JP2738987B2 - Ramjet engine - Google Patents
Ramjet engineInfo
- Publication number
- JP2738987B2 JP2738987B2 JP3020930A JP2093091A JP2738987B2 JP 2738987 B2 JP2738987 B2 JP 2738987B2 JP 3020930 A JP3020930 A JP 3020930A JP 2093091 A JP2093091 A JP 2093091A JP 2738987 B2 JP2738987 B2 JP 2738987B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- air intake
- air
- intake duct
- ramjet engine
- 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 - Fee Related
Links
- 239000000446 fuel Substances 0.000 claims description 81
- 238000002347 injection Methods 0.000 claims description 7
- 239000007924 injection Substances 0.000 claims description 7
- 239000012530 fluid Substances 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 description 11
- 239000007788 liquid Substances 0.000 description 9
- 239000002828 fuel tank Substances 0.000 description 5
- 230000007423 decrease Effects 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 230000020169 heat generation Effects 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
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- Toys (AREA)
- Fuel-Injection Apparatus (AREA)
Description
【０００１】[0001]
【産業上の利用分野】本発明は、超音速ミサイル等の推
進装置に適用されるラムジェットエンジンに関する。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a ramjet engine applied to a propulsion device for a supersonic missile or the like.
【０００２】[0002]
【従来の技術】図３に液体燃料を用いた場合の従来の例
を示す。ラムジェットエンジンは、燃焼器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及びラムジェット点火装置１０を備えてい
る。これらに、前方へ伺う開口２´をもつ複数の空気取
入ダクト２、及び飛翔体本体１の後部に設けられた燃料
タンク５を組み合わせて推進装置とし、飛翔体の後部に
配置される。前記各空気取入ダクト２内には、それぞれ
燃料ノズル９が設けられており、共通の燃料ポンプ６か
ら共通の燃料制御装置７を経て前記各燃料ノズル９へ燃
料が送られ、また、燃料が噴射された空気は共通の燃焼
器１０へ送られ、こゝで燃焼した燃焼ガスが燃焼器１０
に続く排気ノズル４から排出されるようになっている。2. Description of the Related Art FIG. 3 shows a conventional example using a liquid fuel. The ramjet engine includes a combustor 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 are combined with a plurality of air intake ducts 2 each having an opening 2 ′ that is directed forward, and a fuel tank 5 provided at the rear of the flying object main body 1 to form a propulsion device, which is arranged at the rear of the flying object. A fuel nozzle 9 is provided in each of the air intake ducts 2, and fuel is sent from the common fuel pump 6 to each of the fuel nozzles 9 via the common fuel control device 7. The injected air is sent to a common combustor 10, and the combustion gas burned in the combustor 10 is
Is discharged from the exhaust nozzle 4 following the above.
【０００３】飛翔体が補助固体ロケット等によって超音
速に加速されると、開口２´を通って空気取入ダクト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に送って気流中に液体燃料を
噴霧し、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、燃料制御装置７によって、そのときに必要な量
に調整され、各空気取入ダクト２に均等に分配される。When the projectile is accelerated to a supersonic speed by an auxiliary solid rocket or the like, the air intake duct 2 passes through the opening 2 '.
The air begins to flow vigorously from the front. At that time, the fuel pump 6 sucks the liquid fuel from the fuel tank 5 and passes through the fuel control device 7 and the fuel pipe 8 to the air intake duct 2.
When the liquid fuel is sprayed into the air stream by being sent to the fuel nozzle 9 attached to the ramjet and ignited by the ramjet igniter 10, the ramjet igniter 10 thereafter operates as a ramjet engine. The amount of fuel is adjusted by the fuel control device 7 to the amount required at that time and is evenly distributed to each air intake duct 2.
【０００４】[0004]
【発明が解決しようとする課題】前記の従来のラムジェ
ットエンジンでは、飛翔体が迎角及び、または、すべり
角をつけて飛翔して、各空気取入ダクト２への流入空気
流量が均等にならない場合においても、燃料は各空気取
入ダクト２に均等に分配されるので、各空気取入ダクト
毎の燃空比（燃料と空気の混合比）が均一にならない。
従って、燃焼器３内部の局所燃空比にバラツキができ
て、安定燃焼が可能な燃空比の範囲が狭まったり、燃焼
効率（実際の発熱量と理想的な発熱量の比率）が５〜１
０％程度低下する。In the above-described conventional ramjet engine, the flying object flies at an angle of attack and / or a slip angle, and the flow rate of air flowing into each air intake duct 2 is evenly distributed. Even if this is not the case, the fuel is evenly distributed to each air intake duct 2, so that the fuel-air ratio (mixing ratio of fuel and air) for each air intake duct is not uniform.
