JPH0385357A - Liquid methane fuel air liquefaction engine - Google Patents
Liquid methane fuel air liquefaction engineInfo
- Publication number
- JPH0385357A JPH0385357A JP21857789A JP21857789A JPH0385357A JP H0385357 A JPH0385357 A JP H0385357A JP 21857789 A JP21857789 A JP 21857789A JP 21857789 A JP21857789 A JP 21857789A JP H0385357 A JPH0385357 A JP H0385357A
- Authority
- JP
- Japan
- Prior art keywords
- air
- liquid methane
- liquid
- methane
- tank
- 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
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 70
- 239000007788 liquid Substances 0.000 title claims abstract description 43
- 239000000446 fuel Substances 0.000 title claims description 9
- 238000009835 boiling Methods 0.000 claims abstract description 12
- 238000002485 combustion reaction Methods 0.000 claims abstract description 12
- 238000009834 vaporization Methods 0.000 claims abstract description 4
- 230000008016 vaporization Effects 0.000 claims abstract description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 2
- 238000001704 evaporation Methods 0.000 abstract description 2
- 230000008020 evaporation Effects 0.000 abstract description 2
- 239000002826 coolant Substances 0.000 abstract 2
- 230000008602 contraction Effects 0.000 abstract 1
- 238000000605 extraction Methods 0.000 abstract 1
- 239000001257 hydrogen Substances 0.000 description 20
- 229910052739 hydrogen Inorganic materials 0.000 description 20
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 19
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 description 7
- 230000000694 effects Effects 0.000 description 6
- 239000002828 fuel tank Substances 0.000 description 4
- 239000000203 mixture Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 3
- 239000003507 refrigerant Substances 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 150000002431 hydrogen Chemical class 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 239000001301 oxygen Substances 0.000 description 1
- 229910052760 oxygen Inorganic materials 0.000 description 1
Landscapes
- Feeding And Controlling Fuel (AREA)
- Jet Pumps And Other Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
〔産業上の利用分野〕
本発明はロケットブースタおよび宇宙往還機等に適用さ
れる液体メタンを燃料とする空気液化式エンジンに関す
る。DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to an air liquefaction engine using liquid methane as fuel, which is applied to rocket boosters, spacecraft, etc.
ロケットブースタや宇宙往還機等に用いる従来の空気液
化式エンジンは燃料に液体水素またはスラッシュ水素（
液体水素と固体水素の混合物）を用い、かつ、それら液
体水素またはスラッシュ水素を冷熱源として、吸入した
空気を液化し、液化空気と水素を燃焼させてロケットエ
ンジンを作動させるものである。Conventional air-liquefaction engines used in rocket boosters, spacecraft, etc. use liquid hydrogen or slush hydrogen (
The rocket engine is operated by using liquid hydrogen or slush hydrogen (a mixture of liquid hydrogen and solid hydrogen) and using the liquid hydrogen or slush hydrogen as a cold heat source to liquefy the inhaled air and burn the liquefied air and hydrogen.
上記従来の空気液化式エンジンには解決すべき次の課題
があった。The above-mentioned conventional air liquefaction engine had the following problems to be solved.
即ち、従来の空気液化式エンジンは燃料に液体水素また
はスラッシュ水素を用いる。液体水素およびスラッシュ
水素は密度が極めて小さい（それぞれ０．０７１ｇｒ／
ａｍコおよび０．０８１ｇｒ／ｃｍ”）ため、燃料タン
クの容積が過大となり、ロケットブースタおよび宇宙往
還機の重量増加の原因となっている。That is, conventional air-liquefied engines use liquid hydrogen or slush hydrogen as fuel. Liquid hydrogen and slush hydrogen have extremely low densities (0.071 gr/each)
amco and 0.081gr/cm"), the volume of the fuel tank becomes excessive, causing an increase in the weight of rocket boosters and spacecraft.
そこで燃料タンクの容積の減少をはかるため、燃料を密
度の比較的大きい液体メタン（密度は０．４２３ｇｒ／
ｃｍ”）にかえるとすると、液体水素の沸点は２０に、
大気圧における空気の液化温度は７９になので液体水素
の冷熱源を用いて空気を液化することは可能であるが、
液体メタンの沸点は１１１．５ ｋであるため、−船釣
には液体メタンを用いての空気液化は不可能という問題
が生じる。Therefore, in order to reduce the volume of the fuel tank, the fuel was replaced with liquid methane, which has a relatively high density (density is 0.423gr/
cm”), the boiling point of liquid hydrogen is 20,
The liquefaction temperature of air at atmospheric pressure is 79, so it is possible to liquefy air using a liquid hydrogen cold source.
