JP5316947B2 - Combustor for micro gas turbine - Google Patents

Combustor for micro gas turbine Download PDF

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JP5316947B2
JP5316947B2 JP2009151897A JP2009151897A JP5316947B2 JP 5316947 B2 JP5316947 B2 JP 5316947B2 JP 2009151897 A JP2009151897 A JP 2009151897A JP 2009151897 A JP2009151897 A JP 2009151897A JP 5316947 B2 JP5316947 B2 JP 5316947B2
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元英 村山
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Description

本発明は、発電装置および推進装置に適用するためのマイクロガスタービン用燃焼器に関する。   The present invention relates to a combustor for a micro gas turbine to be applied to a power generation device and a propulsion device.

ロボットの駆動電源、緊急時の携帯電源として、レシプロエンジンより軽く静かな発電用超小型マイクロガスタービンの開発が進められており、その燃焼器として超小型燃焼器が要望されている。   Development of an ultra-compact micro gas turbine for power generation that is lighter and quieter than a reciprocating engine as a driving power source for a robot and a portable power source in an emergency is underway, and an ultra-compact combustor is required as the combustor.

このようなマイクロガスタービン用燃焼器は、小型であるとともに、作動の安定性、排気の清浄性が重要であり、例えば特許文献１、２が既に提案されている。   Such a combustor for a micro gas turbine is small in size, and the stability of operation and the cleanliness of exhaust are important. For example, Patent Documents 1 and 2 have been proposed.

米国特許第６，６８４，６４２号明細書，“ＧＡＳ ＴＵＲＢＩＮＥ ＥＮＧＩＮＥ ＨＡＶＩＮＧ Ａ ＭＵＬＴＩ−ＳＴＡＧＥ ＭＵＬＴＩ−ＰＬＡＮＥ ＣＯＭＢＵＳＴＩＯＮ ＳＹＳＴＥＭ”US Pat. No. 6,684,642, “GAS TURBINE ENGINE HAVING A MULTI-STAGE MULTI-PLANE COMBUSTION SYSTEM” 国際公開第２００８／０４７８２５号公報、「ガスタービン燃焼器」International Publication No. 2008/047825, “Gas Turbine Combustor”

上述したマイクロガスタービン用燃焼器は、小型であるとともに、作動の安定性、排気の清浄性が重要となる。
例えば、数百Ｗ容量の小型発電装置を想定した場合、経験則から外挿すると、マイクロガスタービン用燃焼器の燃焼室容積は１００ｃｍ３程度となる。
しかし、従来このような小型燃焼室においては、安定した着火性能、高い燃焼効率、低いＣＯ濃度及びＮＯｘを達成することはできなかった。 The above-described combustor for a micro gas turbine is small in size, and operation stability and exhaust cleanliness are important.
For example, assuming a small power generator with a capacity of several hundred W, extrapolating from a rule of thumb, the combustion chamber volume of the combustor for a micro gas turbine is about 100 cm 3 .
However, conventionally, in such a small combustion chamber, stable ignition performance, high combustion efficiency, low CO concentration and NOx could not be achieved.

特に、可搬性が良いことから液体燃料（例えば灯油）を燃料としたマイクロガスタービン用燃焼器が望まれているが、このような液焚きのマイクロガスタービン用燃焼器では燃料流量が数ｍＬ／ｍｉｎと極めて小流量となるため、燃料の十分な微粒化を行うことが難しく、良好な燃焼を行うことが困難であるため、液焚きでは特に、着火、燃焼安定範囲が十分でなく、低負荷時にはＣＯ濃度や未燃分が高く、臭いやエミッションの排出が問題であった。   In particular, a micro gas turbine combustor using liquid fuel (for example, kerosene) as a fuel is desired because of its good portability. In such a liquid fired micro gas turbine combustor, the fuel flow rate is several mL / Since the flow rate is extremely small, it is difficult to sufficiently atomize the fuel, and it is difficult to perform good combustion. Occasionally, CO concentration and unburned content were high, and emission of odors and emissions was a problem.

