JPH04259649A - Ram jet engine - Google Patents
Ram jet engineInfo
- Publication number
- JPH04259649A JPH04259649A JP2093091A JP2093091A JPH04259649A JP H04259649 A JPH04259649 A JP H04259649A JP 2093091 A JP2093091 A JP 2093091A JP 2093091 A JP2093091 A JP 2093091A JP H04259649 A JPH04259649 A JP H04259649A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- air intake
- air
- intake duct
- control device
- 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.)
- Granted
Links
- 239000000446 fuel Substances 0.000 claims abstract description 85
- 239000012530 fluid Substances 0.000 claims abstract description 8
- 238000002485 combustion reaction Methods 0.000 abstract description 13
- 230000000087 stabilizing effect Effects 0.000 abstract 1
- 239000007788 liquid Substances 0.000 description 9
- 238000002347 injection Methods 0.000 description 6
- 239000007924 injection Substances 0.000 description 6
- 230000003068 static effect Effects 0.000 description 4
- 239000002828 fuel tank Substances 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 238000009530 blood pressure measurement Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 230000001105 regulatory effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Landscapes
- Fuel-Injection Apparatus (AREA)
- Toys (AREA)
Abstract
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 in which liquid fuel is used. 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 having forward openings 2' and a fuel tank 5 provided at the rear of the flying object body 1 to form a propulsion device, which is placed 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 a common fuel pump 6 to each fuel nozzle 9 via a common fuel control device 7. The injected air is sent to a common combustor 10, and the combustion gas combusted here is discharged from an exhaust nozzle 4 following the combustor 10.
【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 a flying object is accelerated to supersonic speed by an auxiliary solid rocket or the like, it passes through the opening 2' and enters the air intake duct 2.
Air begins to rush in from the front. At that time, the fuel pump 6 sucks liquid fuel from the fuel tank 5 and passes it through the fuel control device 7 and fuel piping 8 to the air intake duct 2.
When liquid fuel is sent to a fuel nozzle 9 attached to a fuel nozzle 9 and sprayed into an air stream, and ignited by a ramjet ignition device 10, the engine operates as a ramjet engine. The amount of fuel is regulated by the fuel control device 7 to the amount required at the time and distributed equally 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５〜１０
％程度低下する。[Problems to be Solved by the Invention] In the conventional ramjet engine described above, the projectile flies with an angle of attack and/or a slip angle, so that the flow rate of air flowing into each air intake duct 2 is uniform. Even if this is not the case, the fuel is evenly distributed to each air intake duct 2, so the fuel-air ratio (mixing ratio of fuel and air) for each air intake duct is not uniform. Therefore, variations occur in the local fuel-air ratio inside the combustor 3, narrowing the range of fuel-air ratios that allow stable combustion, and reducing the combustion efficiency (the ratio between the actual calorific value and the ideal calorific value) from 5 to 5. 10
% decrease.
【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-mentioned problems of conventional ramjet engines.
【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。[Means for Solving the Problems] The ramjet engine of the present invention includes a plurality of air intake ducts and a fuel nozzle for injecting fluid fuel provided in each air intake duct. A fuel control device is provided for adjusting the amount of fluid fuel injected from the fuel nozzle depending on 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。[Operation] When a flying object equipped with a ramjet engine flies with an angle of attack and/or a slip angle,
The amount of air flowing into each air intake duct is not equal. In the present invention, the fuel control device controls the injection amount of fluid fuel from the fuel nozzle according to the flow rate of air flowing into each air intake duct, and the amount of fluid fuel corresponding to the flow rate of air flowing into each air intake duct is injected into each air intake duct. Injected into the air intake duct. by this,
Variations in the fuel-air ratio between air intake ports are eliminated, a wide range of fuel-air ratios in which stable combustion can be achieved is maintained, and deterioration in combustion efficiency is also suppressed.
【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。Embodiment A first embodiment of the present invention will be explained with reference to FIG. This embodiment comprises two air intake ducts 2 which are divided into two parts, each having an opening 2' toward the front, and two fuel nozzles for injecting liquid fuel into each air intake duct 2. 9
is provided. A fuel tank 5 containing liquid fuel is provided at the rear of the flying object body 1, and a fuel pump 6 is connected to the tank 5, and the fuel pump 6 is connected to the two fuel nozzles 9. A branch pipe 11 and fuel pipes 8, 8 that branch into two directions are provided within the flying object body 1. Between the branch pipe 11 and the combustion pipe 8, there are two fuel control devices 7 for controlling the fuel injection amount of each fuel nozzle 9,
7 is provided. Each fuel control device 7 is connected to a pitot tube (not shown), a total pressure tube, or a static pressure measuring hole provided in each air intake duct 2, and the inflow air flow rate of each air intake duct 2 is determined based on the detected pressure value. is calculated, and the fuel injection amount of the fuel nozzle 9 is adjusted based on the calculation.
