JP3114136B2 - Combustor - Google Patents
CombustorInfo
- Publication number
- JP3114136B2 JP3114136B2 JP05291901A JP29190193A JP3114136B2 JP 3114136 B2 JP3114136 B2 JP 3114136B2 JP 05291901 A JP05291901 A JP 05291901A JP 29190193 A JP29190193 A JP 29190193A JP 3114136 B2 JP3114136 B2 JP 3114136B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- duct
- air
- upstream
- combustion chamber
- 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.)
- Expired - Lifetime
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Description
【０００１】[0001]
【産業上の利用分野】本発明は、大流量の空気と燃料を
高負荷で燃焼させ、非常に高温の燃焼ガスを生成するこ
とができ、超音速飛しょう体の推進装置に適用されるラ
ムジェットエンジン等に使用される燃焼器に関する。BACKGROUND OF THE INVENTION This invention, ram air and fuel at a high flow rate is combusted at high load, very able to produce hot combustion gases, it is applied to the propulsion unit of a supersonic flying object The present invention relates to a combustor used for a jet engine or the like .
【０００２】[0002]
【従来の技術】本発明の燃焼器は、非常に高負荷燃焼が
可能となるため、超音速飛しょう体の推進装置として有
望なラムジェットエンジン用燃焼器としての応用価値が
高いので、以下ラムジェットエンジンへの応用例につい
て説明する。2. Description of the Related Art Since the combustor of the present invention can perform very high load combustion, it has a high application value as a ramjet engine combustor which is promising as a propulsion device for a supersonic flying object. An application example to a jet engine will be described.
【０００３】図４に２本の空気取入ダクト２を有する飛
しょう体１に装着された従来のラムジェットエンジンの
例を示す。ラムジェットエンジンは燃焼室３、排気ノズ
ル４、燃料ポンプ６、燃料制御装置７、燃料配管８、燃
料ノズル９、ラムジェット点火装置１０から構成され
る。これらに空気取入ダクト２、燃料タンク５を組み合
わせて推進装置とし、飛しょう体１の後部に配置され
る。空気取入ダクト２と燃焼室３は、ポートと呼ぶ開口
部でつながっている。本図の場合、各空気取入ダクト２
の燃焼室３への入口部は、途中でガイドベーン１３によ
り仕切られており、ポートは、空気取入ダクト２に対し
１本当たり２個ある。FIG. 4 shows a flight having two air intake ducts 2.
An example of a conventional ramjet engine mounted on a vehicle 1 is shown. The ramjet engine includes a combustion chamber 3, an exhaust nozzle 4, a fuel pump 6, a fuel control device 7, a fuel pipe 8, a fuel nozzle 9, and a ramjet ignition device 10. These air intake duct 2, a combination of fuel tank 5 and the propulsion device is arranged in the rear of the flight quotient body 1. The air intake duct 2 and the combustion chamber 3 are connected by an opening called a port. In the case of this drawing, each air intake duct 2
The entrance to the combustion chamber 3 is partitioned on the way by a guide vane 13, and there are two ports per air intake duct 2.