本発明は上述した問題点に鑑みて創案されたものである。すなわち、本発明の目的は、小型燃焼室において、安定した着火性能、高い燃焼効率、低いＣＯ濃度及びＮＯｘを達成することができるマイクロガスタービン用燃焼器を提供することにある。   The present invention has been made in view of the above-described problems. That is, an object of the present invention is to provide a combustor for a micro gas turbine that can achieve stable ignition performance, high combustion efficiency, low CO concentration and NOx in a small combustion chamber.

本発明によれば、中心軸を囲み互いに同心かつ円筒形のインナーライナ及びアウターライナと、燃料噴射と着火を行うバーナ部を備え、内部に中空円筒形の燃焼室を形成するマイクロガスタービン用燃焼器であって、
前記燃焼室は、バーナ部に設けられ外径が相対的に小さい１次燃焼室と、該１次燃焼室の下流側に位置し外径が相対的に大きい２次燃焼室とからなり、
前記１次燃焼室は、上流側の着火室と、下流側の急速希釈室とからなり、その間に１次燃焼室の外径を狭める円環状の中間絞りを有し、
前記着火室内で燃料濃度の高い予混合旋回流を形成して着火し、前記急速希釈室内で旋回火炎を急速希釈する、ことを特徴とするマイクロガスタービン用燃焼器が提供される。 According to the present invention, combustion for a micro gas turbine is provided that includes a cylindrical inner liner and outer liner that surround a central axis and a cylindrical inner liner, and a burner portion that performs fuel injection and ignition, and forms a hollow cylindrical combustion chamber therein. A vessel,
The combustion chamber includes a primary combustion chamber that is provided in the burner portion and has a relatively small outer diameter, and a secondary combustion chamber that is located downstream of the primary combustion chamber and has a relatively large outer diameter.
The primary combustion chamber is composed of an upstream ignition chamber and a downstream rapid dilution chamber, and has an annular intermediate throttle for narrowing the outer diameter of the primary combustion chamber,
There is provided a combustor for a micro gas turbine, characterized in that a premixed swirling flow having a high fuel concentration is formed and ignited in the ignition chamber, and a swirling flame is rapidly diluted in the rapid dilution chamber.

本発明の好ましい実施形態によれば、さらに、前記着火室に着火用空気を外部から導入し、かつ急速希釈室に希釈用空気を外部から導入して、中心軸を囲む旋回空気流を形成する旋回空気流形成装置と、
前記着火室内の旋回空気流の旋回方向に向けて燃料を噴射し予混合旋回流を形成する液体燃料噴射装置と、
前記着火室内の予混合旋回流に着火して管状火炎面を形成する着火装置とを備える。 According to a preferred embodiment of the present invention, further, ignition air is introduced from the outside into the ignition chamber and dilution air is introduced from the outside into the rapid dilution chamber to form a swirling air flow surrounding the central axis. A swirling airflow forming device;
A liquid fuel injection device for injecting fuel in a swirling direction of a swirling air flow in the ignition chamber to form a premixed swirling flow;
An ignition device that ignites the premixed swirl flow in the ignition chamber to form a tubular flame surface.

また、前記旋回空気流形成装置は、バーナ部に設けられ、内側に前記１次燃焼室を形成するアニュラー型部材と、
該アニュラー型部材の外面から前記着火室及び急速希釈室内の前記旋回空気流の旋回方向に向けてそれぞれ貫通する着火用空気孔と希釈用空気孔とを有する。 Further, the swirling air flow forming device is provided in a burner portion, and an annular member that forms the primary combustion chamber on the inner side,
There are ignition air holes and dilution air holes penetrating from the outer surface of the annular member toward the swirling direction of the swirling air flow in the ignition chamber and the rapid dilution chamber, respectively.

また、前記燃料噴射装置は、前記燃焼用空気孔を通り前記着火室内の旋回空気流中に燃料を噴射する燃料噴射ノズルを有する、ことが好ましい。   The fuel injection device preferably includes a fuel injection nozzle that injects fuel into the swirling air flow in the ignition chamber through the combustion air hole.

上記本発明の構成によれば、アニュラー型の燃焼室が１００ｃｍ３以下の小型燃焼室の場合でも、安定した燃焼が可能であり、高い燃焼効率が得られることが、後述する実施例により確認された。 According to the configuration of the present invention, it is confirmed by the examples described later that stable combustion is possible and high combustion efficiency is obtained even when the annular combustion chamber is a small combustion chamber of 100 cm 3 or less. It was.