Since the boiling point of liquid methane is 111.5 k, a problem arises in that it is impossible to liquefy air using liquid methane for boat fishing.
本発明は上記課題の解決手段として、空気液化温度を液
体メタンの沸点以上に圧縮可能な空気の圧縮機と、同圧
縮機の圧縮した空気を液体メタンの気化熱により液化す
る空気液化器と、同空気液化器によって液化された空気
を支燃剤として燃焼し推力を発生するとともに減圧され
上記空気液化器に供給されて空気液化に供せられる液体
メタンを貯える液体メタンタンクとを具備してなること
を特徴とする液体メタン燃料空気液化式エンジンを提供
しようとするものである。The present invention provides an air compressor that can compress the air liquefaction temperature to a temperature higher than the boiling point of liquid methane, an air liquefier that liquefies the air compressed by the compressor using the heat of vaporization of the liquid methane, and and a liquid methane tank that stores liquid methane which is combusted using the air liquefied by the air liquefier as a combustion support agent to generate thrust and is depressurized and supplied to the air liquefier for air liquefaction. The present invention aims to provide a liquid methane fuel air liquefaction engine characterized by:
本発明は上記のように構成されるので次の作用を有する
。Since the present invention is configured as described above, it has the following effects.
（１）液体メタンを減圧することにより、液体メタンの
沸点が低下する０例えば、圧力０．４３ｋｇ／ＣＭ”ａ
ｂｓにおいては沸点が１０２ ｋ 、圧力０．２８ｋｇ
／ｃｓ＋”ａｂｓにおいては沸点が９８にである。(1) By reducing the pressure of liquid methane, the boiling point of liquid methane decreases. For example, the pressure is 0.43 kg/CM"a
In bs, the boiling point is 102 k and the pressure is 0.28 kg.
/cs+"abs has a boiling point of 98.
（２）吸入空気を昇圧することにより、空気の液化温度
が上昇する０例えば、圧力１０ｋｇ／ｃｍ”ａｂｓにお
いて１０６ｋ、圧力１２．８ｋｇ／ｃｍ”ａｂｓにおい
て１１０にである。(2) By increasing the pressure of the intake air, the liquefaction temperature of the air increases. For example, it is 106 k at a pressure of 10 kg/cm" abs, and 110 k at a pressure of 12.8 kg/cm" abs.
（３）以上（１）（２）より液体メタンの沸点が空気液
化温度より低くなるため、液体メタンの蒸発潜熱（圧力
０．４３ｋｇ／ｃｍ”ａｂｓにおいて１２６．１ｋｒａ
ｌ／ｋｇ。(3) From (1) and (2) above, the boiling point of liquid methane is lower than the air liquefaction temperature, so the latent heat of vaporization of liquid methane (126.1 kra
l/kg.
圧力０．２８ｋｇ／ｃｍ”ａｂｓにおいて１２７．５ｋ
ｒａｌ／ｋｇ）を用いて、空気を液化できる。127.5k at pressure 0.28kg/cm”abs
ral/kg) can be used to liquefy air.
（４）この結果、液体メタンを用いて空気液化が可能と
なり、水素より高密度のメタンの燃料化が果たされ、従
来に比し迩かに小さい燃料タンクで目的を達する空気液
化式エンジンを得られる。(4) As a result, it has become possible to liquefy air using liquid methane, and methane, which has a higher density than hydrogen, can be used as a fuel, making it possible to create an air-liquefied engine that achieves its purpose with a much smaller fuel tank than before. can get.
本発明の第１実施例を第１図により説明する。 A first embodiment of the present invention will be described with reference to FIG.
第１図において、タンク１には、液体メタンが大気圧（
１，０３３ｋｇ／ｃｓ”ａｂｓ） 、沸点温度（１１１
，５ｋ ）状態で蓄えられている。冷媒用の液体メタン
は絞り２を通って減圧し、空気液化器３を通ってロケッ
トエンジンのノズル１２に設置されているエゼクタ４に
よって外部へ放出される。燃焼用の液体メタンはポンプ
５によって増圧され、噴射器６に導かれ燃焼室７に噴射
される。空気は空気取入口８から入り、空気予冷器９を
通って空気圧縮機１０で圧縮され、空気液化器３に入る
。In Figure 1, liquid methane is in tank 1 at atmospheric pressure (
1,033kg/cs”abs), boiling point temperature (111
, 5k) state. Liquid methane for refrigerant is depressurized through a throttle 2, passes through an air liquefier 3, and is discharged to the outside by an ejector 4 installed in a nozzle 12 of a rocket engine. Liquid methane for combustion is pressurized by a pump 5, guided to an injector 6, and injected into a combustion chamber 7. Air enters through air intake 8, passes through air precooler 9, is compressed by air compressor 10, and enters air liquefier 3.