【０００４】飛しょう体１が補助固体ロケット等によっ
て超音速に加速されると、空気取入ダクト２に前方から
空気が勢いよく流入し始める。そのとき、燃料ポンプ６
が燃料タンク５から液体燃料を吸い込み、燃料制御装置
７、燃料配管８を通して、空気取入ダクト２に取り付け
た燃料ノズル９に送ってガイドベーン１３の上流側で気
流中に噴霧され、上流ダクト２ａから燃焼室３内に流入
した噴霧燃料にラムジェット点火装置１０によって着火
させると、以降、ラムジェットエンジンとして作動す
る。燃料の量は、１個の燃料制御装置７によって、その
ときに必要な燃空比を保持できる流量に調整され、各燃
料ノズル９に均等あるいは決まった比率に分配され、左
右のダクト２では均等あるいは決まった比率の燃空比に
なり、また同一ダクト内に設置された上流側ダクト２
ａ、下流側ダクト２ｂでは燃焼室３入口への流入曲率が
異なることから、上流ダクト２ａから燃焼室３へ流入す
る燃料ガスよりも下流ダクト２ｂからの燃料ガスよりも
燃空比が大きくなる。 [0004] Fei quotient body 1 is accelerated to supersonic speed by the auxiliary solid rocket etc., it begins to flow well air momentum from the front air intake duct 2. At that time, the fuel pump 6
Sucks liquid fuel from the fuel tank 5 and sends it to the fuel nozzle 9 attached to the air intake duct 2 through the fuel control device 7 and the fuel pipe 8 to be sprayed into the airflow on the upstream side of the guide vane 13 and the upstream duct 2a Flows into the combustion chamber 3 from
When the spray fuel thus ignited by the ramjet igniter 10, it operates as a ramjet engine thereafter. The amount of fuel, by a single fuel control unit 7, is adjusted to a flow rate that can hold air ratio required at that time, is distributed evenly or fixed ratio to each fuel nozzle 9, left
In the right duct 2, the fuel / air ratio is equal or fixed
And upstream duct 2 installed in the same duct
a, in the downstream side duct 2b, the inflow curvature to the combustion chamber 3 inlet is
Because they are different, they flow into the combustion chamber 3 from the upstream duct 2a.
Than the fuel gas from the downstream duct 2b
The fuel-air ratio increases.
【０００５】[0005]
【発明が解決しようとする課題】上記従来のラムジェッ
トエンジン等に使用される燃焼器には解決すべき次の課
題があった。The combustor used in the above-mentioned conventional ramjet engine has the following problems to be solved.
【０００６】即ち、従来の空気取入口ダクト２に常に均
等あるいは決まった比率で燃料を分配しながら燃空比を
変化させると、燃焼室３内部で保炎を司る保炎渦１２内
の局所燃空比も、上流ダクトから燃焼室３へ流入するも
のと下流ダクト２ｂから流入するものとの燃空比に差は
生じるものの、空気取入口ダクト２に供給された燃料流
量に応じて変化する。そのため、燃空比を大きくすると
燃焼効率（実際の発熱量と理想的な発熱量の比率）が数
％低下したり、燃空比を小さくすると失火が早くなる等
して安定保炎範囲が広く取れないという問題があった。That is, if the fuel-air ratio is changed while always distributing the fuel to the conventional air intake duct 2 at an equal or fixed ratio, the local fuel in the flame holding vortex 12 which controls the flame inside the combustion chamber 3 is formed. The air ratio also flows into the combustion chamber 3 from the upstream duct.
The difference between the fuel and air ratio between the
The fuel flow that is produced but supplied to the air intake duct 2
It changes according to the quantity . Therefore, if the fuel-air ratio is increased, the combustion efficiency (the ratio of the actual calorific value to the ideal calorific value) is reduced by several percent, and if the fuel-air ratio is decreased, the misfire is accelerated, and the stable flame holding range is widened. There was a problem that it could not be taken.
【０００７】本発明は上記問題解決のため、各空気取入
ダクトへの燃料配分を均等又は決まった比率にしても、
各ダクトを流れる空気流量の変化に伴い変化する燃空比
の変化に応じて燃焼室に噴射される燃料流量を保炎渦の
形成若しくは推力の大きさに対応した燃空比に制御でき
る燃料制御装置を備えたラムジェットエンジン用燃焼器
等として使用される燃焼器を提供することを目的とす
る。[0007] The present invention solves the above-mentioned problems by using various air intakes.
Even if the fuel distribution to the duct is even or fixed,
The fuel flow is injected into the combustion chamber in response to changes in fuel-air ratio which changes with the change of the air flow rate flowing through each duct of the flame stabilizing vortex
An object of the present invention is to provide a combustor used as a combustor for a ramjet engine or the like including a fuel control device capable of controlling a fuel- air ratio corresponding to the magnitude of the formation or thrust .
