JP2009052768A - Gas turbine combustion device - Google Patents

Gas turbine combustion device Download PDF

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JP2009052768A
JP2009052768A JP2007217648A JP2007217648A JP2009052768A JP 2009052768 A JP2009052768 A JP 2009052768A JP 2007217648 A JP2007217648 A JP 2007217648A JP 2007217648 A JP2007217648 A JP 2007217648A JP 2009052768 A JP2009052768 A JP 2009052768A
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combustion
burner
gas turbine
injection
shape
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JP5086001B2 (en
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Hiroyuki Kashiwabara
宏行 柏原
Yasushi Yoshino
泰 吉野
Takanobu Yoshimura
孝信 吉村
Takekiyo Kimura
武清 木村
Tadashi Matsumoto
匡史 松本
Junichi Kitajima
潤一 北嶋
Atsushi Horikawa
敦史 堀川
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Kawasaki Heavy Industries Ltd
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Kawasaki Heavy Industries Ltd
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Abstract

<P>PROBLEM TO BE SOLVED: To provide a gas turbine combustion device capable of responding to high-load combustion while maintaining low NO<SB>x</SB>combustion by a surface combustion burner. <P>SOLUTION: The gas turbine combustion device is equipped with a combustion tube having a cylindrical side wall and formed with a combustion chamber inside. The gas turbine combustion device is provided with the surface combustion burner forming a primary combustion area by injecting premixed air from an injection surface formed with many holes to an upstream part of the combustion chamber, and a reheating burner arranged on the side wall of the combustion tube for forming a secondary combustion area on a downstream side of the primary combustion area by injecting fuel into the combustion chamber. <P>COPYRIGHT: (C)2009,JPO&INPIT

Description

本発明は、燃焼にともなって発生する窒素酸化物の排出量を低減しつつ、広い燃焼負荷範囲で作動可能なガスタービン燃焼装置に関する。   The present invention relates to a gas turbine combustion apparatus that can operate in a wide combustion load range while reducing the emission amount of nitrogen oxides generated by combustion.

ガスタービンエンジンにおいては、環境保全への配慮から、燃焼により排出される排ガスの組成に関して厳しい環境基準が設けられており、窒素酸化物（以下、ＮＯｘという）などの有害物質を低減することが求められている。一方、大型のガスタービンや航空機用エンジンでは、低燃費化および高出力化の要請から、圧力比が高く設定される傾向にあり、それに伴って燃焼装置入口における高温・高圧化が進み、この燃焼装置の入口温度の高温化によって燃焼温度が高くなり易いことから、ＮＯｘをむしろ増加させる要因になることが懸念されている。   Gas turbine engines have strict environmental standards regarding the composition of exhaust gas emitted by combustion, considering environmental conservation, and it is required to reduce harmful substances such as nitrogen oxides (hereinafter referred to as NOx). It has been. On the other hand, large gas turbines and aircraft engines tend to have higher pressure ratios due to demands for lower fuel consumption and higher output, and as a result, higher temperatures and higher pressures at the inlet of the combustion device have progressed. Since the combustion temperature tends to increase due to the increase in the inlet temperature of the apparatus, there is a concern that it may be a factor that rather increases NOx.

ガスタービンの燃焼装置において低ＮＯｘ燃焼を実現するために、火炎を安定して燃焼させるメインバーナとして、予混合気を、多数の孔が形成された噴射面から噴射させる面燃焼バーナを備えたものが提案されている（特許文献１）。この面燃焼バーナを使用すると、希薄な予混合気が、噴射面の孔を通ることによって一層均一に混合される。さらに、燃料が狭い噴射口から集中的に噴射される通常のノズル方式のバーナと異なり、予混合気が広い面に均等に分散されて燃焼室内に噴射される。したがって、局所的に火炎温度が高温となる燃焼領域を存在させず、かつ混合気の希薄化により全体的にも火炎温度を低くできることから、ＮＯｘ発生量を効果的に低減できる利点がある。
特表２００２−５３５５９８ In order to realize low NOx combustion in a gas turbine combustion apparatus, a main burner that stably burns a flame is provided with a surface combustion burner that injects premixed gas from an injection surface in which many holes are formed. Has been proposed (Patent Document 1). When this surface combustion burner is used, the lean premixed gas is mixed more uniformly by passing through the holes in the injection surface. Further, unlike a normal nozzle type burner in which fuel is intensively injected from a narrow injection port, the premixed gas is evenly distributed over a wide surface and injected into the combustion chamber. Accordingly, there is no combustion region where the flame temperature is locally high, and the flame temperature can be lowered overall by diluting the air-fuel mixture, so that there is an advantage that the amount of NOx generated can be effectively reduced.
Special table 2002-535598

しかし、従来の面燃焼バーナを用いた燃焼装置においては、面燃焼バーナから噴射される予混合気によって形成される一次燃焼領域によってのみ燃焼領域が構成されており、燃焼負荷の増加に対しては、面燃焼バーナの負荷を増加すること、すなわち、面燃焼バーナから噴射される予混合気の燃料濃度を上げることにより対応する必要がある。この場合、断熱火炎温度が高くなることから、ＮＯｘ排出値を十分低く抑えることができないこと、および、わずかな予混合気の燃料濃度の不均一によって局所的に過度な高温燃焼が生じ、バーナの焼損を引き起こすおそれがあることから、高負荷側への燃焼負荷変動に十分対応しきれないという問題があった。面燃焼バーナを複数本に分割して構成し、作動本数を切り替えることによって燃焼負荷の変動に対応することも考えられるが、燃焼装置の最大定格負荷での燃焼時には上記の問題が発生することには変わりなく、また、コスト面からも望ましい構成とはいえない。   However, in the conventional combustion apparatus using the surface combustion burner, the combustion region is constituted only by the primary combustion region formed by the premixed gas injected from the surface combustion burner. It is necessary to cope by increasing the load of the surface combustion burner, that is, by increasing the fuel concentration of the premixed gas injected from the surface combustion burner. In this case, since the adiabatic flame temperature becomes high, the NOx emission value cannot be kept low enough, and a slight non-uniformity in the fuel concentration of the premixed gas causes excessively high temperature combustion locally. Since there is a possibility of causing burnout, there is a problem that the combustion load fluctuation to the high load side cannot be sufficiently handled. Although it is possible to divide the surface combustion burner into a plurality of parts and respond to fluctuations in the combustion load by switching the number of operations, the above problem will occur at the time of combustion at the maximum rated load of the combustion device Is not changed and is not desirable from the viewpoint of cost.