Accordingly, the local fuel-air ratio in the combustor 3 varies, and the range of the fuel-air ratio in which stable combustion can be performed is narrowed, and the combustion efficiency (the ratio of the actual heat generation to the ideal heat generation) is 5 to 5. 1
It decreases by about 0%.
【０００５】本発明は、従来のラムジェットエンジンの
以上の問題点を解決しようとするものである。The present invention seeks to solve the above problems of the conventional ramjet engine.
【０００６】[0006]
【課題を解決するための手段】本発明のラムジェットエ
ンジンは、複数の空気取入ダクト及び各空気取入ダクト
内に設けられた流体燃料を噴射する燃料ノズルを備えた
ラムジェットエンジンにおいて、前記各空気取入ダクト
内への流入空気流量によって前記燃料ノズルの流体燃料
の噴射量を調整する燃料制御装置を設けた。A ramjet engine according to the present invention includes a ramjet engine having a plurality of air intake ducts and a fuel nozzle provided in each air intake duct for injecting fluid fuel. A fuel control device is provided for adjusting the amount of fluid fuel injected from the fuel nozzle by the flow rate of air flowing into each air intake duct.
【０００７】[0007]
【作用】ラムジェットエンジンを装備した飛翔体等が迎
角及び、または、すべり角をつけて飛行する場合には、
各空気取入ダクトへの流入空気量が均等にならない。本
発明では、燃料制御装置は各空気取入ダクトへの流入空
気流量によって燃料ノズルの流体燃料の噴射量を制御
し、各空気取入ダクトへの流入空気流量に応じた量の流
体燃料が各空気取入ダクトへ噴射される。これによっ
て、空気取入口毎の燃空比のバラツキがなくなり、安定
燃焼が可能な燃空比の範囲が広く維持され、また燃焼効
率の低下も抑えられる。[Function] When a flying object equipped with a ramjet engine flies at an angle of attack and / or a slip angle,
The amount of air flowing into each air intake duct is not equal. According to the present invention, the fuel control device controls the injection amount of the fluid fuel of the fuel nozzle by the flow rate of the air flowing into each air intake duct, and the amount of the fluid fuel corresponding to the flow rate of the air flowing into each air intake duct is controlled by Injected into the air intake duct. This eliminates variations in the fuel-air ratio for each air intake, maintains a wide range of fuel-air ratios in which stable combustion is possible, and suppresses a decrease in combustion efficiency.
【０００８】[0008]
【実施例】本発明の第１の実施例を、図１によって説明
する。本実施例は、２個に分割され、各々が前方への開
口２´をもつ２個の空気取入ダクト２を備え、各空気取
入ダクト２内へ液体燃料を噴射する２個の燃料ノズル９
が設けられている。飛翔体本体１の後部には液体燃料を
収容する燃料タンク５が設けられ、また同タンク５へ接
続された１個の燃料ポンプ６及び同燃料ポンプ６と前記
２個の燃料ノズル９とを接続する２方向へ分岐する分岐
管１１及び燃料配管８，８が飛翔体本体１内に設けられ
ている。同分岐管１１と燃焼配管８の間には、各燃料ノ
ズル９の燃料噴射量を制御する２個の燃料制御装置７，
７が設けられている。各燃料制御装置７は、各空気取入
ダクト２内に設けられた図示しないピトー管、総圧管又
は静圧測空孔に接続され、その検出圧力値によって各空
気取入ダクト２の流入空気流量を演算し、これに基づい
て燃料ノズル９の燃料噴射量を調整するように構成され
ている。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS A first embodiment of the present invention will be described with reference to FIG. This embodiment comprises two air intake ducts 2 divided into two, each having an opening 2 ′ in front, and two fuel nozzles for injecting liquid fuel into each air intake duct 2. 9
Is provided. A fuel tank 5 for storing liquid fuel is provided at the rear of the flying object body 1, and one fuel pump 6 connected to the fuel tank 5 and the fuel pump 6 are connected to the two fuel nozzles 9. A branch pipe 11 and fuel pipes 8, 8 are provided in the flying object main body 1. Between the branch pipe 11 and the combustion pipe 8, two fuel control devices 7 for controlling the fuel injection amount of each fuel nozzle 9,
7 are provided. Each fuel control device 7 is connected to a pitot tube, a total pressure tube, or a static pressure measuring hole (not shown) provided in each air intake duct 2, and the flow rate of air flowing into each air intake duct 2 is determined by the detected pressure value. Is calculated, and the fuel injection amount of the fuel nozzle 9 is adjusted based on this.
