JPH0323745B2 - - Google Patents
Info
- Publication number
- JPH0323745B2 JPH0323745B2 JP62249617A JP24961787A JPH0323745B2 JP H0323745 B2 JPH0323745 B2 JP H0323745B2 JP 62249617 A JP62249617 A JP 62249617A JP 24961787 A JP24961787 A JP 24961787A JP H0323745 B2 JPH0323745 B2 JP H0323745B2
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- rocket
- nozzle
- liquid oxygen
- gas
- 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
Links
- 239000000446 fuel Substances 0.000 claims description 62
- MYMOFIZGZYHOMD-UHFFFAOYSA-N Dioxygen Chemical compound O=O MYMOFIZGZYHOMD-UHFFFAOYSA-N 0.000 claims description 40
- 239000007789 gas Substances 0.000 claims description 31
- 239000003380 propellant Substances 0.000 claims description 27
- 238000002485 combustion reaction Methods 0.000 claims description 23
- 239000007788 liquid Substances 0.000 claims description 20
- 238000000889 atomisation Methods 0.000 claims description 18
- 230000000704 physical effect Effects 0.000 claims description 7
- 239000000567 combustion gas Substances 0.000 claims description 5
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 4
- 239000001301 oxygen Substances 0.000 claims description 4
- 229910052760 oxygen Inorganic materials 0.000 claims description 4
- 239000002737 fuel gas Substances 0.000 claims description 2
- 239000001257 hydrogen Substances 0.000 description 28
- 229910052739 hydrogen Inorganic materials 0.000 description 28
- 239000003350 kerosene Substances 0.000 description 23
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 22
- 238000000034 method Methods 0.000 description 9
- 238000002347 injection Methods 0.000 description 8
- 239000007924 injection Substances 0.000 description 8
- 150000002431 hydrogen Chemical class 0.000 description 7
- 238000002156 mixing Methods 0.000 description 7
- 239000007800 oxidant agent Substances 0.000 description 6
- 229930195733 hydrocarbon Natural products 0.000 description 4
- 150000002430 hydrocarbons Chemical class 0.000 description 4
- -1 kerosene Chemical class 0.000 description 3
- 239000010409 thin film Substances 0.000 description 3
- ATUOYWHBWRKTHZ-UHFFFAOYSA-N Propane Chemical compound CCC ATUOYWHBWRKTHZ-UHFFFAOYSA-N 0.000 description 2
- 238000009835 boiling Methods 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 239000001307 helium Substances 0.000 description 2
- 229910052734 helium Inorganic materials 0.000 description 2
- SWQJXJOGLNCZEY-UHFFFAOYSA-N helium atom Chemical compound [He] SWQJXJOGLNCZEY-UHFFFAOYSA-N 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 239000004215 Carbon black (E152) Substances 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000010419 fine particle Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003534 oscillatory effect Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000001294 propane Substances 0.000 description 1
- 230000001141 propulsive effect Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Landscapes
- Nozzles (AREA)
Description
【発明の詳細な説明】
（産業上の利用分野）
この発明は、液体炭化水素等の燃料を安定燃焼
させるためのロケツト噴射器、特に物性値の異な
る複数種類の燃料を高効率で安定燃焼させるため
のロケツト噴射器に関する。[Detailed Description of the Invention] (Industrial Application Field) This invention is a rocket injector for stably burning fuel such as liquid hydrocarbon, and in particular for stably burning multiple types of fuels with different physical properties with high efficiency. Regarding rocket injectors for.
（従来技術）
従来、ケロシン等を含む高密度炭化水素と液体
酸素等の酸化剤を用いたロケツトエンジンが広く
用いられている。(Prior Art) Conventionally, rocket engines using high-density hydrocarbons such as kerosene and oxidizing agents such as liquid oxygen have been widely used.