本発明は、面燃焼バーナによる低温かつ均一な燃焼、すなわち低ＮＯｘ燃焼を維持し、面燃焼バーナの焼損を防止しながら、広い負荷範囲にわたって低ＮＯｘ燃焼可能なガスタービン燃焼装置を提供することを目的とする。   The present invention provides a gas turbine combustion apparatus capable of low NOx combustion over a wide load range while maintaining low temperature and uniform combustion by a surface combustion burner, that is, low NOx combustion, and preventing burning of the surface combustion burner. Objective.

前記した目的を達成するために、本発明に係るガスタービン燃焼装置は、筒状の側壁を有し、内側に燃焼室を形成する燃焼筒と、多数の孔が形成された噴射面から予混合気を前記燃焼室の上流部に噴射して一次燃焼領域を形成させる面燃焼バーナと、前記燃焼筒の側壁に配置され、前記一次燃焼領域の下流側に二次燃焼領域を形成させる追焚バーナとを備えている。   In order to achieve the above-described object, a gas turbine combustion apparatus according to the present invention is premixed from a combustion cylinder having a cylindrical side wall and forming a combustion chamber inside, and an injection surface in which a large number of holes are formed. A surface combustion burner for injecting air into the upstream portion of the combustion chamber to form a primary combustion region, and a remnant burner which is disposed on a side wall of the combustion cylinder and forms a secondary combustion region on the downstream side of the primary combustion region And.

この構成によれば、希薄な予混合気が、多数の孔を持つ噴射面を備えた面燃焼バーナから噴射されて、燃焼室の上流側の一次燃焼領域が形成されるので、低負荷燃焼において断熱火炎温度を低く保ち、ＮＯｘ排出量を低く抑えることができる。さらに、燃焼装置に高負荷燃焼が要求される場合にも、第２のバーナである追焚バーナを作動させて一次燃焼領域の下流側に二次燃焼領域を形成することにより出力を調整できるので、一次燃焼領域における高温・不均一な燃焼が回避される。したがって低ＮＯｘ燃焼を維持し、面燃焼バーナの負荷の増大による焼損を防止しつつ、燃焼装置全体として高負荷燃焼への対応が可能となる。   According to this configuration, the lean premixed gas is injected from the surface combustion burner having the injection surface having a large number of holes to form the primary combustion region on the upstream side of the combustion chamber. The adiabatic flame temperature can be kept low and the NOx emission amount can be kept low. Furthermore, even when high-load combustion is required for the combustion device, the output can be adjusted by operating the tracking burner, which is the second burner, to form a secondary combustion region downstream of the primary combustion region. High temperature and non-uniform combustion in the primary combustion region is avoided. Therefore, it is possible to cope with high-load combustion as a whole combustion apparatus while maintaining low NOx combustion and preventing burnout due to an increase in the load of the surface combustion burner.

前記面燃焼バーナは、好ましくは、前記予混合気を通過させて噴射面から噴射する面燃焼部材と、この面燃焼部材に予混合気を供給するミキサとを有する。このように構成することで、簡易な構造のバーナによって、希薄な予混合気を燃焼室内で均一に燃焼させてＮＯｘ排出量を抑制することができる。   The surface combustion burner preferably includes a surface combustion member that allows the premixed gas to pass through and is injected from an injection surface, and a mixer that supplies the surface combustion member with the premixed gas. With this configuration, the lean premixed gas can be uniformly burned in the combustion chamber and the NOx emission amount can be suppressed by the burner having a simple structure.

前記面燃焼バーナの前記噴射面は、例えば、前記燃焼筒の軸心に垂直な平坦面形状を有するものである。このような形状の採用により、簡易な構成によって均一な一次燃焼領域を形成することができる。   The injection surface of the surface combustion burner has, for example, a flat surface shape perpendicular to the axis of the combustion cylinder. By adopting such a shape, a uniform primary combustion region can be formed with a simple configuration.

あるいは、前記面燃焼バーナの前記噴射面を、次の（ａ）〜（ｇ）のいずれかの形状を有するものとしてもよい。
（ａ）前記燃焼室の上流から下流に向かって先細りの円錐形状。
（ｂ）閉じた下流端面を備えた円筒形状。
（ｃ）前記燃焼筒の軸心を回転対称軸とする曲面形状。ここで曲面とは、滑らかに湾曲した面を意味し、例えば、下流側に膨出する半球形状、椀形形状、半楕円球形状、弾丸形状などである。
（ｄ）閉じた下流端面を備えた多角筒形状。
（ｅ）前記燃焼室の上流から下流に向かって先細りの多角錐形状。
（ｆ）前記燃焼室の上流から下流に向かって先細りの円錐台形状。
（ｇ）前記燃焼室の上流から下流に向かって先細りの多角錐台形状。
前記噴射面をこのような形状とした場合には、燃焼面の面積を増加させることにより、面燃焼バーナ自体の最大燃焼負荷が向上するので、広い負荷範囲にわたって低ＮＯｘ燃焼可能な燃焼装置とすることができる。 Alternatively, the injection surface of the surface combustion burner may have any one of the following shapes (a) to (g).
(A) A conical shape tapered from the upstream to the downstream of the combustion chamber.
(B) A cylindrical shape with a closed downstream end face.
(C) A curved surface shape with the axis of the combustion cylinder as the axis of rotational symmetry. Here, the curved surface means a smoothly curved surface, for example, a hemispherical shape, a bowl shape, a semi-elliptical spherical shape, a bullet shape, or the like that bulges downstream.
(D) Polygonal cylinder shape with a closed downstream end face.
(E) A polygonal pyramid shape that tapers from upstream to downstream of the combustion chamber.
(F) A truncated cone shape that tapers from the upstream to the downstream of the combustion chamber.
(G) A polygonal frustum shape that tapers from the upstream to the downstream of the combustion chamber.
When the injection surface has such a shape, by increasing the area of the combustion surface, the maximum combustion load of the surface combustion burner itself is improved, so that the combustion apparatus is capable of low NOx combustion over a wide load range. be able to.