【０００８】[0008]
【課題を解決するための手段】本発明は上記課題の解決
手段として、空気取入ダクトの後流側が上流ダクトと下
流ダクトの２つのダクトに分れて燃焼室に連通する燃焼
器において、燃料ポンプから上流ダクトに燃料を供給す
る燃料配管に介装され、上流ダクト内を流れる空気流量
に対し常に安定した保炎渦を形成できる範囲の燃空比に
する流量に制御して上流ダクト内に燃料を供給する燃料
制御装置Ａと、燃料ポンプから下流ダクトに燃料を供給
する燃料配管に介装され、上流ダクト内に供給される燃
料流量とは独立に制御され、推力の変動に対応させて下
流ダクト内を流れる空気を所定範囲の燃空比にする流量
に制御して下流ダクト内に燃料を供給する燃料制御装置
Ｂとを具え、速度、飛しょう姿勢により変動する上流ダ
クト及び下流ダクト内を流れる空気流量の変化に対応さ
せ上流ダクト及び下流ダクトに噴射される燃料流量の割
合を制御し、低負荷から高負荷に至る広い作動範囲に渡
って高い燃焼効率を維持することのできる燃料制御装置
を具備することを特徴とする燃焼器を提供しようとする
ものである。As the invention of the means for solving the problems In order to solve the problems], in the combustor downstream of the air intake duct communicates with the combustion chamber is divided into two ducts upstream duct and the downstream duct, the fuel Supply fuel from pump to upstream duct
Of air flowing through the upstream duct installed in the fuel pipe
To a fuel-air ratio within a range where a stable flame holding vortex can always be formed
To supply fuel into the upstream duct at a controlled flow rate
Supply fuel to downstream duct from controller A and fuel pump
Fuel supplied to the upstream duct
It is controlled independently of the fuel flow rate,
Flow rate to make the air flowing in the flow duct a fuel-air ratio within a certain range
Control device that supplies fuel into the downstream duct by controlling the flow rate
B and responds to changes in the air flow rate flowing in the upstream and downstream ducts that fluctuate depending on the speed and flying attitude.
Control the proportion of fuel flow injected into the upstream duct and downstream duct to cover a wide operating range from low to high loads.
Accordingly, it is an object of the present invention to provide a combustor comprising a fuel control device capable of maintaining high combustion efficiency .
【０００９】[0009]
【作用】本発明の燃焼器は上記のように構成されるので
次の作用を有する。Since the combustor of the present invention is constructed as described above, it has the following functions.
【００１０】即ち、上流ダクトと下流ダクトに分配され
る燃料流量の割合を、各ダクト内を流れる空気流量によ
り変動する燃空比の変化に応じて、それぞれ変更可能な
燃料制御装置を備えるため、推力が小さく全体の燃空比
を小さくする場合でも一方のダクト、たとえば燃料制御
装置Ａにより上流ダクトへの燃料流量を大きくして燃空
比を安定した保炎渦の形成ができる範囲に保って同ダク
ト側に点火手段を設け、下流ダクトの燃空比を相補的に
小さくすれば失火を生じることがない。That is, the ratio of the fuel flow rate distributed to the upstream duct and the downstream duct is determined by the air flow rate flowing through each duct.
Ri in response to changes in fuel-air ratio to change, for each with a modifiable fuel control device, fuel-air ratio of the entire thrust is small
One duct even when Reduces the, for example, fuel control
An ignition means is provided on the duct side by increasing the fuel flow rate to the upstream duct by means of the device A and maintaining a fuel-air ratio within a range where a stable flame holding vortex can be formed, and the fuel-air ratio of the downstream duct is complementarily reduced. It will not cause a misfire.
【００１１】また、燃焼器内にあって保炎渦の燃空比は
上流ダクトの燃空比の影響を最も強く受けるので、推力
を増大させるために空気取入ダクトに多くの燃料を供給
する場合でも、燃料制御装置Ａにより上流ダクトへの燃
料供給量を保炎渦を形成できる燃空比の範囲にすると共
に、燃料制御装置Ｂによって下流ダクトの燃空比を所定
範囲の大きさのものに適切に変更することによって、全
体の燃空比とは別に保炎渦の燃空比を燃焼に最適な状態
に保つことができるため、全体の燃空比を大きくしても
高い燃焼効率を維持できる。この結果、燃空比の広い領
域にわたって高い燃焼器性能を発揮できる。Further, since there into the combustor fuel-air ratio of the flame stabilizing vortex most strongly affected by the fuel-air ratio of the upstream duct, thrust
More fuel to the air intake duct to increase air quality
The fuel control device A is
When the feed rate is set within the range of the fuel-air ratio that can form the flame holding vortex,
Next , the fuel control device B determines the fuel-air ratio of the downstream duct
By appropriately changed to the size of the range, the fuel-air ratio of the separate flame holding vortex the entire fuel-air ratio can be maintained in an optimum state for combustion, and increases the overall fuel-air ratio Even at high combustion efficiency can be maintained. As a result, high combustor performance can be exhibited over a wide range of fuel-air ratio.