特に、１次燃焼室が着火室と急速希釈室とからなり、その間に１次燃焼室の外径を狭める円環状の中間絞りを有するので、中間絞りより着火室の着火用空気を調整することにより着火室内の燃料濃度を高く設定でき、燃焼安定性を高めることができ、これにより着火時やアイドル時の排ガス臭いや未燃分の排出を抑えることができる。また、中間絞りにより２次燃焼室側の急速希釈室の希釈用空気を調整することにより旋回火炎を急速希釈してＮＯｘも低減できる。
In particular, the primary combustion chamber is composed of an ignition chamber and a rapid dilution chamber, and has an annular intermediate throttle that narrows the outer diameter of the primary combustion chamber, so that the ignition air in the ignition chamber is adjusted from the intermediate throttle. As a result, the fuel concentration in the ignition chamber can be set high, and the combustion stability can be enhanced, thereby suppressing the exhaust gas odor and unburned emissions during ignition and idling. Further, by adjusting the dilution air in the rapid dilution chamber on the secondary combustion chamber side with the intermediate throttle, the swirling flame can be rapidly diluted to reduce NOx.

本発明によるマイクロガスタービン用燃焼器の第１実施形態図である。1 is a first embodiment of a combustor for a micro gas turbine according to the present invention. 図１の燃焼器の燃焼試験結果である。It is a combustion test result of the combustor of FIG. 本発明による燃焼器の試験装置の構成図である。It is a block diagram of the testing apparatus of the combustor by this invention. 本発明によるマイクロガスタービン用燃焼器の第２実施形態図である。It is 2nd Embodiment figure of the combustor for micro gas turbines by this invention.

以下、本発明の好ましい実施例を図面を参照して説明する。なお、各図において共通する部分には同一の符号を付し、重複した説明を省略する。   Hereinafter, preferred embodiments of the present invention will be described with reference to the drawings. In addition, the same code | symbol is attached | subjected to the common part in each figure, and the overlapping description is abbreviate | omitted.

図１は、本発明によるマイクロガスタービン用燃焼器の第１実施形態図であり、（Ａ）は縦断面図、（Ｂ）はそのＡ−Ａ断面図である。
この図において、本発明のマイクロガスタービン用燃焼器１０（以下、単に「燃焼器」と呼ぶ）は、インナーライナ１２、アウターライナ１４、及びバーナ部１６を備える。
インナーライナ１２及びアウターライナ１４は、それぞれ円筒形であり、中心軸Ｚ−Ｚを囲み互いに同心に形成されている。 FIG. 1 is a diagram showing a first embodiment of a combustor for a micro gas turbine according to the present invention, in which (A) is a longitudinal sectional view and (B) is an AA sectional view thereof.
In this figure, a combustor 10 for micro gas turbine of the present invention (hereinafter simply referred to as “combustor”) includes an inner liner 12, an outer liner 14, and a burner portion 16.
The inner liner 12 and the outer liner 14 are each cylindrical, and are formed concentrically with respect to the central axis ZZ.

バーナ部１６は、インナーライナ１２とアウターライナ１４の上流側端部（この図で下端）を塞ぐ円環状の円板を有する。インナーライナ１２とアウターライナ１４の下流側端部（この図で上端）は発生した燃焼排ガス９をタービン２と排気管６を介して外部に排気するために開口している。
この燃焼器１０の燃焼室１８は、インナーライナ１２とアウターライナ１４で囲まれるほぼアニュラー型の領域である。 The burner portion 16 has an annular disc that closes the upstream end portions (lower ends in this figure) of the inner liner 12 and the outer liner 14. The downstream end portions (upper end in this figure) of the inner liner 12 and the outer liner 14 are opened to exhaust the generated combustion exhaust gas 9 to the outside through the turbine 2 and the exhaust pipe 6.
The combustion chamber 18 of the combustor 10 is a substantially annular region surrounded by the inner liner 12 and the outer liner 14.