以上のように、本発明に係るガスタービン燃焼装置によれば、一次燃焼領域を形成させる面燃焼バーナとは別に、二次燃焼領域を形成させる追焚バーナを設けることにより、面燃焼バーナによる低ＮＯｘ燃焼という利点を維持し、かつ面燃焼バーナの負荷増大による焼損を回避しつつ、広い負荷範囲にわたって低ＮＯｘ燃焼が可能となる。   As described above, according to the gas turbine combustion apparatus according to the present invention, by providing the remedy burner for forming the secondary combustion region separately from the surface combustion burner for forming the primary combustion region, Low NOx combustion is possible over a wide load range while maintaining the advantage of NOx combustion and avoiding burnout due to increased load of the surface combustion burner.

以下、本発明の実施形態を図面に従って詳細に説明する。図１は本発明の第１実施形態に係る燃焼装置が適用されるガスタービンエンジンを示す簡略構成図である。ガスタービンエンジンＧＴは圧縮機１、燃焼装置２およびタービン３を主構成要素として構成されており、圧縮機１から供給される圧縮空気を燃焼装置２で燃焼させ、それにより発生する高圧の燃焼ガスをタービン３に供給する。圧縮機１は回転軸５を介してタービン３に連結されて、このタービン３によって駆動される。このガスタービンエンジンＧＴの出力により、発電機または航空機のロータのような負荷４を駆動する。燃焼装置２には、燃料供給装置７から送給される燃料が、燃料制御装置９を介して供給される。燃焼装置２には、キャン型、アニュラー型があるが、本発明に係る実施形態では、主にキャン型について説明する。なお、本発明はアニュラー型にも適用可能である。   Hereinafter, embodiments of the present invention will be described in detail with reference to the drawings. FIG. 1 is a simplified configuration diagram showing a gas turbine engine to which a combustion apparatus according to a first embodiment of the present invention is applied. The gas turbine engine GT includes a compressor 1, a combustion device 2, and a turbine 3 as main components. The compressed air supplied from the compressor 1 is combusted by the combustion device 2, and high-pressure combustion gas generated thereby. Is supplied to the turbine 3. The compressor 1 is connected to the turbine 3 via the rotating shaft 5 and is driven by the turbine 3. A load 4 such as a generator or a rotor of an aircraft is driven by the output of the gas turbine engine GT. The fuel supplied from the fuel supply device 7 is supplied to the combustion device 2 via the fuel control device 9. The combustion apparatus 2 includes a can type and an annular type. In the embodiment according to the present invention, the can type is mainly described. The present invention can also be applied to an annular type.

図２は図１の実施形態に係る燃焼装置２を示す断面図である。この燃焼装置２は、エンジン回転軸心の周りに環状に複数個配置されるもので、内側に燃焼室１０を形成する燃焼筒１２と、多数の孔が形成された噴射面１４ａを有する面燃焼バーナ１４Ａと、燃焼筒１２の側壁１２ａに配置された追焚バーナ１８とを備えている。燃焼筒１２および面燃焼バーナ１４Ａは、燃焼装置２の外筒となる円筒状のハウジングＨに同心状に、すなわち共通の軸心Ｏを有して収容されている。   FIG. 2 is a sectional view showing the combustion apparatus 2 according to the embodiment of FIG. This combustion apparatus 2 is arranged in a plurality of rings around the engine rotation axis, and is a surface combustion having a combustion cylinder 12 forming a combustion chamber 10 inside and an injection surface 14a in which a large number of holes are formed. A burner 14 </ b> A and a memorial burner 18 disposed on the side wall 12 a of the combustion cylinder 12 are provided. The combustion cylinder 12 and the surface combustion burner 14 </ b> A are accommodated concentrically, that is, having a common axis O in a cylindrical housing H that is an outer cylinder of the combustion apparatus 2.

前記ハウジングＨは、その上流側を形成するハウジング上流部Ｈｕと、下流側を形成するハウジング下流部Ｈｄとを主な構成要素としており、ハウジング上流部Ｈｕとハウジング下流部Ｈｄとは、それぞれの接合側端部に設けられた環状のフランジ２０，２２を介してボルト２４により連結されている。また、ハウジングＨは、その下流側端に設けられたフランジ２６を介して、圧縮機１およびタービン３を含むエンジン本体のメインハウジング（図示せず）にボルト（図示せず）により結合されている。一方、ハウジングＨの上流側端にはエンドカバー２８がボルト３０により固定されている。   The housing H is mainly composed of a housing upstream portion Hu that forms the upstream side and a housing downstream portion Hd that forms the downstream side. The housing upstream portion Hu and the housing downstream portion Hd are joined to each other. The bolts 24 are connected via annular flanges 20 and 22 provided at the side end portions. The housing H is coupled to a main housing (not shown) of the engine body including the compressor 1 and the turbine 3 by a bolt (not shown) via a flange 26 provided at the downstream end thereof. . On the other hand, an end cover 28 is fixed to the upstream end of the housing H with bolts 30.

前記燃焼筒１２の上流端には、一端に環状のフランジ部３２ａを有する支持筒３２の他端がボルト３４によって連結されており、支持筒３２のフランジ部３２ａをハウジングＨのハウジング上流部Ｈｕのフランジ２０にボルト３６で連結することにより、燃焼筒１２の上流端部がハウジングＨに固定されている。燃焼筒１２の頂壁中央は、上流側に凹入しており、この凹入部における中央に円形の連通孔１６が形成され、この連通孔１６の周縁部分がバーナ取付座１５とされている。燃焼筒１２への面燃焼バーナ１４Ａの取付構造については、後に詳述する。   The other end of the support cylinder 32 having an annular flange portion 32a at one end is connected to the upstream end of the combustion cylinder 12 by a bolt 34, and the flange portion 32a of the support cylinder 32 is connected to the housing upstream portion Hu of the housing H. The upstream end of the combustion cylinder 12 is fixed to the housing H by being connected to the flange 20 with a bolt 36. The center of the top wall of the combustion cylinder 12 is recessed upstream, and a circular communication hole 16 is formed at the center of the recess, and the peripheral portion of the communication hole 16 is a burner mounting seat 15. The attachment structure of the surface combustion burner 14A to the combustion cylinder 12 will be described in detail later.

