into the combustion cylinder 22 on the way to cool the interior of the combustion cylinder 22, the fuel-air ratio can be reduced, and as a result NO
x is reduced, and the exhaust gas 9 can be kept clean.
【図１】本発明の一実施例に係るガスタービン用燃焼器
の燃焼筒の形状を示す斜視図である。FIG. 1 is a perspective view showing a shape of a combustion cylinder of a gas turbine combustor according to an embodiment of the present invention.
【図２】本発明の一実施例に係るガスタービン全体のシ
ステムフロー図である。FIG. 2 is a system flow diagram of the entire gas turbine according to one embodiment of the present invention.
【図３】本発明の一実施例に係るガスタービン燃焼器の
断面図である。FIG. 3 is a cross-sectional view of a gas turbine combustor according to one embodiment of the present invention.
【図４】本発明の一実施例に係る燃焼筒外表面の展開図
で見た冷却フィンの配置図である。FIG. 4 is a layout view of cooling fins in a development view of an outer surface of a combustion cylinder according to one embodiment of the present invention.
【図５】本発明の一実施例に係る冷却フィンの図４にお
ける作用を示す図である。FIG. 5 is a view showing an operation of the cooling fin according to one embodiment of the present invention in FIG. 4;
【図６】本発明の一実施例に係る冷却フィンの図４にお
ける迎え角γの効果を示す図である。6 is a diagram showing the effect of the angle of attack γ in FIG. 4 of the cooling fin according to one embodiment of the present invention.
【図７】本発明の一実施例に係る環状流路の断面で見た
冷却フィンの形状と作用を示す図である。FIG. 7 is a view showing a shape and an action of a cooling fin as viewed in a cross section of an annular flow channel according to an embodiment of the present invention.
【図８】本発明の一実施例に係る冷却フィンの図７にお
ける傾斜角βの効果を示す図である。8 is a diagram showing the effect of the inclination angle β in FIG. 7 of the cooling fin according to one embodiment of the present invention.
【図９】本発明の他の実施例に係る燃焼筒外表面の展開
図で見た冷却フィンの配置図である。FIG. 9 is a layout view of cooling fins in a development view of an outer surface of a combustion cylinder according to another embodiment of the present invention.
【図１０】本発明の他の実施例に係るガスタービン用燃
焼器の燃焼筒の形状を示す斜視図である。FIG. 10 is a perspective view showing a shape of a combustion cylinder of a gas turbine combustor according to another embodiment of the present invention.
【図１１】本発明の他の実施例に係る環状流路の断面で
見た冷却フィンの形状と作用を示す図である。FIG. 11 is a view showing the shape and operation of a cooling fin as viewed in a cross section of an annular flow channel according to another embodiment of the present invention.
【図１２】本発明の他の実施例に係る環状流路の断面で
見た冷却フィンの形状と作用を示す図である。FIG. 12 is a view showing the shape and operation of a cooling fin as viewed in a cross section of an annular flow channel according to another embodiment of the present invention.
【図１３】本発明の他の実施例に係るガスタービン用燃
焼器の燃焼筒の形状を示す斜視図である。FIG. 13 is a perspective view showing a shape of a combustion cylinder of a gas turbine combustor according to another embodiment of the present invention.
【図１４】本発明の他の実施例に係るガスタービン用燃
焼器の燃焼筒の形状を示す斜視図である。FIG. 14 is a perspective view showing a shape of a combustion cylinder of a gas turbine combustor according to another embodiment of the present invention.
１…圧縮機、２…燃焼器、３…タービン、４…発電機、
５…起動源、６…圧縮空気、７…燃料、８…燃焼ガス、
９…排ガス、２１…燃焼器外筒、２２…燃焼筒、２３…
尾筒、２４…主バーナ、２５…副バーナ、２６…冷却フ
ィン、２７…ガイドフィン。DESCRIPTION OF SYMBOLS 1 ... Compressor, 2 ... Combustor, 3 ... Turbine, 4 ... Generator,
5 start-up source, 6 compressed air, 7 fuel, 8 combustion gas,
9 ... exhaust gas, 21 ... combustor outer cylinder, 22 ... combustion cylinder, 23 ...
Transition tube, 24: Main burner, 25: Sub burner, 26: Cooling fin, 27: Guide fin.
───────────────────────────────────────────────────── フロントページの続き (72)発明者 関原 傑 茨城県土浦市神立町502番地 株式会社日 立製作所機械研究所内 (72)発明者 石橋 洋二 茨城県日立市大みか町七丁目２番１号 株 式会社日立製作所電力・電機開発研究所内 ──────────────────────────────────────────────────続 き Continuing on the front page (72) Inventor Mamoru Sekihara 502 Kandachi-cho, Tsuchiura-city, Ibaraki Pref. Machinery Research Laboratory, Hitachi, Ltd. (72) Inventor Yoji Ishibashi 7-2-1, Omika-cho, Hitachi-shi, Ibaraki Hitachi, Ltd. Power & Electric Development Laboratory
Claims (7)
を燃焼筒（ライナ）の内部で混合して燃焼させるととも
に、圧縮機から送り込まれる圧縮空気を燃焼筒の外周面
に沿って流して該燃焼筒を冷却するガスタービン燃焼器
において、 前記燃焼筒の外周面上に、燃焼筒外表面の展開図におい
て、空気流入方向に対して３０〜６０度の迎え角γを有
する断続する冷却フィンを設けたことを特徴とするガス
タービン燃焼器。The compressed air and fuel fed from a compressor are mixed and burned inside a combustion cylinder (liner), and the compressed air sent from the compressor is caused to flow along the outer peripheral surface of the combustion cylinder. In a gas turbine combustor for cooling a combustion cylinder, intermittent cooling fins having an angle of attack γ of 30 to 60 degrees with respect to an air inflow direction in a development view of an outer surface of the combustion cylinder on an outer peripheral surface of the combustion cylinder. A gas turbine combustor characterized by being provided.