図１（Ａ）において、燃焼器１０の燃焼室１８は、１次燃焼室１８ａと２次燃焼室１８ｂからなる。
１次燃焼室１８ａは、燃焼室１８のエンドライナ１２側に設けられ、外径Ｄ１が相対的に小さく形成されている。また、２次燃焼室１８ｂは、１次燃焼室１８ａの下流側（図で上側）に位置し、外径Ｄ２が相対的に大きく形成されている。 In FIG. 1A, the combustion chamber 18 of the combustor 10 includes a primary combustion chamber 18a and a secondary combustion chamber 18b.
The primary combustion chamber 18a is provided on the end liner 12 side of the combustion chamber 18, and has an outer diameter D1 that is relatively small. Further, the secondary combustion chamber 18b is located on the downstream side (upper side in the drawing) of the primary combustion chamber 18a, and has an outer diameter D2 that is relatively large.

図１（Ａ）において、１次燃焼室１８ａは、着火室１９ａと急速希釈室１９ｂとからなり、その間に１次燃焼室１８ａの外径Ｄ１を狭める円環状の中間絞り２０を有する。中間絞り２０は内径Ｄ３の中心孔を有する。   In FIG. 1A, the primary combustion chamber 18a includes an ignition chamber 19a and a rapid dilution chamber 19b, and has an annular intermediate throttle 20 that narrows the outer diameter D1 of the primary combustion chamber 18a. The intermediate aperture 20 has a central hole with an inner diameter D3.

後述する実施例１において、燃焼室容積は５０ｃｍ３であり、１次燃焼室１８ａの外径Ｄ１と２次燃焼室１８ｂの外径Ｄ２との比率は、１：１．３６、１次燃焼室１８ａの外径Ｄ１と中間絞り２０の内径Ｄ３の比率は、１：０．９である。
しかし、本発明はこれに限定されず、任意に変更することができる。 In Example 1 to be described later, the combustion chamber volume is 50 cm 3 , and the ratio of the outer diameter D1 of the primary combustion chamber 18a to the outer diameter D2 of the secondary combustion chamber 18b is 1: 1.36, the primary combustion chamber. The ratio of the outer diameter D1 of 18a and the inner diameter D3 of the intermediate diaphragm 20 is 1: 0.9.
However, the present invention is not limited to this, and can be arbitrarily changed.

図１（Ａ）（Ｂ）において、本発明の燃焼器１０は、さらに旋回空気流形成装置２２、液体燃料噴射装置２４、及び着火装置２６を備える。
旋回空気流形成装置２２は、着火室１９ａに着火用空気７ａを外部から導入し、急速希釈室１９ｂに希釈用空気７ｂを外部から導入して、中心軸Ｚ−Ｚを囲む旋回空気流を形成する。
液体燃料噴射装置２４は、着火室１９ａ内に形成された旋回空気流の旋回方向に向けて液体燃料８を噴射し予混合旋回流を形成する。
着火装置２６は、例えば周知の点火栓であり、形成された予混合旋回流に着火して管状火炎面１１を形成する。 1A and 1B, the combustor 10 of the present invention further includes a swirling air flow forming device 22, a liquid fuel injection device 24, and an ignition device 26.
The swirling air flow forming device 22 introduces the ignition air 7a from the outside into the ignition chamber 19a and introduces the diluting air 7b from the outside into the rapid dilution chamber 19b to form a swirling air flow surrounding the central axis ZZ. To do.
The liquid fuel injection device 24 injects the liquid fuel 8 toward the swirling direction of the swirling air flow formed in the ignition chamber 19a to form a premixed swirling flow.
The ignition device 26 is, for example, a known spark plug, and ignites the formed premixed swirl flow to form the tubular flame surface 11.

旋回空気流形成装置２２は、この例では、アニュラー型部材２３と着火用空気孔２３ａと希釈用空気孔２３ｂからなる。アニュラー型部材２３は、アウターライナ１４内面のエンドライナ側端部に設けられ、内側に１次燃焼室１８ａを形成する。着火用空気孔２３ａは、アニュラー型部材２３の外面から着火室１９ａ内の旋回空気流の旋回方向に向けて貫通する。希釈用空気孔２３ｂは、アニュラー型部材２３の外面から急速希釈室１９ｂ内の旋回空気流の旋回方向に向けて貫通する。   In this example, the swirling air flow forming device 22 includes an annular member 23, an ignition air hole 23a, and a dilution air hole 23b. The annular member 23 is provided at an end liner side end of the inner surface of the outer liner 14 and forms a primary combustion chamber 18a on the inner side. The ignition air hole 23a penetrates from the outer surface of the annular member 23 toward the swirling direction of the swirling air flow in the ignition chamber 19a. The dilution air hole 23b penetrates from the outer surface of the annular member 23 toward the swirling direction of the swirling air flow in the rapid dilution chamber 19b.