燃焼筒１２の下流端部は、タービン部への燃焼ガス導入路である遷移ダクト（図示せず）の入口部に支持されている。ハウジングＨと燃焼筒１２との間に、圧縮機１からの圧縮空気を矢印Ａで示すように燃焼筒１２に対し上流方向に導く空気通路４０が形成されている。さらに、この空気通路４０に面して、支持筒３２の側壁を形成する周壁に複数の空気導入孔４２が周方向に並んで設けられ、空気通路４０を通って送られてきた圧縮空気Ａが、支持筒３２，ハウジングＨの上流部Ｈｕおよびエンドカバー２８によって形成される空気導入空間４４に導入される。   A downstream end portion of the combustion cylinder 12 is supported by an inlet portion of a transition duct (not shown) that is a combustion gas introduction path to the turbine portion. An air passage 40 is formed between the housing H and the combustion cylinder 12 to guide the compressed air from the compressor 1 in the upstream direction with respect to the combustion cylinder 12 as indicated by an arrow A. Furthermore, facing the air passage 40, a plurality of air introduction holes 42 are provided in the circumferential wall forming the side wall of the support cylinder 32 in the circumferential direction, and the compressed air A sent through the air passage 40 is The support cylinder 32, the upstream portion Hu of the housing H, and the end cover 28 are introduced into the air introduction space 44.

燃焼筒１２の上流側の周壁には、１つ又は複数の点火プラグ４６が、ハウジングＨを貫通してハウジングＨに固定されており、面燃焼バーナ１４Ａの噴射面１４ａから噴射された予混合気Ｐに点火して、燃焼筒１２の上流部において一次燃焼領域Ｓ１を形成させる。また、燃焼筒１２における一次燃焼領域Ｓ１よりも下流側には、短いパイプを貫通させて形成された複数の希釈用空気孔４８が配設されており、ハウジングＨにおける各希釈用空気孔４８に対向する部分に、第２のバーナである複数の追焚バーナ１８が、各々の先端部を希釈用空気孔４８に臨ませてハウジングＨのハウジング下流部Ｈｄに取り付けられている。この追焚バーナ１８は、燃料を希釈用空気孔４８を通じて燃焼筒１２内に噴射して、燃焼室１０内で一次燃焼領域Ｓ１の下流側に二次燃焼領域Ｓ２を形成させる。追焚バーナ１８は、燃焼筒１２の軸心Ｏに沿ってほぼ同一の位置、すなわち、ほぼ同一の軸心方向位置に、円周方向に等間隔に複数設けられて、追焚バーナ段１８Ｓを形成している。図２の実施形態ではこの追焚バーナ段１８Ｓを軸心方向に離間して２段設けているが、燃焼装置２に要求される燃焼負荷や寸法などによって、１段としてもよく、３段以上としてもよい。なお、追焚バーナ１８を予混合式のバーナとしてもよい。   One or a plurality of spark plugs 46 are fixed to the housing H through the housing H on the upstream peripheral wall of the combustion cylinder 12, and the premixed gas injected from the injection surface 14a of the surface combustion burner 14A. P is ignited to form a primary combustion region S1 in the upstream portion of the combustion cylinder 12. Further, a plurality of dilution air holes 48 formed by penetrating a short pipe are disposed on the downstream side of the primary combustion region S 1 in the combustion cylinder 12, and each dilution air hole 48 in the housing H is provided in each of the dilution air holes 48. A plurality of remnant burners 18 as second burners are attached to the housing downstream portion Hd of the housing H with their respective leading ends facing the dilution air holes 48 at the opposing portions. The follow-up burner 18 injects fuel into the combustion cylinder 12 through the dilution air hole 48 to form a secondary combustion region S2 in the combustion chamber 10 on the downstream side of the primary combustion region S1. A plurality of the memorial burners 18 are provided at substantially the same position along the axis O of the combustion cylinder 12, that is, at substantially the same axial center position, at equal intervals in the circumferential direction. Forming. In the embodiment of FIG. 2, the memorial burner stage 18S is provided in two stages apart in the axial direction, but may be one stage depending on the combustion load and dimensions required for the combustion device 2, and three or more stages. It is good. The memorial burner 18 may be a premixed burner.

面燃焼バーナ１４Ａは、平坦面形状の噴射面１４ａを有する面燃焼部材５０Ａ、面燃焼部材５０Ａに向けて予混合気Ｐを案内するノズル５２、バーナ取付座１５の連通孔１６およびノズル５２を介して面燃焼部材５０Ａに予混合気Ｐを供給するミキサ５４、および燃料Ｆをミキサ５４に導入する燃料導入通路５６を備えている。面燃焼部材５０Ａは、軸心方向に貫通する多数の孔を有する円板状の部材であり、その円板形状の中心が燃焼筒１２の軸心Ｏ上に配置されて、噴射面１４ａが軸心Ｏに垂直となるように設定されている。本実施形態においては、メタルニットによって面燃焼部材５０Ａを形成しているが、これに限らず、軸心方向に貫通する多数の孔がほぼ均一に分布している部材であれば、面燃焼部材５０Ａとして使用することができる。例えば、ステンレス板のような金属板にパンチングによって孔を開けたパンチングプレート、金属粉、金属繊維、金属網等を焼結した焼結金属、あるいは金属網を積層したものを用いることが可能である。   The surface combustion burner 14A includes a surface combustion member 50A having a flat injection surface 14a, a nozzle 52 for guiding the premixed gas P toward the surface combustion member 50A, the communication hole 16 of the burner mounting seat 15, and the nozzle 52. The mixer 54 for supplying the premixed gas P to the surface combustion member 50 </ b> A and the fuel introduction passage 56 for introducing the fuel F into the mixer 54 are provided. The surface combustion member 50A is a disk-shaped member having a large number of holes penetrating in the axial direction, the center of the disk shape is disposed on the axis O of the combustion cylinder 12, and the injection surface 14a is the shaft. It is set to be perpendicular to the heart O. In the present embodiment, the surface combustion member 50A is formed by metal knit, but the surface combustion member is not limited to this, and any surface combustion member may be used as long as it is a member in which a large number of holes penetrating in the axial direction are substantially uniformly distributed. 50A can be used. For example, it is possible to use a punching plate in which a hole is formed by punching on a metal plate such as a stainless steel plate, a sintered metal obtained by sintering metal powder, a metal fiber, a metal net, or a metal net laminated. .