【００１２】[0012]
【実施例】本発明の第１〜第３実施例を図１〜図３によ
り説明する。なお、従来例ないしは先の実施例と同様な
構成部材には同符号を付し、必要ある場合を除き説明を
省略する。DESCRIPTION OF THE PREFERRED EMBODIMENTS First to third embodiments of the present invention will be described with reference to FIGS. The same components as those in the conventional example or the previous embodiment are denoted by the same reference numerals, and description thereof will be omitted unless necessary.
【００１３】（第１実施例） 第１実施例を図１により説明する。(First Embodiment) A first embodiment will be described with reference to FIG.
【００１４】図１は本実施例のラムジェットエンジンを
搭載した飛しょう体１の縦断面図で、２は後流側が、上
流ダクト２ａと下流ダクト２ｂの２つのダクトに分れて
燃焼室３に連通する空気取入ダクト、７ａは上流ダクト
２ａ内に流入した空気流に分配される燃料流量の割合
を、下流ダクト２ｂ内に流入した空気流に分配される割
合よりは違えて供給できる燃料制御装置Ａとしての燃料
制御装置、７ｂは下流ダクト２ｂに分配される燃料流量
の割合を上流ダクト２ａに分配される割合とは独立に違
えて供給できる燃料制御装置Ｂとしての燃料制御装置で
ある。その他の構成は以下の作用の説明において併述す
る。[0014] Figure 1 is a longitudinal sectional view of the flight quotient body 1 equipped with a ramjet engine of the present embodiment, 2 is the downstream side, a combustion chamber 3 is divided into two ducts upstream duct 2a and the downstream duct 2b air intake duct communicating with the fuel 7a is the ratio of fuel flow rate to be distributed to the airflow flowing into the upstream duct 2a, which can be supplied Chigae than ratio of distribution in the air stream flowing into the downstream duct 2b The fuel control device 7b serves as a control device A, and the fuel control device B can supply the fuel flow rate distributed to the downstream duct 2b independently of the fuel flow rate distributed to the upstream duct 2a. It is a control device. Other configurations will be described in the following description of the operation.
【００１５】次に上記構成の本実施例の燃焼器の作用に
ついて説明する。Next , the operation of the combustor according to the present embodiment having the above configuration will be described.
【００１６】本実施例では空気取入ダクト２が機軸対称
に２個設けられており、２個の燃料制御装置７ａ、７ｂ
がそれぞれの上流ダクト２ａ、下流ダクト２ｂ専用に取
り付けられて、各空気取入ダクト２のそれぞれに設けら
れた上流ダクト２ａ、下流ダクト２ｂ内を流れる空気流
に液体燃料を噴霧するようにしている。燃料ポンプ６か
ら送り出された燃料は分岐管１１で２方向に分岐したあ
と、それぞれ燃料制御装置７ａ、７ｂ、燃料配管８ａ、
８ｂを通って、上流ダクト２ａ、下流ダクト２ｂに取り
付けられた燃料ノズル９ａ、９ｂに送られる。それぞれ
の燃料流量は、各燃料制御装置７ａ、７ｂによって、上
流ダクト２ａ、下流ダクト２ｂそれぞれの燃空比に応じ
た流量比に配分される。[0016] Ri Contact air intake duct 2 is provided two in axis symmetry in this embodiment, two fuel control system 7a, 7b
Are provided exclusively for the respective upstream duct 2a and the downstream duct 2b, and are provided in each of the air intake ducts 2.