従来の液体酸素、ケロシン等の液体燃料の組合
せの推進薬を用いたロケツトエンジンの場合、推
進薬を微粒化し、推進薬相互の混合を促進させる
ことを目的として用いられる噴射器の噴口形状を
第６図に示す。ケロシン３は、燃料供給口を経て
燃料噴口１０から燃焼室内に噴霧される。一方、
液体酸素２は燃料噴口１０の周囲に配置された液
酸噴口１１からケロシンの噴流に衝突するように
噴出させられ、推進薬どうしの衝突によつて混合
が行われる。しかし、衝突型噴射器の微粒化特性
は、噴口加工の工作精度に大きく影響を受けるた
め、同一の設計寸法の噴口でも得られる燃焼性能
に差異が生じることが多い。又、衝突点に至るま
での推進薬噴流及び衝突後の推進薬微粒化メカニ
ズムは、周囲燃焼ガス流の影響を受け易く、不安
定に陥り易いため、有害な振動燃焼を誘発しやす
い。又、噴射面への熱負荷が過大になり易い等の
欠点を有している。このために液体酸素とケロシ
ン等を推進薬とするロケツトエンジン噴射器の計
計、工作には多くの労力が必要とされてきた。 In the case of a rocket engine that uses conventional propellants that are a combination of liquid fuels such as liquid oxygen and kerosene, the nozzle shape of the injector used for the purpose of atomizing the propellant and promoting mutual mixing of the propellants is It is shown in Figure 6. The kerosene 3 is sprayed into the combustion chamber from the fuel injection port 10 via the fuel supply port. on the other hand,
The liquid oxygen 2 is ejected from a liquid acid nozzle 11 disposed around the fuel nozzle 10 so as to collide with the jet of kerosene, and the propellants are mixed by collision with each other. However, the atomization characteristics of impingement-type injectors are greatly affected by the machining accuracy of the nozzle, so differences often occur in the combustion performance obtained even with nozzles with the same design dimensions. Furthermore, the propellant jet up to the collision point and the propellant atomization mechanism after the collision are easily influenced by the surrounding combustion gas flow and easily become unstable, which tends to induce harmful oscillatory combustion. Further, it has the disadvantage that the thermal load on the injection surface tends to be excessive. For this reason, a great deal of effort has been required to measure and construct rocket engine injectors that use liquid oxygen, kerosene, etc. as propellants.
一方、近年、ロケツトエンジンを用いた究極的
飛翔体の形態は、航空機と同様に、何度も使用出
来る有翼帰還可能な単段式飛翔体（SSTO）であ
ると考えられ、その実現のためのブラン作りが試
みられている。この様なSSTOを実現するために
は、機体構造重量及びロケツトエンジン重量等を
軽くし、エンジン重量当たりの推進力を大きく、
かつ、、ロケツトが得る速度増分の配分が適切に
なるように、高度に合わせて、使用する推進薬を
順次切り替えることが必要となる。 On the other hand, in recent years, it has been thought that the ultimate form of a flying vehicle using a rocket engine is a single-stage flying vehicle (SSTO) with winged return capability that can be used many times, similar to an aircraft, and efforts are being made to realize this. Attempts are being made to make bran. In order to achieve this kind of SSTO, it is necessary to reduce the weight of the aircraft structure and rocket engine, increase the propulsive force per engine weight,
In addition, it is necessary to sequentially switch the propellants used according to the altitude so that the increase in velocity obtained by the rocket is distributed appropriately.