ノズル５２は上流端の外周に環状のフランジ部５２ａを有する円筒状の部材であり、他端に面燃焼部材５０Ａが接合されている。ノズル５２の上流側に配置されるミキサ５４もほぼ円筒状の部材であり、その下流側端には、ノズル５２のフランジ部５２ａに対応する環状のフランジ部５４ａが設けられている。面燃焼バーナ１４Ａと燃焼筒１２との連結は、次のようにして行われる。凹状のバーナ取付座１５にノズル５２のフランジ部５２ａを嵌め込み、バーナ取付座１５を、ノズル５２の上流側端のフランジ部５２ａとミキサ５４の下流側端のフランジ部５４ａとの間に介在させて、ボルト５５をミキサ５４のフランジ部５４ａおよびバーナ取付座１５の各挿通孔に挿通し、ノズル５２のフランジ部５２ａに設けたねじ孔にねじ込むことにより、ミキサ５４およびノズル５２をバーナ取付座１５に取り付けている。   The nozzle 52 is a cylindrical member having an annular flange portion 52a on the outer periphery of the upstream end, and the surface combustion member 50A is joined to the other end. The mixer 54 disposed on the upstream side of the nozzle 52 is also a substantially cylindrical member, and an annular flange portion 54a corresponding to the flange portion 52a of the nozzle 52 is provided at the downstream end thereof. The surface combustion burner 14A and the combustion cylinder 12 are connected as follows. The flange portion 52 a of the nozzle 52 is fitted into the concave burner mounting seat 15, and the burner mounting seat 15 is interposed between the flange portion 52 a at the upstream end of the nozzle 52 and the flange portion 54 a at the downstream end of the mixer 54. The bolts 55 are inserted into the insertion holes of the flange portion 54a of the mixer 54 and the burner mounting seat 15 and screwed into the screw holes provided in the flange portion 52a of the nozzle 52, whereby the mixer 54 and the nozzle 52 are inserted into the burner mounting seat 15. It is attached.

燃料導入通路５６の本体部５６ａは、ミキサ５４よりも小径の円筒部材により形成されており、その下流側端の外周部とミキサ５４の内周部との間に、軸心Ｏから径方向に放射状に延びる６〜８本の円管からなるスポーク５６ｂが設けられている。スポーク５６ｂの背面には、図３の背面図に示すように、下流側に向く複数の噴射孔５６ｄが径方向に離間して形成されている。図２の燃料導入通路５６の本体部５６ａを通過した燃料Ｆは、さらにスポーク５６ｂの内方を通って、噴射孔５６ｄからミキサ５４内へ噴射される。上記のように６〜８本のスポーク５６ｂを設けることにより、ミキサ５４内へ燃料Ｆを均一に噴射することができる。一方、ミキサ５４の上流開口である空気導入口５４ｂから空気Ａがミキサ５４内に導入され、スポーク５６ｂの噴射孔５６ｄから噴射された燃料Ｆと混合される。スポーク５６ｂのさらに下流側には、燃料Ｆと空気Ａの予混合を促進するための予混合体５８が取り付けられている。予混合体５８は、金属板に複数の孔を開けた板材を用いているが、軸心方向に貫通する多数の孔がほぼ均一に分布している部材であればよい。例えば、ステンレス板のような金属板にパンチングによって孔を開けたパンチングプレート、金属粉、金属繊維、金属網等を焼結した焼結金属、あるいは金属網を積層したものを用いることが可能である。なお、この予混合体５８は軸心方向に離間させて複数設けてもよく、あるいは省略してもよい。   The main body portion 56 a of the fuel introduction passage 56 is formed of a cylindrical member having a smaller diameter than the mixer 54, and extends radially from the axis O between the outer peripheral portion at the downstream end thereof and the inner peripheral portion of the mixer 54. Spokes 56b composed of 6 to 8 circular tubes extending radially are provided. As shown in the rear view of FIG. 3, a plurality of injection holes 56d facing downstream are formed on the rear surface of the spoke 56b so as to be spaced apart from each other in the radial direction. The fuel F that has passed through the main body portion 56a of the fuel introduction passage 56 of FIG. 2 is further injected into the mixer 54 from the injection hole 56d through the inside of the spoke 56b. As described above, the fuel F can be uniformly injected into the mixer 54 by providing the six to eight spokes 56b. On the other hand, air A is introduced into the mixer 54 from the air inlet 54b, which is the upstream opening of the mixer 54, and mixed with the fuel F injected from the injection hole 56d of the spoke 56b. A premixer 58 for promoting premixing of the fuel F and air A is attached further downstream of the spoke 56b. The premixed body 58 uses a plate material in which a plurality of holes are formed in a metal plate, but may be a member in which a large number of holes penetrating in the axial direction are distributed almost uniformly. For example, it is possible to use a punching plate in which a hole is formed by punching on a metal plate such as a stainless steel plate, a sintered metal obtained by sintering metal powder, a metal fiber, a metal net, or a metal net laminated. . A plurality of the premixed bodies 58 may be provided so as to be separated in the axial direction, or may be omitted.

次に、本実施形態に係る燃焼装置２の動作について説明する。図２に示すように、燃料導入通路５６から導入された燃料Ｆは、スポーク５６ｂの内方を通って、噴射孔５６ｄからミキサ５４内へ噴射され、一方、燃焼筒１２の外側の空気通路４０および空気導入孔４２を経て空気導入空間４４に導入された圧縮空気Ａは、面燃焼バーナ１４Ａの空気導入口５４ｂからミキサ５４の内方空間に導入される。燃料Ｆと圧縮空気Ａとは、スポーク５６ｂおよび予混合体５８によって希薄な予混合気Ｐとして混合され、面燃焼部材５０Ａの表面にほぼ均一に分布する多数の孔を介して噴射面１４ａから燃焼室１０内に噴射される。このとき、希薄な予混合気Ｐが、噴射面１４ａから広く均一に分散して噴射されるため、この予混合気Ｐに点火プラグ４６で点火して形成させる一次燃焼領域Ｓ１においては、火炎の断熱温度は全体として低く抑えられ、また局所的に高温となる領域が形成されることもないため、ＮＯｘの発生量は低く抑えられる。   Next, operation | movement of the combustion apparatus 2 which concerns on this embodiment is demonstrated. As shown in FIG. 2, the fuel F introduced from the fuel introduction passage 56 passes through the inside of the spoke 56 b and is injected from the injection hole 56 d into the mixer 54, while the air passage 40 outside the combustion cylinder 12. The compressed air A introduced into the air introduction space 44 through the air introduction hole 42 is introduced into the inner space of the mixer 54 from the air introduction port 54b of the surface combustion burner 14A. The fuel F and the compressed air A are mixed as a lean premixed gas P by the spokes 56b and the premixed body 58, and burned from the injection surface 14a through a large number of holes distributed almost uniformly on the surface of the surface combustion member 50A. It is injected into the chamber 10. At this time, since the lean premixed gas P is sprayed widely and uniformly from the injection surface 14a, in the primary combustion region S1 formed by igniting the premixed gas P with the spark plug 46, the flame The adiabatic temperature can be kept low as a whole, and since no locally high temperature region is formed, the amount of NOx generated can be kept low.