空気液化器３において、冷媒の液体メタンの蒸発熱によ
って空気は液化される。液化された液化空気はポンプ１
１が増圧され、空気予冷器９に入り、その後、噴射器６
に導かれ、燃焼室７へ噴射される。ｊ２！焼室７におい
て、液体メタンと空気が燃焼し、ノズル１２より噴出し
て推力を発生する。In the air liquefier 3, air is liquefied by the heat of evaporation of liquid methane as a refrigerant. The liquefied air is pumped to pump 1.
1 is increased in pressure and enters the air precooler 9, then the injector 6
and is injected into the combustion chamber 7. j2! In the combustion chamber 7, liquid methane and air are combusted and ejected from the nozzle 12 to generate thrust.
次に本発明の第２実施例を第２図により説明する。第２
図は第１図のエンジンにタンク１３〜スプレーヘツド１
５の液体酸素系統を付加し、エンジンの単位空気流量当
りの推力の向上を図ったものである。付加された液体酸
素系統の作用について説明すると、タンク１３内の液体
酸素はポンプ１４で約１５ｋｇ／ｃｍ”ａｂｓに増圧さ
れ、スプレーヘ−）ド１５より空気液化器３へ噴霧され
、空気流に混入する。この混入により、液体酸素の冷熱
源と空気中の酸素濃度上昇のため空気の液化が促進され
ると共に、液体酸素の混入による酸化剤量の増加により
、エンジン推力が増加する。その他の槽底、作用につい
ては第１実施例と同様である。Next, a second embodiment of the present invention will be described with reference to FIG. Second
The figure shows the engine in Figure 1 with tank 13 to spray head 1.
5 liquid oxygen system was added to improve the thrust per unit air flow rate of the engine. To explain the operation of the added liquid oxygen system, the liquid oxygen in the tank 13 is increased in pressure to about 15 kg/cm" abs by the pump 14, and is sprayed from the spray head 15 to the air liquefier 3, and is added to the air flow. This mixture promotes the liquefaction of the air due to the cold heat source of liquid oxygen and the increase in the oxygen concentration in the air, and the engine thrust increases due to the increase in the amount of oxidizer due to the mixture of liquid oxygen.Others The tank bottom and operation are the same as in the first embodiment.
次に本発明の第３実施例を第３図により説明する。第３
図と第２図との違いは第２図のエゼクタ−４が第３図で
は小ノズル４′にかわった点である。Next, a third embodiment of the present invention will be described with reference to FIG. Third
The difference between this figure and FIG. 2 is that the ejector 4 in FIG. 2 is replaced by a small nozzle 4' in FIG.
この変更によりノズル１２のサクション効果が利かなく
なるため、空気液化器３の熱交換器内のメタンの沸点は
１１１．５ ｋ以上（大気圧１．０３３ａｔａ以上にお
ける沸点）となるので、空気の液化温度をこれ以上にす
る必要がある。そこで空気圧縮ｉｔｏの能力を向上し、
出口圧力を約２０ｋｇ／ａｓ”ａｂｓとする。Due to this change, the suction effect of the nozzle 12 becomes ineffective, and the boiling point of methane in the heat exchanger of the air liquefier 3 becomes 111.5 k or more (the boiling point at atmospheric pressure 1.033 ata or more), so the liquefaction of air becomes impossible. The temperature needs to be higher than this. Therefore, we improved the ability of air compressor ITO,
The outlet pressure is approximately 20 kg/as"abs.
また、液体酸素ポンプ１４の吐出圧も約２５ｋｇ／ｃｍ
”ａｂｓとする。Also, the discharge pressure of the liquid oxygen pump 14 is approximately 25 kg/cm.
``Abs.
本実施例によれば、空気圧縮機１０、ポンプ１４の能力
増加が必要な半面、エゼクタ−４の除去により、システ
ムが簡素化されるという利点を有する。According to this embodiment, although it is necessary to increase the capacity of the air compressor 10 and the pump 14, there is an advantage that the system is simplified by removing the ejector 4.