【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 to the rear of the combustor 3. 10 is 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 this embodiment, the liquid fuel sent out from the fuel pump 6 is branched into two directions by a branch pipe 11, and then
are sent to fuel nozzles 9 attached to each air intake duct 2 through a fuel control device 7 and a fuel pipe 8, respectively,
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 depending on the flow rate of the incoming air in each air intake duct 2. In each air intake duct 2, due to the flight of the flying object with an angle of attack and/or a slip angle,
Although the flow rate of incoming air may not be equal in some cases, in this embodiment, by injecting fuel into each air intake duct 2 in an amount corresponding to the flow rate of incoming air in each inflow air intake duct 2,
The fuel-air ratio for each air intake duct 2 can be made uniform. Therefore, there is no variation in the local fuel-air ratio inside the combustor 3, the range of fuel-air ratios that allow stable combustion is not narrowed, and there is no reduction in combustion efficiency.
【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 explained with reference to FIG. This embodiment relates to a ramjet engine for a flying object that rotates gently in the vertical direction and strongly in the horizontal direction.
【００１３】本実施例では、４本の空気取入ダクト２ａ
，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２ｄ
，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 2a
, 2b, 2c, and 2d, and these four air intake ducts 2a, 2b, 2c, and 2d are arranged in an X-shape. Since the flying object of this embodiment turns strongly in the left and right directions while maintaining this posture, the slip angle is large during turning, and the two air intake ducts 2a and 2b on the right side and the two air intake ducts 2c on the left side , 2d have different inflow air flow rates. On the other hand, in the case of this embodiment, since the movement in the vertical direction is gradual, the inflow air flow rate of the upper and lower air intake ducts 2a, 2b on the right side and the upper and lower air intake ducts 2d, 2c on the left side is always approximately equal. Therefore, the fuel flow rate may be equal in the upper and lower air ducts 2a and 2b on the right side, and may be equal in the upper and lower air ducts 2d and 2c on the left side. Therefore, in this embodiment, two fuel control devices 7, each having the same configuration as the first embodiment, are installed only on the right side and one on the left side. One of the fuel control devices 7 is connected to a pitot pipe, a total pressure pipe, or a static pressure hole of any of the left 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 the inflow air flow rate of either of the air intake ducts 2a, 2b. The right air intake duct 2d is connected to either the pitot pipe, the total pressure pipe or the static pressure hole of the air intake duct 2c, and the right air intake duct 2d is connected to the inflow air flow rate of either the air intake duct 2d, 2c.
, 2c, the amount of fuel injected from the fuel nozzles 9 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。Further, the liquid fuel sent out from the fuel pump 6 is branched into two directions by a branch pipe 11, passes through each fuel control device 7, and is further branched by a fuel pipe 8, and is then branched into each air intake. The fuel is sent to a fuel nozzle 9 attached to the duct. Note that the configuration of 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 this embodiment, the air intake ducts 2a and 2b on the right side are
When the flow rates of air flowing into the air intake ducts 2d and 2c on the left side are no longer equal, the fuel control devices 7, 7 control liquid fuel according to the flow rate of air flowing into each air intake duct 2a, 2b or 2d, 2c. will be injected. Therefore,
The fuel-air ratio in each air intake duct is maintained constant, and the same effects as in the first embodiment can be achieved.
【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 devices are used for the four air intake ducts, but one fuel control device is used for each air intake duct, for a total of four fuel control devices. It's okay.
【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 the fuel control device measures the angle of attack and slip angle of the projectile. The inflow air flow rate of each air duct may be determined in the fuel control device using a relational expression that is measured and created in advance based on wind tunnel test data.
【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
。Furthermore, although liquid fuel is used in the first and second embodiments, gaseous fuel may also 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。[Effects of the Invention] In the present invention, the amount of fuel injection into each air intake duct is adjusted according to the flow rate of air flowing into each air intake duct, thereby making the fuel-air ratio in each air intake duct uniform. Therefore, even if a 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 level. Further, in conjunction with this, a flying object to which the present invention is applied can perform more vigorous movements than before.
【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 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 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 flying vehicle ramjet engine.
Claims (1)
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、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。Claims: 1. A ramjet engine comprising a plurality of air intake ducts and a fuel nozzle provided in each air intake duct for injecting fluid fuel, wherein the air flow rate into each air intake duct causes the A ramjet engine characterized by being provided with a fuel control device that adjusts the amount of fluid fuel injected from 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 true JPH04259649A (en) | 1992-09-16 |
| JP2738987B2 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) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109650A (en) * | 2021-10-27 | 2022-03-01 | 厦门大学 | Integral liquid rocket punching combined power device |
Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02163448A (en) * | 1988-12-16 | 1990-06-22 | Tech Res & Dev Inst Of Japan Def Agency | Gas generator for ram rocket |
-
1991
- 1991-02-14 JP JP3020930A patent/JP2738987B2/en not_active Expired - Fee Related
Patent Citations (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH02163448A (en) * | 1988-12-16 | 1990-06-22 | Tech Res & Dev Inst Of Japan Def Agency | Gas generator for ram rocket |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114109650A (en) * | 2021-10-27 | 2022-03-01 | 厦门大学 | Integral liquid rocket punching combined power device |
| CN114109650B (en) * | 2021-10-27 | 2023-02-28 | 厦门大学 | Integral liquid rocket punching combined power device |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2738987B2 (en) | 1998-04-08 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A01 | Written decision to grant a patent or to grant a registration (utility model) |
Free format text: JAPANESE INTERMEDIATE CODE: A01 Effective date: 19971216 |
|
| LAPS | Cancellation because of no payment of annual fees |