低負荷燃焼時には面燃焼バーナ１４Ａのみを作動させるが、高負荷燃焼時には、面燃焼バーナ１４Ａによる一次燃焼領域Ｓ１での燃焼負荷を変動させることなく、追焚バーナ１８から負荷に応じた量の燃料を噴射して、一次燃焼領域Ｓ１の下流側に二次燃焼領域Ｓ２を形成させることによって、高負荷時の負荷変動に対応する。このとき、一次燃焼領域Ｓ１で発生した高温の燃焼ガス中に、空気および燃料を投入することにより、二次燃焼領域Ｓ２では、燃料によるＮＯｘ還元作用および高温低酸素燃焼でのＮＯｘ排出量の低減効果により、一次燃焼領域での希薄予混合燃焼による低ＮＯｘと相まって、燃焼装置２全体でＮＯｘ排出量が低減されるとともに、要求される必要負荷を満足することが可能となる。その結果、一次燃焼領域Ｓ１においてＮＯｘ発生量が抑えられる状態は維持され、かつ、追加分の負荷を二次燃焼領域Ｓ２からの出力で補うことができるので、燃焼装置２全体として対応できる負荷変動範囲が広くなる。本実施形態に係る燃焼装置２において全負荷の３０％を追焚バーナ１８に負担させた場合と、従来の平面燃焼バーナのみを備え追焚バーナ１８を有しない燃焼装置において全負荷を平面燃焼バーナに負担させた場合とで、高負荷燃焼の比較実験を行ったところ、本実施形態のＮＯｘ排出量は、従来のものに比べて約半分に低減されていた。さらには、高負荷燃焼時でも、噴射面１４ａにおける予混合気濃度の不均一によって引き起こされる面燃焼バーナ１４Ａの焼損を防止することができた。なお、追焚バーナ１８に負担させる負荷は、ＮＯｘ抑制のために、全負荷の５０％未満であり、好ましくは４０％未満である。   Only the surface combustion burner 14A is operated during low load combustion, but during high load combustion, an amount of fuel corresponding to the load from the combustor burner 18 is obtained without changing the combustion load in the primary combustion region S1 by the surface combustion burner 14A. And a secondary combustion region S2 is formed on the downstream side of the primary combustion region S1, thereby responding to load fluctuations during high loads. At this time, by introducing air and fuel into the high-temperature combustion gas generated in the primary combustion region S1, in the secondary combustion region S2, the NOx reduction action by the fuel and the reduction of NOx emissions in the high-temperature low-oxygen combustion are reduced. Due to the effect, combined with low NOx due to lean premixed combustion in the primary combustion region, it is possible to reduce the NOx emission amount in the entire combustion device 2 and to satisfy the required load required. As a result, the state in which the NOx generation amount is suppressed in the primary combustion region S1 is maintained, and the additional load can be supplemented by the output from the secondary combustion region S2, so that the load fluctuation that can be handled as the entire combustion device 2 The range becomes wider. In the combustion apparatus 2 according to the present embodiment, when the remedy burner 18 bears 30% of the total load, and in the combustion apparatus that has only the conventional planar combustion burner and does not have the remedy burner 18, the full load is the planar combustion burner. When a comparative experiment of high-load combustion was performed in the case where the load was imposed on the engine, the NOx emission amount of the present embodiment was reduced by about half compared to the conventional one. Furthermore, even during high-load combustion, burnout of the surface combustion burner 14A caused by non-uniform premixed gas concentration on the injection surface 14a could be prevented. Note that the load imposed on the commemorative burner 18 is less than 50% of the total load and preferably less than 40% in order to suppress NOx.

なお、上記の第１実施形態においては、面燃焼バーナとして、平坦面形状の噴射面１４ａを有する面燃焼バーナ１４Ａを用いたが、噴射面の形状は、曲面を含む下流側へ向かって膨出した形状であってもよい。例えば、図４に示す第２実施形態のように、円錐面形状の噴射面１４Ｂａを有する面燃焼バーナ１４Ｂを使用することができる。面燃焼バーナ１４Ｂは、第１実施形態において、平坦面形状を有する面燃焼部材５０Ａを、燃焼筒１２と同心で下流側に向かって先細りの円錐形状を有する面燃焼部材５０Ｂに置き換えたものであり、そのほかの構造は第１実施形態と同様である。   In the first embodiment, the surface combustion burner 14A having the flat injection surface 14a is used as the surface combustion burner. However, the shape of the injection surface bulges toward the downstream side including the curved surface. The shape may be sufficient. For example, as in the second embodiment shown in FIG. 4, a surface combustion burner 14B having an injection surface 14Ba having a conical surface shape can be used. In the first embodiment, the surface combustion burner 14B is obtained by replacing the surface combustion member 50A having a flat surface shape with a surface combustion member 50B having a conical shape tapered toward the downstream side concentrically with the combustion cylinder 12. Other structures are the same as those in the first embodiment.

さらに、図５〜図１０にそれぞれ示す第３〜第８実施形態のように、面燃焼バーナとして、第１実施形態における面燃焼部材５０Ａを以下の各形状を有する面燃焼部材５０Ｃ〜５０Ｈに置き換えたものを用いることもできる。   Further, as in the third to eighth embodiments shown in FIGS. 5 to 10, as a surface combustion burner, the surface combustion member 50 </ b> A in the first embodiment is replaced with surface combustion members 50 </ b> C to 50 </ b> H having the following shapes. Can also be used.