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
。Since the present invention is configured as described above, it has the following effects.
即ち、従来の液体水素またはスラッシュ水素（液体水素
と固体水素の混合物）を燃料とする空気液化式エンジン
の欠点である過大な燃料タンクの容積を減少させ得る効
果を有する。That is, it has the effect of reducing the excessive volume of the fuel tank, which is a drawback of conventional air-liquefaction engines that use liquid hydrogen or slush hydrogen (a mixture of liquid hydrogen and solid hydrogen) as fuel.
これによって、ロケットブースタおよび宇宙往還機の機
体重量の低減が図られ、性能向上が可能となる。This reduces the weight of the rocket booster and the spacecraft, making it possible to improve performance.
第１図は本発明の第１実施例の、第２図は同じく第２実
施例の、第３図は同じく第３実施例の各液体メタン燃料
空気液化式エンジンの模式的縦断面図である。
１・・・タンク（液体メタン用）、 ２・・・絞り、３
・・・空気液化器、 ４・・・エゼクタ、５・・・
ポンプ、 ６・・・噴射器、７・・・燃焼室
、 ８・・・空気取入口、９・・・空気予冷器
、 １０・・・空気圧ｌ１ｉＩｌ！、１１・・・ポ
ンプ、 １２・・・ノズル、１３・・・タンク
（液体酸素用）、
１４・・・ポンプ、
１５・・・スプレーヘッド、
４′・・・小ノズル。FIG. 1 is a schematic vertical sectional view of a liquid methane fuel air liquefaction engine according to a first embodiment of the present invention, FIG. 2 is a second embodiment, and FIG. 3 is a third embodiment of the present invention. . 1... Tank (for liquid methane), 2... Throttle, 3
...Air liquefier, 4...Ejector, 5...
Pump, 6... Injector, 7... Combustion chamber, 8... Air intake, 9... Air precooler, 10... Air pressure l1iIl! , 11... Pump, 12... Nozzle, 13... Tank (for liquid oxygen), 14... Pump, 15... Spray head, 4'... Small nozzle.
Claims (1)
の圧縮機と、同圧縮機の圧縮した空気を液体メタンの気
化熱により液化する空気液化器と、同空気液化器によっ
て液化された空気を支燃剤として燃焼し推力を発生する
とともに減圧され上記空気液化器に供給されて空気液化
に供せられる液体メタンを貯える液体メタンタンクとを
具備してなることを特徴とする液体メタン燃料空気液化
式エンジン。An air compressor that can compress the air to a temperature higher than the boiling point of liquid methane, an air liquefier that liquefies the air compressed by the compressor using the heat of vaporization of liquid methane, and an air liquefier that liquefies the air by the air liquefier. A liquid methane fuel air liquefaction type characterized by comprising a liquid methane tank for storing liquid methane which is burned as a combustion support agent to generate thrust and is depressurized and supplied to the air liquefier for air liquefaction. engine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1218577A JP2647507B2 (en) | 1989-08-28 | 1989-08-28 | Liquid methane fuel air liquefied engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP1218577A JP2647507B2 (en) | 1989-08-28 | 1989-08-28 | Liquid methane fuel air liquefied engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0385357A true JPH0385357A (en) | 1991-04-10 |
| JP2647507B2 JP2647507B2 (en) | 1997-08-27 |
Family
ID=16722130
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP1218577A Expired - Fee Related JP2647507B2 (en) | 1989-08-28 | 1989-08-28 | Liquid methane fuel air liquefied engine |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP2647507B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110067673B (en) * | 2019-04-24 | 2020-10-27 | 北京航空航天大学 | Parallel precooling stamping combined propulsion system and propulsion method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5242433A (en) * | 1974-06-13 | 1977-04-02 | Honey Kasei Kk | Coating of metal surface |
| JPS62237068A (en) * | 1986-04-07 | 1987-10-17 | Mitsubishi Heavy Ind Ltd | Air liquefaction cycle rocket engine |
-
1989
- 1989-08-28 JP JP1218577A patent/JP2647507B2/en not_active Expired - Fee Related
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS5242433A (en) * | 1974-06-13 | 1977-04-02 | Honey Kasei Kk | Coating of metal surface |
| JPS62237068A (en) * | 1986-04-07 | 1987-10-17 | Mitsubishi Heavy Ind Ltd | Air liquefaction cycle rocket engine |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2647507B2 (en) | 1997-08-27 |
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