【０００９】前記複数の空気取入ダクト２は共通の燃焼
器３に接続され、また、燃焼器３の後方には排気ノズル
４が接続されている。１０は燃焼器３の直前に設けられ
たラムジェット点火装置である。The plurality of air intake ducts 2 are connected to a common combustor 3, and an exhaust nozzle 4 is connected behind the combustor 3. Reference numeral 10 denotes a ramjet ignition device provided immediately before the combustor 3.
【００１０】本実施例では、燃料ポンプ６から送り出さ
れた液体燃料は、分岐管１１で２方向へ分岐したあと、
それぞれ燃料制御装置７、燃料配管８を通って、各空気
取入ダクト２に取り付けられた燃料ノズル９に送られ、
各空気取入ダクト２内に噴射される。In the present embodiment, the liquid fuel sent from the fuel pump 6 is branched by a branch pipe 11 in two directions.
Each is sent to the fuel nozzle 9 attached to each air intake duct 2 through the fuel control device 7 and the fuel pipe 8,
It is injected into each air intake duct 2.
【００１１】各空気取入ダクト２における流入空気の流
量によって、燃焼制御装置７は、燃焼ノズル９の燃料噴
射量を調整する。各空気取入ダクト２においては、飛翔
体の迎角及び、またはすべり角をつけた飛行によって、
流入空気流量が均等にならない場合があるが、本実施例
では各流入空気取入ダクト２の流入空気流量に応じた量
の燃料を各空気取入ダクト２へ噴射することによって、
各空気取入ダクト２毎の燃空比を均一にすることができ
る。従って、燃焼器３内部の局所的燃空比にバラツキが
生ずることがなく安定燃焼が可能な燃空比の範囲が狭ま
ることがなく、また燃焼効率の低下を来すことがない。The combustion control device 7 adjusts the fuel injection amount of the combustion nozzle 9 based on the flow rate of the inflow air in each air intake duct 2. In each air intake duct 2, the flight with the angle of attack and / or the slip angle of the flying object
Although the inflow air flow rate may not be uniform, in the present embodiment, by injecting fuel into each air intake duct 2 in an amount corresponding to the inflow air flow rate of each inflow air intake duct 2,
The fuel-air ratio of each air intake duct 2 can be made uniform. Therefore, the local fuel-air ratio in the combustor 3 does not vary, and the range of the fuel-air ratio in which stable combustion can be performed is not narrowed, and the combustion efficiency does not decrease.
【００１２】本発明の第２の実施例を、図２によって説
明する。本実施例は、上下方向にゆるやかに、左右方向
に強く旋回する飛翔体のラムジェットエンジンに係る。A second embodiment of the present invention will be described with reference to FIG. The present embodiment relates to a ramjet engine of a flying object which slowly turns vertically and strongly turns left and right.
【００１３】本実施例では、４本の空気取入ダクト２
ａ，２ｂ，２ｃ，２ｄを有し、この４本の空気取入ダク
ト２ａ，２ｂ，２ｃ，２ｄがＸ字型に配置されている。
本実施例の飛翔体は、この姿勢のまま、左右方向に強く
旋回するので、旋回時はすべり角度が大きく、右側２本
の空気取入ダクト２ａ，２ｂと左側２本の空気取入ダク
ト２ｃ，２ｄの流入空気流量がそれぞれ異なる。一方本
実施例の場合、上下方向の運動はゆるやかとしてあるの
で、右側の上下の空気取入ダクト２ａ，２ｂ、及び左側
の上下の空気取入ダクト２ｄ，２ｃは、それぞれ流入空
気流量が常にほぼ等しい。従って、燃料流量は、右側の
上下の空気ダクト２ａ，２ｂは等しくてよく、かつ、左
側の上下の空気ダクト２ｄ，２ｃは等しくてよい。従っ
て、本実施例では、各々が前記第１の実施例と同様の構
成の２個の燃料制御装置７が右側専用及び左側専用に取
り付けられる。前記燃料制御装置７のうちの一方は、左
側空気取入ダクト２ａ，２ｂのいづれかのピトー管、総
圧管又は静圧孔に接続されて空気取入ダクト２ａ，２ｂ
のいづれかの流入空気流量に基づいて、左側の空気取入
ダクト２ａ，２ｂの燃料ノズル９からの燃料噴射量を調
整し、前記燃料制御装置７のうちの他方は、右側空気取
入ダクト２ｄ，２ｃのいづれかのピトー管、総圧管又は
静圧孔に接続されて空気取入ダクト２ｄ，２ｃのいづれ
かの流入空気流量に基づいて右側の空気取入ダクト２
ｄ，２ｃの燃料ノズル９からの燃料噴射量を調整するよ
うになっている。In this embodiment, four air intake ducts 2
a, 2b, 2c and 2d, and these four air intake ducts 2a, 2b, 2c and 2d are arranged in an X-shape.
