JPH07174046A - Oxygen/hydrogen rocket engine - Google Patents
Oxygen/hydrogen rocket engineInfo
- Publication number
- JPH07174046A JPH07174046A JP5226335A JP22633593A JPH07174046A JP H07174046 A JPH07174046 A JP H07174046A JP 5226335 A JP5226335 A JP 5226335A JP 22633593 A JP22633593 A JP 22633593A JP H07174046 A JPH07174046 A JP H07174046A
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- main combustion
- angle
- distributor
- attached
- 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.)
- Pending
Links
Abstract
Description
【０００１】[0001]
【産業上の利用分野】主として航空機の推進機として利
用出来る。[Industrial field of application] Mainly used as a propulsion device for aircraft.
【０００２】[0002]
【従来の技術】従来、航空機の推進機としては、プロペ
ラによるもの、ジェット・エンジン、ケロシン・ロケッ
ト等があった。2. Description of the Related Art Conventionally, propellers for airplanes include those using propellers, jet engines, and kerosene rockets.
【０００３】[0003]
【発明が解決しようとする課題】此れ等には皆燃料とし
て石油を使用する為有毒な排ガスが出るのと石油の枯渇
後には使用できなくなるという欠点があった。All of these have the drawbacks that, since petroleum is used as a fuel, toxic exhaust gas is emitted and it cannot be used after petroleum is exhausted.
【０００４】[0004]
【課題を解決する為の手段】直円筒状の主燃焼室（１）
の尾部にスロート（１９）を持つノズル（１８）を設
け、頭部に小燃焼室（７）を設けて此れに混合気噴射器
（１０）と点火栓（１４）を取り付け、混合気噴射器
（１０）に管を継ないで分配器（１７）を設け此れに混
合気入口（１３）を取り付けて主燃焼室（１）と全く同
じ構成の付属機器を取り付けた主燃焼室（２）から主燃
焼室（６）までと主燃焼室（１）とを同一円周上に此の
円を含む平面に垂直に等間隔に並べてそれぞれ分配器
（１７）に管で継なぎ主燃焼室（１）から主燃焼室
（６）までを支える為にアングル（２１）アングル（２
２）アングル（２３）アングル（２４）を取り付けてア
ングル（２１）とアングル（２３）の外側に冷却気入口
（２５）と冷却気入口（２６）を開けたナセル（２０）
を取り付ける。本発明は以上の様な構成よりなる酸素水
素ロケット・エンジンである。[Means for Solving the Problem] Right cylinder main combustion chamber (1)
A nozzle (18) having a throat (19) is provided at the tail of the, and a small combustion chamber (7) is provided at the head, and a mixture injection device (10) and a spark plug (14) are attached to this, and mixture injection is performed. A main combustion chamber (2) in which a distributor (17) is provided without connecting pipes to the vessel (10), an air-fuel mixture inlet (13) is attached to this, and auxiliary equipment having exactly the same configuration as the main combustion chamber (1) is attached. ) To the main combustion chamber (6) and the main combustion chamber (1) are arranged on the same circumference at equal intervals perpendicular to the plane containing this circle, and are connected to the distributor (17) by pipes. Angle (21) Angle (2) to support from (1) to main combustion chamber (6)
2) Angle (23) Attaching the angle (24), the nacelle (20) with the cooling air inlet (25) and the cooling air inlet (26) opened on the outside of the angle (21) and the angle (23).
Attach. The present invention is an oxygen-hydrogen rocket engine having the above structure.
【０００５】[0005]
【作用】酸素タンクと水素タンクから気化器を経て混合
気入口（１３）へ入った酸素水素混合気を分配器（１
７）によって混合気噴射器（１０）へ送り、混合気噴射
器（１０）によって混合気を小燃焼室（７）の中へ噴射
し、点火栓（１４）によって点火燃焼させるが主燃焼室
（１）の中に溜まった燃焼生成水蒸気は熱解離状態と成
って小燃焼室（７）内の後の燃焼によって再燃焼をくり
返してスロート（１９）を持つノズル（１８）より噴出
して推力を得る。同様にして主燃焼室（２）以下の主燃
焼室の中で順次燃焼生成水蒸気を再燃焼させて大きな推
力を得る。The oxygen-hydrogen mixture entering the mixture inlet (13) from the oxygen tank and the hydrogen tank via the vaporizer is distributed to the distributor (1
7) sends it to the air-fuel mixture injector (10), injects the air-fuel mixture into the small combustion chamber (7) by the air-fuel mixture injector (10), and ignites and burns it by the spark plug (14). The combustion-generated steam accumulated in 1) becomes a thermal dissociation state, and is repeatedly re-combusted by the subsequent combustion in the small combustion chamber (7) and jetted from the nozzle (18) having the throat (19) to generate thrust. obtain. Similarly, in the main combustion chambers below the main combustion chamber (2), the combustion-generated steam is sequentially re-combusted to obtain a large thrust.