図５に示す第３実施形態の面燃焼部材５０Ｃは、燃焼筒１２と同心の、円筒部５０Ｃａと下流端面を閉じる端壁部５０Ｃｂとからなる円筒形状を有する。端壁部５０Ｃｂは軸心Ｏに垂直な平坦面であり、円筒部５０Ｃａおよび端壁部５０Ｃｂが面燃焼バーナ１４Ｃの噴射面１４Ｃａを形成している。   A surface combustion member 50C of the third embodiment shown in FIG. 5 has a cylindrical shape that is concentric with the combustion cylinder 12 and includes a cylindrical portion 50Ca and an end wall portion 50Cb that closes the downstream end surface. The end wall portion 50Cb is a flat surface perpendicular to the axis O, and the cylindrical portion 50Ca and the end wall portion 50Cb form the injection surface 14Ca of the surface combustion burner 14C.

図６に示す第４実施形態の面燃焼部材５０Ｄは、燃焼筒１２の軸心Ｏを回転対称軸とする曲面形状、より具体的には、下流側に向かって膨出する半球形状を有する。半球の球面全体が面燃焼バーナ１４Ｄの噴射面１４Ｄａを形成している。   The surface combustion member 50D of the fourth embodiment shown in FIG. 6 has a curved surface shape with the axis O of the combustion cylinder 12 as a rotationally symmetric axis, more specifically, a hemispherical shape that bulges toward the downstream side. The entire spherical surface of the hemisphere forms the injection surface 14Da of the surface combustion burner 14D.

図７に示す第５実施形態の面燃焼部材５０Ｅは、燃焼筒１２と同心の、多角筒部５０Ｅａと下流端を閉じる端壁部５０Ｅｂとからなる多角筒形状を有する。本実施形態では六角筒形状としている。円筒部５０Ｅａおよび端壁部５０Ｅｂが面燃焼バーナ１４Ｅの噴射面１４Ｅａを形成している。   The surface combustion member 50E of the fifth embodiment shown in FIG. 7 has a polygonal cylinder shape that is concentric with the combustion cylinder 12 and includes a polygonal cylinder part 50Ea and an end wall part 50Eb that closes the downstream end. In this embodiment, it is a hexagonal cylinder shape. The cylindrical portion 50Ea and the end wall portion 50Eb form the injection surface 14Ea of the surface combustion burner 14E.

図８に示す第６実施形態の面燃焼部材５０Ｆは、燃焼筒１２と同心の、燃焼室１０の上流から下流に向かって先細りの多角錐形状を有する。本実施形態では六角錘としている。多角錐面全体が面燃焼バーナ１４Ｆの噴射面１４Ｆａを形成している。   The surface combustion member 50F of the sixth embodiment shown in FIG. 8 has a polygonal pyramid shape that is concentric with the combustion cylinder 12 and is tapered from the upstream side to the downstream side of the combustion chamber 10. In this embodiment, a hexagonal weight is used. The entire polygonal pyramid surface forms the injection surface 14Fa of the surface combustion burner 14F.

図９に示す第７実施形態の面燃焼部材５０Ｇは、燃焼筒１２と同心の、燃焼室１０の上流から下流に向かって先細りの円錐台形状を有しており、円錐部５０Ｇａと下流端面を閉じる端壁部５０Ｇｂとからなる。端壁部５０Ｇｂは軸心Ｏに垂直な平坦面であり、円錐部５０Ｇａおよび端壁部５０Ｇｂが燃焼バーナ１４Ｇの噴射面１４Ｇａを形成している。   The surface combustion member 50G of the seventh embodiment shown in FIG. 9 has a truncated cone shape that is concentric with the combustion cylinder 12 from the upstream side to the downstream side of the combustion chamber 10, and has a conical portion 50Ga and a downstream end surface. It consists of a closing end wall 50Gb. The end wall portion 50Gb is a flat surface perpendicular to the axis O, and the conical portion 50Ga and the end wall portion 50Gb form the injection surface 14Ga of the combustion burner 14G.

図１０に示す第８実施形態の面燃焼部材５０Ｈは、燃焼室１０の上流から下流に向かって先細りの多角錐台形状を有しており、燃焼筒１２と同心の、多角錐部５０Ｈａと下流端面を閉じる端壁部５０Ｈｂとからなる。本実施形態では六角錐台としている。端壁部５０Ｈｂは軸心Ｏに垂直な平坦面であり、多角錐部５０Ｈａおよび端壁部５０Ｈｂが燃焼バーナ１４Ｈの噴射面１４Ｈａを形成している。   The surface combustion member 50H of the eighth embodiment shown in FIG. 10 has a polygonal frustum shape that tapers from the upstream to the downstream of the combustion chamber 10, and is concentric with the combustion cylinder 12 and downstream of the polygonal pyramid 50Ha. It consists of an end wall portion 50Hb that closes the end surface. In this embodiment, a hexagonal frustum is used. The end wall portion 50Hb is a flat surface perpendicular to the axis O, and the polygonal pyramid portion 50Ha and the end wall portion 50Hb form the injection surface 14Ha of the combustion burner 14H.

上記の各実施形態における面燃焼部材５０Ｂ〜５０Ｈとして、メタルニットと金属網とを積層した板状部材、ステンレス板のような金属板にパンチングによって孔を開けたパンチングプレート、金属粉、金属繊維、金属網等を焼結した焼結金属、あるいは金属網を積層したものを用いることが可能である。   As the surface combustion members 50B to 50H in each of the above embodiments, a plate-like member obtained by laminating a metal knit and a metal net, a punching plate in which a hole is punched in a metal plate such as a stainless steel plate, metal powder, metal fiber, It is possible to use a sintered metal obtained by sintering a metal net or the like, or a metal net laminated.