Air flow flowing through the separated upstream duct 2a and downstream duct 2b
Is sprayed with liquid fuel. After the fuel delivered from the fuel pump 6 is branched in two directions by a branch pipe 11, the fuel control devices 7a and 7b, the fuel pipes 8a and
8b, the fuel is sent to fuel nozzles 9a and 9b attached to the upstream duct 2a and the downstream duct 2b. Each of the fuel flow, the fuel control system 7a, by 7b, the upper
It is distributed to a flow ratio according to the fuel-air ratio of each of the flow duct 2a and the downstream duct 2b .
【００１７】従って、全体の燃空比の制限内で個々の上
流ダクト２ａ、下流ダクト２ｂの燃空比は適切に変更で
き、燃焼室３の供給燃料が少い場合においても、上流ダ
クト２ａ内への燃料流量を大きくして燃焼室３内の保炎
渦の形成に好適な燃空比にして高い燃焼効率を維持でき
る最適な値に保つことができ、また、燃焼室３への供給
燃料を多くする必要がある場合でも、上流ダクト２ａ内
へ供給する燃料流量を燃焼室３内の保炎渦の形成に好適
な燃空比にして高い燃焼効率を維持できる最適な値に保
つことができるので、燃焼室３の低負荷から高負荷に至
る広い作動範囲に渡って高い燃焼効率を維持できる燃焼
器とすることができる。 Therefore, the fuel-air ratio of each of the upstream duct 2a and the downstream duct 2b can be appropriately changed within the limit of the whole fuel-air ratio , and even when the fuel supplied to the combustion chamber 3 is small , the upstream duct 2a and the downstream
It can be maintained at an optimum value capable of maintaining a high combustion efficiency at the appropriate fuel-air ratio for the formation of flame holding vortex in the combustion chamber 3 by increasing the fuel flow to the transfected 2a, also into the combustion chamber 3 Supply of
Even if it is necessary to increase the amount of fuel,
Suitable for forming a flame holding vortex in the combustion chamber 3
To the optimal value to maintain high combustion efficiency
From low load to high load in the combustion chamber 3
Combustion that can maintain high combustion efficiency over a wide operating range
Vessel.
【００１８】（第２実施例） 第２実施例を図２により説明する。(Second Embodiment) A second embodiment will be described with reference to FIG.
【００１９】第２実施例は４本の空気取入ダクト２を有
するラムジェットエンジンの例で、図２は燃料ノズル取
付位置における機軸に垂直な断面を表している。第１実
施例と同じく上流ダクト２ａ、下流ダクト２ｂ専用の燃
料制御装置Ａおよび燃料制御装置としての燃料制御装置
７ａ、７ｂがそれぞれ設けられている。その他の構成及
び全体の作用効果は第１実施例と同様である。The second embodiment is an example of a ramjet engine having four air intake ducts 2, and FIG. 2 shows a cross section perpendicular to the machine axis at a fuel nozzle mounting position. As in the first embodiment, a fuel dedicated to the upstream duct 2a and the downstream duct 2b is used.
A fuel control device A and fuel control devices 7a and 7b as fuel control devices are provided, respectively. The other configuration and overall operation and effect are the same as those of the first embodiment.
【００２０】（第３実施例） 第３実施例を図３により説明する。前述した第１実施
例、第２実施例では異なる空気取入ダクト２に流入する
空気流量が異なる場合でも、各空気取入ダクト２に設置
された上流ダクト２ａ、下流ダクト２ｂに噴霧される燃
料流量は同じにされ、各上流ダクト２ａおよび下流ダク
ト２ｂに噴霧される燃料流量を変化させるようにしてい
たが、本実施例は、飛しょう時の姿勢変化時等におい
て、各空気取入ダクト２に流入する空気流量が異なるよ
うな場合に、上流ダクト２ａ、下流ダクト２ｂの燃料分
配比率を変えるだけでなく、たとえば、異なる空気取入
ダクトにそれぞれ設けられている上流ダクト２ａ及び下
流ダクト２ｂ同士間でも空気流に噴射される燃料流量が
変えられるよう、即ち１本毎のダクトに供給される燃料
の独立制御が行えるように、各上流ダクト２ａ、各下流
ダクト２ｂそれぞれに１個ずつ燃料制御装置７を取り付
けるようにしてある。その他の構成は第１実施例等と同
様である。本実施例によれば各空気取入ダクト２に非対
称に空気が流入した場合でも燃空比を、それぞれ好適な
範囲のものにできるという利点がある。Third Embodiment A third embodiment will be described with reference to FIG. First implementation described above
For example, in the second embodiment, the air flows into a different air intake duct 2
Installed in each air intake duct 2 even when air flow is different
Sprayed on the upstream duct 2a and the downstream duct 2b
The feed rates are the same and each upstream duct 2a and downstream duct
To change the flow rate of fuel sprayed on
Was, but the present embodiment, Fei quotient when the posture change or the like smell
In the case where the flow rate of air flowing into each air intake duct 2 is different, not only the fuel distribution ratio of the upstream duct 2a and the downstream duct 2b is changed, but also, for example , different air intake
The upper duct 2a and the lower duct which are respectively provided in the duct
The flow rate of the fuel injected into the air flow can be changed between the flow ducts 2b , i.e., the fuel supplied to each duct.