【０００６】[0006]
【実施例】以下、本発明の実施例について説明する。直
円筒状の主燃焼室（１）の尾部にスロート（１９）を持
つノズル（１８）を設け、頭部に小燃焼室（７）を設け
て此れに混合気噴射器（１０）と点火栓（１４）を取り
付け、混合気噴射器（１０）に管を継ないで分配器（１
７）を設け此れに混合気入口（１３）を取り付けて主燃
焼室（１）と全く同じ構成の付属機器を取り付けた主燃
焼室（２）から主燃焼室（６）までと主燃焼室（１）と
を同一円周上に此の円を含む平面に垂直に等間隔に並べ
てそれぞれ分配器（１７）に管で継なぎ主燃焼室（１）
から主燃焼室（６）までを支える為にアングル（２１）
アングル（２２）アングル（２３）アングル（２４）を
取り付けてアングル（２１）とアングル（２３）の外側
に冷却気入口（２５）と冷却気入口（２６）を開けたナ
セル（２０）を取り付ける。本発明は以上の様な構成よ
りなる酸素水素ロケット・エンジンであるから、此れを
運転する場合には、酸素タンクと水素タンクから気化器
を経て混合気入口（１３）へ入った酸素水素混合気を分
配器（１７）によって混合気噴射器（１０）へ送り、混
合気噴射器（１０）によって混合気を小燃焼室（７）の
中へ噴射し、点火栓（１４）によって点火燃焼させるが
主燃焼室（１）の中に溜まった燃焼生成水蒸気は熱解離
状態と成って小燃焼室（７）内の後の燃焼によって再燃
焼をくり返してスロート（１９）を持つノズル（１８）
より噴出して推力を得る。同様にして主燃焼室（２）以
下の主燃焼室の中で順次燃焼生成水蒸気を再燃焼させて
大きな推力を得る。EXAMPLES Examples of the present invention will be described below. A nozzle (18) having a throat (19) is provided at the tail of the main combustion chamber (1) having a right cylindrical shape, and a small combustion chamber (7) is provided at the head of the main combustion chamber (1), where an air-fuel mixture injector (10) and ignition are performed. A stopper (14) is attached, and the distributor (1
7) provided with an air-fuel mixture inlet (13) and attached auxiliary equipment having exactly the same configuration as the main combustion chamber (1) to the main combustion chamber (6) and the main combustion chamber (6) (1) and (1) are arranged on the same circumference perpendicularly to the plane containing this circle at equal intervals and connected to a distributor (17) by a pipe, respectively, and the main combustion chamber (1)
To the main combustion chamber (6) to the angle (21)
Angle (22) Angle (23) Angle (24) is attached and the nacelle (20) with the cooling air inlet (25) and the cooling air inlet (26) opened is attached to the outside of the angle (21) and the angle (23). Since the present invention is an oxygen-hydrogen rocket engine having the above-mentioned configuration, when operating this, an oxygen-hydrogen mixture is introduced from the oxygen tank and the hydrogen tank through the vaporizer into the mixture inlet (13). The air is sent to the air-fuel mixture injector (10) by the distributor (17), the air-fuel mixture is injected into the small combustion chamber (7) by the air-fuel mixture injector (10), and is ignited and burned by the spark plug (14). The combustion-generated steam accumulated in the main combustion chamber (1) is in a thermal dissociation state, and is repeatedly re-combusted by the subsequent combustion in the small combustion chamber (7) to have a nozzle (18) having a throat (19).
Get more thrust and get thrust. Similarly, in the main combustion chambers below the main combustion chamber (2), the combustion-generated steam is sequentially re-combusted to obtain a large thrust.
【０００７】[0007]
【発明の効果】排気が水蒸気であるので無公害であり又
石油枯渇後も有効である。EFFECT OF THE INVENTION Since the exhaust gas is water vapor, it is non-polluting and is effective even after petroleum depletion.
【図１】本発明のＡ−Ａ断面図である。FIG. 1 is a sectional view taken along the line AA of the present invention.