燃焼装置２に面燃焼バーナ１４Ａの代わりに面燃焼バーナ１４Ｂ〜１４Ｈを使用しても、予混合気Ｐが広い面に渡って均等に分散噴射されるため、低ＮＯｘ燃焼が可能である。さらに、噴射面１４Ｂａ〜１４Ｈａの各面積が、第１実施形態の噴射面１４ａの面積よりも増大し、燃焼室１０内に噴射できる予混合気量が増加することにより、面燃焼バーナ１４Ａよりも高負荷まで良好な予混合燃焼が可能となる。したがって、追焚バーナ１８の効果と併せて、燃焼装置２全体としての燃焼負荷を一層大きくすることができる。   Even if the surface combustion burners 14B to 14H are used in the combustion device 2 instead of the surface combustion burner 14A, the premixed gas P is uniformly dispersed and injected over a wide surface, so that low NOx combustion is possible. Further, each area of the injection surfaces 14Ba to 14Ha is larger than the area of the injection surface 14a of the first embodiment, and the amount of premixed air that can be injected into the combustion chamber 10 is increased, so that the surface combustion burner 14A is increased. Good premixed combustion is possible up to high loads. Therefore, in addition to the effect of the commemorative burner 18, the combustion load of the entire combustion apparatus 2 can be further increased.

本発明の第１実施形態に係る燃焼装置が適用されるガスタービンエンジンを示す概略図である。1 is a schematic view showing a gas turbine engine to which a combustion apparatus according to a first embodiment of the present invention is applied. 同実施形態に係る燃焼装置を示す断面図である。It is sectional drawing which shows the combustion apparatus which concerns on the same embodiment. 図２の燃焼装置に用いる燃料導入通路のスポークを示す背面図である。It is a rear view which shows the spoke of the fuel introduction channel | path used for the combustion apparatus of FIG. 本発明の第２実施形態に係る燃焼装置を示す断面図である。It is sectional drawing which shows the combustion apparatus which concerns on 2nd Embodiment of this invention. 本発明の第３実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 3rd Embodiment of this invention. 本発明の第４実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 4th Embodiment of this invention. 本発明の第５実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 5th Embodiment of this invention. 本発明の第６実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 6th Embodiment of this invention. 本発明の第７実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 7th Embodiment of this invention. 本発明の第８実施形態に係る燃焼装置に用いる面燃焼部材を示す斜視図である。It is a perspective view which shows the surface combustion member used for the combustion apparatus which concerns on 8th Embodiment of this invention.

符号の説明Explanation of symbols

２ 燃焼装置
１０ 燃焼室
１２ 燃焼筒
１４Ａ〜１４Ｈ 面燃焼バーナ
１４ａ，１４Ｂａ〜１４Ｈａ 噴射面
１８ 追焚バーナ
５０Ａ〜５０Ｈ 面燃焼部材
５４ ミキサ
Ｐ 予混合気
Ｓ１ 一次燃焼領域
Ｓ２ 二次燃焼領域
Ｏ 燃焼筒の軸心 2 Combustion device 10 Combustion chamber 12 Combustion cylinders 14A-14H Surface combustion burners 14a, 14Ba-14Ha Injection surface 18 Combustion burners 50A-50H Surface combustion member 54 Mixer P Premixed gas S1 Primary combustion area S2 Secondary combustion area O Combustion cylinder Axis of

Claims (11)

筒状の側壁を有し、内側に燃焼室を形成する燃焼筒と、
多数の孔が形成された噴射面から予混合気を前記燃焼室の上流部に噴射して一次燃焼領域を形成させる面燃焼バーナと、
前記燃焼筒の側壁に配置され、前記一次燃焼領域の下流側に二次燃焼領域を形成させる追焚バーナとを備えるガスタービン燃焼装置。 A combustion cylinder having a cylindrical side wall and forming a combustion chamber inside;
A surface combustion burner for injecting premixed gas from an injection surface formed with a large number of holes to an upstream portion of the combustion chamber to form a primary combustion region;
A gas turbine combustion apparatus comprising: a combustor burner disposed on a side wall of the combustion cylinder and forming a secondary combustion region downstream of the primary combustion region. 請求項１において、前記面燃焼バーナは、前記予混合気を通過させて噴射面から噴射する面燃焼部材と、この面燃焼部材に予混合気を供給するミキサとを有するガスタービン燃焼装置。   2. The gas turbine combustion apparatus according to claim 1, wherein the surface combustion burner includes a surface combustion member that allows the premixed gas to pass through and is injected from an injection surface, and a mixer that supplies the surface combustion member with the premixed gas. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼筒の軸心に垂直な平坦面形状を有するガスタービン燃焼装置。   3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a flat surface shape perpendicular to an axis of the combustion cylinder. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼室の上流から下流に向かって先細りの円錐形状を有するガスタービン燃焼装置。   3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a conical shape tapered from an upstream side to a downstream side of the combustion chamber. 請求項１または２において、前記面燃焼バーナの噴射面が、閉じた下流端面を備えた円筒形状を有するガスタービン燃焼装置。   The gas turbine combustion apparatus according to claim 1 or 2, wherein an injection surface of the surface combustion burner has a cylindrical shape having a closed downstream end surface. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼筒の軸心を回転対称軸とする曲面形状を有するガスタービン燃焼装置。   3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a curved surface shape in which an axis center of the combustion cylinder is a rotationally symmetric axis. 請求項６において、前記面燃焼バーナの噴射面が、下流側に向かって膨出する半球形状を有するガスタービン燃焼装置。   7. The gas turbine combustion apparatus according to claim 6, wherein an injection surface of the surface combustion burner has a hemispherical shape that bulges toward the downstream side. 請求項１または２において、前記面燃焼バーナの噴射面が、閉じた下流端面を備えた多角筒形状を有するガスタービン燃焼装置。   The gas turbine combustion apparatus according to claim 1 or 2, wherein an injection surface of the surface combustion burner has a polygonal cylindrical shape having a closed downstream end surface. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼室の上流から下流に向かって先細りの多角錐形状を有するガスタービン燃焼装置。   3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a polygonal pyramid shape that tapers from upstream to downstream of the combustion chamber. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼室の上流から下流に向かって先細りの円錐台形状を有するガスタービン燃焼装置。   3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a truncated cone shape that is tapered from an upstream side to a downstream side of the combustion chamber. 請求項１または２において、前記面燃焼バーナの噴射面が、前記燃焼室の上流から下流に向かって先細りの多角錐台形状を有するガスタービン燃焼装置。
3. The gas turbine combustion apparatus according to claim 1, wherein an injection surface of the surface combustion burner has a polygonal truncated pyramid shape that tapers from upstream to downstream of the combustion chamber.
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