Independently as control can be performed, the upstream duct 2a, are the <br/> only so that Attach the one by one fuel control device 7 to each of the downstream duct 2b. Other configurations are the same as those of the first embodiment. According to the present embodiment, even when air asymmetrically flows into each of the air intake ducts 2, the fuel-to-air ratio is set to a suitable value.
There is an advantage that it can be in a range .
【００２１】 ［発明の名称］本発明は上記のように構成されるので次
の効果を有する。[Title of the Invention] Since the present invention is configured as described above, it has the following effects.
【００２２】即ち、本発明を適用した燃焼器は広作動域
化が行えることにより、たとえば、これを飛しょう体に
搭載した場合、従来の飛しょう体よりも飛行可能領域が
大きくなる他、同領域内を機敏に運動でき、しかも、柔
軟性（フレキシビリティ）の高い運動ができる。また、
高い燃焼効率を維持できることにより、燃費が良くな
り、飛しょう体等の長射程化、小型化ができる。[0022] That is, the combustor according to the present invention by enabling the wide dynamic range of, for example, if this was mounted on a flying quotient body, other flight area than conventional flight quotient body increases, the It is possible to exercise agilely in the area and exercise with high flexibility (flexibility). Also,
The ability to maintain a high combustion efficiency, fuel consumption is improved, it is long-range, smaller size, such as fly quotient body.
【図１】本発明の第１実施例に係る縦断面図、FIG. 1 is a longitudinal sectional view according to a first embodiment of the present invention,
【図２】本発明の第２実施例に係る断面図、FIG. 2 is a sectional view according to a second embodiment of the present invention;
【図３】本発明の第３実施例に係る縦断面図、FIG. 3 is a longitudinal sectional view according to a third embodiment of the present invention,
【図４】従来例に係る縦断面図である。FIG. 4 is a longitudinal sectional view according to a conventional example.
１ 飛しょう体 ２ 空気取入ダクト ２ａ 上流ダクト ２ｂ 下流ダクト ３ 燃焼室 ５ 燃料タンク ６ 燃料ポンプ ７ 燃料制御装置 ７ａ 燃料制御装置（燃料制御装置Ａ） ７ｂ 燃料制御装置（燃料制御装置Ｂ） ８ａ、８ｂ 燃料配管 ９ａ、９ｂ 燃料ノズル １０ ラムジェット点火装置 １１ 分岐管1 flight quotient body 2 air intake duct 2a upstream duct 2b downstream duct 3 the combustion chamber 5 Fuel tank 6 the fuel pump 7 fuel control system 7a fuel control system (fuel control apparatus A) 7b fuel control system (fuel control system B) 8a, 8b fuel pipe 9a, 9b fuel nozzle 10 ramjet igniter 11 branch pipe
フロントページの続き (72)発明者 久保田 健一 愛知県小牧市大字東田中1200番地 三菱 重工業株式会社名古屋誘導推進システム 製作所内 (56)参考文献 特開 平２−64256（ＪＰ，Ａ) 特開 平４−259649（ＪＰ，Ａ) 特開 平５−195872（ＪＰ，Ａ) 特開 平４−148048（ＪＰ，Ａ) 特開 平３−237257（ＪＰ，Ａ) (58)調査した分野(Int.Cl.7，ＤＢ名) F02K 7/10 - 7/20 Continuation of the front page (72) Inventor Kenichi Kubota 1200, Higashi Tanaka, Oaza, Komaki City, Aichi Prefecture Mitsubishi Heavy Industries, Ltd. Nagoya Guidance Propulsion System Works (56) References JP-A-2-64256 (JP, A) JP-A-4- 259649 (JP, A) JP-A-5-195872 (JP, A) JP-A-4-148048 (JP, A) JP-A-3-237257 (JP, A) (58) Fields investigated (Int. Cl. 7 , DB name) F02K 7/ 10-7/20
Claims (1)
ダクトが燃焼室入口付近においてガイドベーン等を利用
して分流した上流ダクトと下流ダクト内で流入空気へ燃
料を噴射して生成した混合気を導入ポートから燃焼室へ
噴出し、上流ダクトからの混合気の一部を利用して燃焼
室内で強制的な渦を形成させて保炎を行い、上流ダクト
の残りの混合気及び下流ダクトの混合気を燃焼室内で燃
焼させることが可能な形式の燃焼器において、燃料ポン