The flying object of this embodiment turns strongly in the left-right direction while maintaining this posture, and therefore has a large slip angle when turning, and the two air intake ducts 2a, 2b on the right and the two air intake ducts 2c on the left. , 2d are different from each other. On the other hand, in the case of the present embodiment, since the vertical movement is gradual, the upper and lower air intake ducts 2a and 2b on the right side and the upper and lower air intake ducts 2d and 2c on the left side always have almost the same inflow air flow rate. equal. Therefore, the fuel flow rate may be equal for the upper and lower right air ducts 2a and 2b, and may be equal for the left and upper and lower air ducts 2d and 2c. Therefore, in this embodiment, two fuel control devices 7 each having the same configuration as that of the first embodiment are mounted exclusively for the right side and exclusively for the left side. One of the fuel control devices 7 is connected to a pitot tube, a total pressure tube, or a static pressure hole of any of the left air intake ducts 2a, 2b, and is connected to the air intake ducts 2a, 2b.
The fuel injection amount from the fuel nozzle 9 of the left air intake duct 2a, 2b is adjusted based on one of the inflow air flow rates, and the other of the fuel control devices 7 is controlled by the right air intake duct 2d, The right air intake duct 2 connected to any one of the pitot tube, the total pressure tube, or the static pressure hole based on the inflow air flow rate of any one of the air intake ducts 2d and 2c.
The fuel injection amount from the fuel nozzle 9 of d and 2c is adjusted.
【００１４】また、燃料ポンプ６から送り出された液体
燃料は分岐管１１で２方向に分岐して、各燃料制御装置
７を通ったあと、燃料配管８でさらに分岐して、それぞ
れの空気取入ダクトに取り付けられた燃料ノズル９に送
られるようになっている。なお、本実施例の他の部分の
構成は前記第１の実施例と同様である。The liquid fuel delivered from the fuel pump 6 is branched in two directions by a branch pipe 11, passes through each fuel control device 7, and further branches by a fuel pipe 8 to take in each air intake. The fuel is sent to the fuel nozzle 9 attached to the duct. The configuration of the other parts of this embodiment is the same as that of the first embodiment.
【００１５】本実施例では、飛翔体の左右方向に強く旋
回する飛行によって、右側の空気取入ダクト２ａ，２ｂ
と左側の空気取入ダクト２ｄ，２ｃへの流入空気流量が
等しくなくなると、燃料制御装置７，７によって、各空
気取入ダクト２ａ，２ｂ又は２ｄ，２ｃへの流入空気流
量に応じた液体燃料が噴射されることゝなる。従って、
各空気取入ダクトにおける燃空比は一定に維持され、前
記第１の実施例と同様な効果を奏することができる。In the present embodiment, the right air intake ducts 2a and 2b are provided by a flight in which the flying object turns strongly in the left-right direction.
When the flow rates of the air flowing into the air intake ducts 2d and 2c on the left and the left side become unequal, the fuel control devices 7 and 7 control the liquid fuel according to the flow rates of the air flowing into the respective air intake ducts 2a and 2b or 2d and 2c. Is injected. Therefore,
The fuel-air ratio in each air intake duct is kept constant, and the same effect as in the first embodiment can be obtained.
【００１６】なお、本実施例では、４本の空気取入ダク
トに２個の燃料制御装置を用いているが、各空気取入ダ
クトに１個づつ計４個の燃料制御装置を用いるようにし
てもよい。In this embodiment, two fuel control units are used for four air intake ducts, but four fuel control units are used for each air intake duct. You may.