液体燃料噴射装置２４は、この例では、着火用空気孔２３ａを通り着火室１９ａ内の旋回空気流中にガス燃料８（例えばプロパン）を噴射する燃料噴射ノズルである。   In this example, the liquid fuel injection device 24 is a fuel injection nozzle that injects the gas fuel 8 (for example, propane) into the swirling air flow in the ignition chamber 19a through the ignition air hole 23a.

この例において、着火用空気孔２３ａは、周方向に同一間隔で２箇所設けられ、希釈用空気孔２３ｂは、周方向に同一間隔で４箇所設けられており、燃料噴射ノズル２４は、各着火用空気孔２３ａに計２本設けられている。
この構成により、各着火用空気孔２３ａから着火室１９ａ内に外部から着火用空気７ａを導入して中心軸Ｚ−Ｚを囲む旋回空気流を形成することができる。
また、液体燃料噴射装置２４から着火室１９ａ内に形成された旋回空気流の旋回方向に向けて液体燃料８を噴射し予混合旋回流を形成することができる。
さらに、着火装置２６で着火室１９ａに形成された予混合旋回流に着火して管状火炎面１１を形成することができる。 In this example, two ignition air holes 23a are provided at the same interval in the circumferential direction, four dilution air holes 23b are provided at the same interval in the circumferential direction, and the fuel injection nozzle 24 is provided for each ignition. A total of two air holes 23a are provided.
With this configuration, it is possible to form a swirling air flow surrounding the central axis ZZ by introducing the ignition air 7a from the outside into the ignition chamber 19a from each ignition air hole 23a.
Further, it is possible to inject the liquid fuel 8 from the liquid fuel injection device 24 toward the swirling direction of the swirling air flow formed in the ignition chamber 19a to form a premixed swirling flow.
Further, the tubular flame surface 11 can be formed by igniting the premixed swirl flow formed in the ignition chamber 19 a by the ignition device 26.

なお、着火用空気孔２３ａと希釈用空気孔２３ｂは、周方向に１箇所以上あればよい。また、燃料噴射ノズル２４も、周方向に１箇所以上あればよい。また、各寸法は、この実施例に限定されず、任意に変更することができる。
さらに、旋回空気流形成装置２２は、この例に限定されず、燃焼器入口にスワーラを設け、燃焼器周方向全体にわたり旋回する空気流を形成するようにしてもよい。 The ignition air hole 23a and the dilution air hole 23b may be at least one place in the circumferential direction. Further, the fuel injection nozzle 24 may be at least one place in the circumferential direction. Moreover, each dimension is not limited to this Example, It can change arbitrarily.
Further, the swirling air flow forming device 22 is not limited to this example, and a swirler may be provided at the combustor inlet to form an air flow swirling over the entire combustor circumferential direction.

図２は、図１の燃焼器の燃焼試験結果である。なおこの試験では、燃料としてプロパンガスを用い、着火特性を試験した。
この図において、横軸は空気流量、縦軸は燃料流量、図中の◆は上述した中間絞り有り、■は中間絞り無しの場合の着火限界を示しており、それより空気流量が少ない領域では着火ができなくなる。中間絞り無しでは空気流量が多い条件で着火できなくなるが、中間絞り有りでは少ない燃料流量で空気流量が多い条件でも着火可能である。 FIG. 2 shows a combustion test result of the combustor of FIG. In this test, propane gas was used as the fuel and the ignition characteristics were tested.
In this figure, the horizontal axis is the air flow rate, the vertical axis is the fuel flow rate, ◆ in the figure is the ignition limit with the above-mentioned intermediate restriction, and ■ is the ignition limit when there is no intermediate restriction. I cannot ignite. Without an intermediate throttle, it becomes impossible to ignite under conditions with a large air flow rate, but with an intermediate throttle, ignition is possible even under conditions with a small fuel flow rate and a large air flow rate.