プから上流ダクトに燃料を供給する燃料配管に介装さ
れ、上流ダクト内を流れる空気流量に対し常に安定した
保炎渦を形成できる範囲の燃空比にする流量に制御して
上流ダクト内に燃料を供給する燃料制御装置Ａと、燃料
ポンプから下流ダクトに燃料を供給する燃料配管に介装
され、上流ダクト内に供給される燃料流量とは独立に制
御され、推力の変動に対応させて下流ダクト内を流れる
空気を所定範囲の燃空比にする流量に制御して下流ダク
ト内に燃料を供給する燃料制御装置Ｂとを具え、速度、
飛しょう姿勢により変動する上流ダクト及び下流ダクト
内を流れる空気流量の変化に対応させ上流ダクト及び下
流ダクトに噴射される燃料流量の割合を各々制御し、低
負荷から高負荷に至る広い作動範囲に渡って高い燃焼効
率を維持することのできる燃空比にする燃料制御装置を
具備することを特徴とする燃焼器。An air intake duct located on the side of a cylindrical combustion chamber is used to feed fuel into an inflow air in an upstream duct and a downstream duct which are divided by using guide vanes or the like near an inlet of the combustion chamber. The air-fuel mixture generated by injecting air is injected into the combustion chamber from the introduction port, and a part of the air-fuel mixture from the upstream duct is used to form a forced vortex in the combustion chamber to perform flame holding, and In a combustor of a type capable of burning the remaining mixture and the mixture in the downstream duct in the combustion chamber, a fuel pump
Is installed in the fuel pipe that supplies fuel from the pump to the upstream duct.
Is always stable with respect to the airflow flowing through the upstream duct.
Control the flow rate so that the fuel-air ratio is within the range where a flame holding vortex can be formed.
A fuel control device A for supplying fuel into the upstream duct;
Interposed in the fuel pipe that supplies fuel from the pump to the downstream duct
Is controlled independently of the fuel flow supplied to the upstream duct.
And flows through the downstream duct in response to fluctuations in thrust.
Control the air flow rate to bring the air to a predetermined
And a fuel control device B for supplying fuel into the
Upstream and downstream ducts that vary with flying attitude
The ratio of the inner to correspond to changes in the air flow through the fuel flow injected into the upstream duct and the lower <br/> flow duct each control, the high combustion efficiency over a wide operating range leading to a high load from the low load A combustor characterized by comprising a fuel control device for maintaining a fuel-air ratio that can be maintained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP05291901A JP3114136B2 (en) | 1993-11-22 | 1993-11-22 | Combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP05291901A JP3114136B2 (en) | 1993-11-22 | 1993-11-22 | Combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH07145756A JPH07145756A (en) | 1995-06-06 |
| JP3114136B2 true JP3114136B2 (en) | 2000-12-04 |
Family
ID=17774931
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP05291901A Expired - Lifetime JP3114136B2 (en) | 1993-11-22 | 1993-11-22 | Combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3114136B2 (en) |
-
1993
- 1993-11-22 JP JP05291901A patent/JP3114136B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPH07145756A (en) | 1995-06-06 |
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