【００１７】前記第１及び第２の実施例では、燃料制御
装置は空気ダクトに設けられたピトー管、総圧管又は静
圧測定孔に接続されているが、飛翔体の迎角とすべり角
を測定し、予め風洞試験データに基づいて作成した関係
式を用いて燃料制御装置において各空気ダクトの流入空
気流量を求めるようにしてもよい。In the first and second embodiments, the fuel control device is connected to the pitot tube, the total pressure tube, or the static pressure measurement hole provided in the air duct, and determines the angle of attack and the slip angle of the flying object. The fuel control device may measure the inflow air flow rate of each air duct by using a relational expression that is measured and created based on wind tunnel test data in advance.
【００１８】また、前記第１及び第２の実施例では、液
体燃料を用いているが、気体燃料を用いることもでき
る。In the first and second embodiments, a liquid fuel is used, but a gaseous fuel may be used.
【００１９】[0019]
【発明の効果】本発明では、各空気取入ダクトへの流入
空気流量に応じて同各空気取入ダクトへの燃料噴射量を
調整して各空気取入ダクトにおける燃空比を均一として
いるために、飛翔体等が強く旋回しても、燃焼を安定化
させ、かつ燃焼効率の低下を小さく抑えることができ
る。また、これに伴って本発明を適用した飛翔体等は、
従来より激しい運動が可能になる。According to the present invention, the amount of fuel injected into each air intake duct is adjusted in accordance with the flow rate of air flowing into each air intake duct to make the fuel-air ratio in each air intake duct uniform. Therefore, even if the flying object or the like makes a strong turn, combustion can be stabilized and a decrease in combustion efficiency can be suppressed to a small extent. In addition, the projectiles and the like to which the present invention is applied,
Intense exercise becomes possible.
【図１】本発明の第１の実施例の側面図である。FIG. 1 is a side view of a first embodiment of the present invention.
【図２】本発明の第２の実施例の断面図である。FIG. 2 is a sectional view of a second embodiment of the present invention.
【図３】従来の飛翔体のラムジェットエンジンの側面図
である。FIG. 3 is a side view of a conventional ramjet engine of a flying object.
１ 飛翔体本体 ２，２ａ，２ｂ，２ｃ，２ｄ 空気取入ダクト ３ 燃焼器 ４ 排気ノズル ５ 燃料タンク ６ 燃料ポンプ ７ 燃料制御装置 ８ 燃料配管 ９ 燃料ノズル １０ ラムジェット点火装置 １１ 分岐管 DESCRIPTION OF SYMBOLS 1 Flying object main body 2, 2a, 2b, 2c, 2d Air intake duct 3 Combustor 4 Exhaust nozzle 5 Fuel tank 6 Fuel pump 7 Fuel control device 8 Fuel pipe 9 Fuel nozzle 10 Ramjet ignition device 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２−163448（ＪＰ，Ａ) ────────────────────────────────────────────────── ─── Continuation of 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-2-163448 (JP, A)
Claims (1)
クト内に設けられた流体燃料を噴射する燃料ノズルを備
えたラムジェットエンジンにおいて、各空気取入ダクト
内への流入空気流量によって前記燃料ノズルの流体燃料
の噴射量を調整する燃料制御装置を設けたことを特徴と
するラムジェットエンジン。1. A ramjet engine having a plurality of air intake ducts and a fuel nozzle for injecting a fluid fuel provided in each air intake duct, wherein the ramjet engine has a plurality of air intake ducts. A ramjet engine provided with a fuel control device for adjusting an injection amount of fluid fuel of a fuel nozzle.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3020930A JP2738987B2 (en) | 1991-02-14 | 1991-02-14 | Ramjet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3020930A JP2738987B2 (en) | 1991-02-14 | 1991-02-14 | Ramjet engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH04259649A JPH04259649A (en) | 1992-09-16 |
| JP2738987B2 true JP2738987B2 (en) | 1998-04-08 |
Family
ID=12040936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3020930A Expired - Fee Related JP2738987B2 (en) | 1991-02-14 | 1991-02-14 | Ramjet engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2738987B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109650B (en) * | 2021-10-27 | 2023-02-28 | 厦门大学 | Integral liquid rocket punching combined power device |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH079215B2 (en) * | 1988-12-16 | 1995-02-01 | 防衛庁技術研究本部長 | Gas generator for ram rocket |
-
1991
- 1991-02-14 JP JP3020930A patent/JP2738987B2/en not_active Expired - Fee Related
Also Published As
| Publication number | Publication date |
|---|---|
| JPH04259649A (en) | 1992-09-16 |
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| LAPS | Cancellation because of no payment of annual fees |