を燃焼筒（ライナ）の内部で混合して燃焼させるととも
に、圧縮機から送り込まれる圧縮空気を燃焼筒の外周面
に沿って流して該燃焼筒を冷却するガスタービン燃焼器
において、 前記燃焼筒の外周面上に、燃焼筒の軸を含む縦断面にお
いて、空気流入方向に対して３０度以上９０度未満の傾
斜角度βを有する断続する冷却フィンを設けたことを特
徴とするガスタービン燃焼器。2. A method according to claim 1, wherein the compressed air and the fuel fed from the compressor are mixed and burned in a combustion cylinder (liner), and the compressed air fed from the compressor flows along the outer peripheral surface of the combustion cylinder. In a gas turbine combustor for cooling a combustion cylinder, on the outer peripheral surface of the combustion cylinder, a vertical section including the axis of the combustion cylinder is intermittently provided with an inclination angle β of 30 degrees or more and less than 90 degrees with respect to an air inflow direction. A gas turbine combustor comprising cooling fins.
を燃焼筒（ライナ）の内部で混合して燃焼させるととも
に、圧縮機から送り込まれる圧縮空気を燃焼筒の外周面
に沿って流して該燃焼筒を冷却するガスタービン燃焼器
において、 前記燃焼筒の外周面上に、燃焼筒外表面の展開図におい
て、空気流入方向に対して３０〜６０度の迎え角γを有
し、かつ、燃焼筒の軸を含む縦断面において、空気流入
方向に対して３０度以上９０度未満の傾斜角度βを有す
る断続する冷却フィンを設けたことを特徴とするガスタ
ービン燃焼器。3. A combustion system in which compressed air and fuel fed from a compressor are mixed and burned in a combustion cylinder (liner), and compressed air sent from the compressor flows along the outer peripheral surface of the combustion cylinder. In a gas turbine combustor for cooling a combustion cylinder, an outer peripheral surface of the combustion cylinder has an attack angle γ of 30 to 60 degrees with respect to an air inflow direction in a development view of an outer surface of the combustion cylinder, and A gas turbine combustor characterized in that intermittent cooling fins having an inclination angle β of not less than 30 degrees and less than 90 degrees with respect to the air inflow direction are provided in a longitudinal section including the axis of the cylinder.
スタービン燃焼器において、燃焼筒に接続する尾筒（ト
ランジションピース）外周上に、空気流入方向に対して
３０〜６０度の迎え角γを有し、かつ、尾筒の軸を含む
縦断面において、空気流入方向に対して３０度以上９０
度未満の傾斜角度βを有する断続する冷却フィンを設け
たことを特徴とするガスタービン燃焼器。4. The gas turbine combustor according to claim 1, wherein the transition piece connected to the combustion cylinder has an angle of 30 to 60 degrees with respect to the air inflow direction. In a longitudinal section having an angle of attack γ and including the axis of the transition piece, at least 30 degrees 90 to the air inflow direction
A gas turbine combustor comprising intermittent cooling fins having an inclination angle β of less than degree.
スタービン燃焼器において、燃焼筒より直径が大きく同
心円筒状に位置する燃焼器外周壁の内面に、迎え角γ，
傾斜角（１８０−β）の断続する冷却フィンを設けたこ
とを特徴とするガスタービン燃焼器。5. The gas turbine combustor according to claim 1, wherein an angle of attack γ,
A gas turbine combustor characterized in that intermittent cooling fins having an inclination angle (180-β) are provided.
スタービン燃焼器において、前記燃焼筒が遠心鋳造法に
より形成されることを特徴とするガスタービン燃焼器。6. The gas turbine combustor according to claim 1, wherein said combustion cylinder is formed by a centrifugal casting method.
スタービン燃焼器において、前記燃焼筒の冷却フィンが
巻フィンによって形成されることを特徴とするガスター
ビン燃焼器。7. The gas turbine combustor according to claim 1, wherein the cooling fins of the combustion cylinder are formed by winding fins.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP12556899A JP2000320837A (en) | 1999-05-06 | 1999-05-06 | Gas turbine combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP12556899A JP2000320837A (en) | 1999-05-06 | 1999-05-06 | Gas turbine combustor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JP2000320837A true JP2000320837A (en) | 2000-11-24 |
Family
ID=14913421
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP12556899A Pending JP2000320837A (en) | 1999-05-06 | 1999-05-06 | Gas turbine combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2000320837A (en) |
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