図２の試験結果から、１次燃焼室１８ａが、着火室１９ａと急速希釈室１９ｂとからなり、その間に１次燃焼室１８ａの外径を狭める円環状の中間絞り２０を有するので、着火用空気７ａを調整することにより着火室１９ａ内の燃料濃度を高く設定でき、着火性能を高めることができ、これにより着火時やアイドル時の排ガス臭いや未燃分の排出を抑えることができる。また、中間絞り２０より２次燃焼室側の急速希釈室１９ｂの希釈用空気を調整することにより旋回火炎を急速希釈してＮＯｘも低減できることが確認された。   From the test results of FIG. 2, the primary combustion chamber 18a is composed of an ignition chamber 19a and a rapid dilution chamber 19b, and has an annular intermediate throttle 20 for narrowing the outer diameter of the primary combustion chamber 18a. By adjusting the air 7a, the fuel concentration in the ignition chamber 19a can be set high, and the ignition performance can be enhanced, thereby suppressing the exhaust gas odor and unburned emissions during ignition and idling. It was also confirmed that the swirling flame can be rapidly diluted to reduce NOx by adjusting the dilution air in the rapid dilution chamber 19b on the secondary combustion chamber side from the intermediate throttle 20.

（実験装置および方法）
図３は、本発明によるマイクロガスタービン用燃焼器の第２実施形態図である。
図１のガス焚き燃焼器との違いは、液体燃料用に噴射弁と点火栓を変えた点であり、その他の基本構造は同一である。 (Experimental equipment and method)
FIG. 3 is a diagram showing a second embodiment of a combustor for a micro gas turbine according to the present invention.
The difference from the gas-fired combustor in FIG. 1 is that the injection valve and spark plug are changed for liquid fuel, and the other basic structure is the same.

図４は、図３の燃焼器の燃焼試験結果である。なおこの試験では、燃料として灯油を用い、燃焼安定性の吹き消え限界を試験した。
この図において、横軸は空気流量、縦軸は燃料流量、図中の◆は上述した中間絞り有り、■は中間絞り無しの場合を示している。 FIG. 4 shows the result of the combustion test of the combustor of FIG. In this test, kerosene was used as the fuel, and the blowout limit of combustion stability was tested.
In this figure, the horizontal axis indicates the air flow rate, the vertical axis indicates the fuel flow rate, ♦ in the figure indicates the case with the above-described intermediate restriction, and ■ indicates the case without the intermediate restriction.

図２の試験結果から、１次燃焼室１８ａが、着火室１９ａと急速希釈室１９ｂとからなり、その間に１次燃焼室１８ａの外径を狭める円環状の中間絞り２０を有するので、着火用空気７ａを調整することにより着火室１９ａ内の燃料濃度を高く設定でき、燃焼安定性を高めることができ、これにより着火時やアイドル時の排ガス臭いや未燃分の排出を抑えることができる。   From the test results of FIG. 2, the primary combustion chamber 18a is composed of an ignition chamber 19a and a rapid dilution chamber 19b, and has an annular intermediate throttle 20 for narrowing the outer diameter of the primary combustion chamber 18a. By adjusting the air 7a, the fuel concentration in the ignition chamber 19a can be set high, and the combustion stability can be increased, thereby suppressing the exhaust gas odor and unburned emissions during ignition and idling.

なお、本発明は上述した実施の形態に限定されず、本発明の要旨を逸脱しない範囲で種々の変更を加え得ることは勿論である。   In addition, this invention is not limited to embodiment mentioned above, Of course, a various change can be added in the range which does not deviate from the summary of this invention.

２ タービン、６ 排気管、
７ａ 着火用空気、７ｂ 希釈用空気、
８ 液体燃料、９ 燃焼排ガス、
１０ マイクロガスタービン用燃焼器（燃焼器）、
１１ 管状火炎面、１２ インナーライナ、１２ａ 下流側端部、
１４ アウターライナ、１６ バーナ部、
１８ 燃焼室、１８ａ １次燃焼室、１８ｂ ２次燃焼室、
１９ａ 着火室、１９ｂ 急速希釈室、２０ 中間絞り、
２２ 旋回空気流形成装置、２３ アニュラー型部材、
２３ａ，２３ｂ 燃焼用空気孔、
２４ 液体燃料噴射装置（燃料噴射ノズル）、
２６ 着火装置 2 turbine, 6 exhaust pipe,
7a Air for ignition, 7b Air for dilution,
8 liquid fuel, 9 flue gas,
10 Combustor for micro gas turbine (combustor),
11 tubular flame surface, 12 inner liner, 12a downstream end,
14 outer liner, 16 burner section,
18 combustion chamber, 18a primary combustion chamber, 18b secondary combustion chamber,
19a ignition chamber, 19b rapid dilution chamber, 20 intermediate throttle,
22 swirling air flow forming device, 23 annular type member,
23a, 23b combustion air holes,
24 Liquid fuel injection device (fuel injection nozzle),
26 Ignition system