【図２】本発明の平面図である。FIG. 2 is a plan view of the present invention.
１ 主燃焼室 １０ 混合気噴射器
１９ スロート ２ 主燃焼室 １１ 混合気噴射器
２０ ナセル ３ 主燃焼室 １２ 混合気噴射器
２１ アングル ４ 主燃焼室 １３ 混合気入口
２２ アングル ５ 主燃焼室 １４ 点火栓
２３ アングル ６ 主燃焼室 １５ 点火栓
２４ アングル ７ 小燃焼室 １６ 点火栓
２５ 冷却気入口 ８ 小燃焼室 １７ 分配器
２６ 冷却気入口 ９ 小燃焼室 １８ ノズル1 Main combustion chamber 10 Mixture injector
19 Throat 2 Main combustion chamber 11 Mixture injector
20 Nacelle 3 Main combustion chamber 12 Mixture injector
21 Angle 4 Main combustion chamber 13 Mixture inlet
22 angle 5 main combustion chamber 14 spark plug
23 Angle 6 Main combustion chamber 15 Spark plug
24 angle 7 small combustion chamber 16 spark plug
25 Cooling air inlet 8 Small combustion chamber 17 Distributor
26 Cooling air inlet 9 Small combustion chamber 18 Nozzle
Claims (1)
ト（１９）を持つノズル（１８）を設け、頭部に小燃焼
室（７）を設けて此れに混合気噴射器（１０）と点火栓
（１４）を取り付け、混合気噴射器（１０）に管を継な
いで分配器（１７）を設け此れに混合気入口（１３）を
取り付けて主燃焼室（１）と全く同じ構成の付属機器を
取り付けた主燃焼室（２）から主燃焼室（６）までと主
燃焼室（１）とを同一円周上に此の円を含む平面に垂直
に等間隔に並べてそれぞれ分配器（１７）に管で継なぎ
主燃焼室（１）から主燃焼室（６）までを支える為にア
ングル（２１）アングル（２２）アングル（２３）アン
グル（２４）を取り付けてアングル（２１）とアングル
（２３）の外側に冷却気入口（２５）と冷却気入口（２
６）を開けたナセル（２０）を取り付けた酸素水素ロケ
ット・エンジン。1. A straight cylinder-shaped main combustion chamber (1) is provided with a nozzle (18) having a throat (19) at a tail portion thereof, and a small combustion chamber (7) is provided at a head portion thereof, where a mixture injection device is provided. (10) and a spark plug (14) are attached, a distributor (17) is provided without connecting pipes to the air-fuel mixture injector (10), and an air-fuel mixture inlet (13) is attached to this, and the main combustion chamber (1) is attached. The main combustion chamber (2) to the main combustion chamber (6) and the main combustion chamber (6), which are equipped with accessories having exactly the same structure as the above, are arranged on the same circumference at equal intervals perpendicular to a plane including these circles. Angle (21), angle (22), angle (23) and angle (24) are attached to the distributors (17) to connect them to each other with pipes to support the main combustion chamber (1) to the main combustion chamber (6). Outside the (21) and the angle (23) are the cooling air inlet (25) and the cooling air inlet (2
Oxyhydrogen rocket engine with nacelle (20) opened 6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5226335A JPH07174046A (en) | 1993-07-26 | 1993-07-26 | Oxygen/hydrogen rocket engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP5226335A JPH07174046A (en) | 1993-07-26 | 1993-07-26 | Oxygen/hydrogen rocket engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH07174046A true JPH07174046A (en) | 1995-07-11 |
Family
ID=16843558
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP5226335A Pending JPH07174046A (en) | 1993-07-26 | 1993-07-26 | Oxygen/hydrogen rocket engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH07174046A (en) |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6053650A (en) * | 1983-08-04 | 1985-03-27 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング | Bypass type rocket engine and operation method thereof |
| JPS62291454A (en) * | 1986-04-16 | 1987-12-18 | マットラ マーコニ スペース ユーケイ リミテッド | Thruster |
-
1993
- 1993-07-26 JP JP5226335A patent/JPH07174046A/en active Pending
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS6053650A (en) * | 1983-08-04 | 1985-03-27 | メツセルシユミツト−ベルコウ−ブロ−ム・ゲゼルシヤフト・ミト・ベシユレンクテル・ハフツング | Bypass type rocket engine and operation method thereof |
| JPS62291454A (en) * | 1986-04-16 | 1987-12-18 | マットラ マーコニ スペース ユーケイ リミテッド | Thruster |
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