Claims (3)

中心軸を囲み互いに同心かつ円筒形のインナーライナ及びアウターライナと、燃料噴射と着火を行うバーナ部を備え、内部に中空円筒形の燃焼室を形成するマイクロガスタービン用燃焼器であって、
前記燃焼室は、エンドライナ側に設けられ外径が相対的に小さい１次燃焼室と、該１次燃焼室の下流側に位置し外径が相対的に大きい２次燃焼室とからなり、
前記１次燃焼室は、エンドライナ側の着火室と、２次燃焼室側の急速希釈室とからなり、その間に１次燃焼室の外径を狭める円環状の中間絞りを有し、
前記着火室内で燃料濃度の高い予混合旋回流を形成して着火し、前記急速希釈室内で旋回火炎を急速希釈する、ことを特徴とするマイクロガスタービン用燃焼器。 A combustor for a micro gas turbine that includes a cylindrical inner liner and outer liner that surround a central axis and a burner portion that performs fuel injection and ignition, and forms a hollow cylindrical combustion chamber therein.
The combustion chamber includes a primary combustion chamber that is provided on the end liner side and has a relatively small outer diameter, and a secondary combustion chamber that is located downstream of the primary combustion chamber and has a relatively large outer diameter.
The primary combustion chamber includes an ignition chamber on the end liner side and a rapid dilution chamber on the secondary combustion chamber side, and has an annular intermediate throttle that narrows the outer diameter of the primary combustion chamber between the ignition chamber and the primary combustion chamber.
A combustor for a micro gas turbine, characterized in that a premixed swirling flow having a high fuel concentration is formed in the ignition chamber and ignited, and a swirling flame is rapidly diluted in the rapid dilution chamber. さらに、前記着火室に着火用空気を外部から導入し、かつ急速希釈室に希釈用空気を外部から導入して、中心軸を囲む旋回空気流を形成する旋回空気流形成装置と、
前記着火室内の旋回空気流の旋回方向に向けて燃料を噴射し予混合旋回流を形成する燃料噴射装置と、
前記着火室内の予混合旋回流に着火して管状火炎面を形成する着火装置とを備える、ことを特徴とする請求項１に記載のマイクロガスタービン用燃焼器。 Furthermore, a swirling air flow forming device that introduces ignition air into the ignition chamber from outside and introduces dilution air from the outside into the rapid dilution chamber to form a swirling air flow surrounding the central axis;
A fuel injection device for injecting fuel in a swirling direction of the swirling air flow in the ignition chamber to form a premixed swirling flow;
The combustor for a micro gas turbine according to claim 1, further comprising an ignition device configured to ignite a premixed swirl flow in the ignition chamber to form a tubular flame surface. 前記旋回空気流形成装置は、バーナ部に設けられ、内側に前記１次燃焼室を形成するアニュラー型部材と、
該アニュラー型部材の外面から前記着火室及び急速希釈室内の前記旋回空気流の旋回方向に向けてそれぞれ貫通する着火用空気孔と希釈用空気孔とを有する、ことを特徴とする請求項２に記載のマイクロガスタービン用燃焼器。 The swirling air flow forming device is provided in a burner portion, and an annular member that forms the primary combustion chamber on the inside thereof,
3. An ignition air hole and a dilution air hole penetrating from the outer surface of the annular member toward the swirling direction of the swirling air flow in the ignition chamber and the rapid dilution chamber, respectively. 3. The combustor for a micro gas turbine as described.
JP2009151897A 2009-06-26 2009-06-26 Combustor for micro gas turbine Expired - Fee Related JP5316947B2 (en)

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