例えば、２種類の組合せの推進薬を切り替えて
燃焼させる直列燃焼式エンジン（打ち上げから低
高度で作動させるモード１及び高空で作動させる
モード２）によつてSSTOを実現させるために
は、理論解析によれば、各モードの推進薬選択の
条件は、モード１の推進薬平均密度ρ1、比推力
I1、モード２の推進薬平均密度ρ2、比推力I2とす
れば、
ρ1＞ρ2
I2＞I1
ρ1I1＞ρ2I2
であることが必要条件である。この条件を満たす
具体的な推進薬の組合せは、モード１に対しては
酸化剤：液体酸素
燃料：ケロシン等を含む高密度炭化水素又は液化
メタン、プロパン等軽質炭化水素
モード２に対しては
酸化剤：液体酸素
燃料：液体水素
の組合せが代表的である。 For example, in order to realize SSTO using a series combustion engine that switches between two types of propellant combinations (Mode 1 operates at low altitude from launch and Mode 2 operates at high altitude), theoretical analysis is required. According to
I 1 , the propellant average density ρ 2 in mode 2, and the specific impulse I 2 , it is necessary that ρ 1 >ρ 2 I 2 >I 1 ρ 1 I 1 >ρ 2 I 2 . The specific propellant combinations that meet this condition are: oxidizing agent for mode 1: liquid oxygen fuel: high-density hydrocarbons including kerosene, or liquefied methane, light hydrocarbons such as propane, and oxidizing agent for mode 2. A typical combination is: agent: liquid oxygen fuel: liquid hydrogen.
これまで提案されているSSTO用のロケツトエ
ンジンは、基本的には各各のモードに対応するロ
ケツト燃焼器を個別に、又は二重式に統合した燃
焼器で各各の推進薬に対応した個別の噴射器を有
する構成のものだけであつた。これは各モードに
対応する異なる燃料の物性値、例えば、上記の酸
化剤と燃料の組合せの中、モード１の燃料として
ケロシン類を用いると、密度約800〜1100Kg／m3、
沸騰温度約220〜280℃であり、これに対してモー
ド２の液体水素は密度約70Kg／m3、沸騰温度約−
253℃と２つの燃料の物性値が極端に異なり、こ
れらを１つの噴射器で、推進薬の良好な微粒化、
推進薬相互間の良好な混合状態を得ることが極め
て困難になる。従つて、燃焼に必要な条件が達成
出来ず、効率が高く安定な燃焼が実現出来ないと
いう理由によるものである。 The rocket engines for SSTO that have been proposed so far basically have rocket combustors that correspond to each mode, either individually or in a dual-integrated combustor, with individual rocket combustors that correspond to each propellant. The only one that had a configuration with an injector was This is based on the physical properties of different fuels corresponding to each mode. For example, among the above combinations of oxidizer and fuel, when kerosene is used as the fuel for mode 1, the density is approximately 800 to 1100 Kg/m 3 ,
The boiling temperature is about 220-280℃, whereas liquid hydrogen in mode 2 has a density of about 70Kg/m 3 and a boiling temperature of about -
At 253℃, the physical properties of the two fuels are extremely different, and a single injector can be used to achieve good atomization of the propellant.
It becomes extremely difficult to obtain good mixing between the propellants. Therefore, the conditions necessary for combustion cannot be achieved, and highly efficient and stable combustion cannot be achieved.
（この発明が解決しようとする問題点）
本発明は、ケロシン等の液体燃料を安定に高効
率で燃焼させることが出来るだけでなく、物性値
が極端に異なる複数の推進薬を切り替え燃焼させ
る場合にも、１つの噴射器で最適な燃焼条件を達
成し、高効率な燃焼を実現しようとするものであ
る。(Problems to be Solved by the Invention) The present invention not only allows liquid fuel such as kerosene to be burned stably and with high efficiency, but also enables the switching and combustion of multiple propellants with extremely different physical properties. The aim is to achieve optimal combustion conditions with a single injector and achieve highly efficient combustion.
（問題点を解決するための手段）
この発明のロケツト噴射器は、気化した液体水
素の噴口、該水素の噴口から噴出する噴流中に液
体燃料を送入し微粒化する燃料噴口、該燃料噴口
と同軸型噴口として構成された液体酸素噴口とを
有することを特徴とする。(Means for Solving the Problems) The rocket injector of the present invention includes a nozzle for vaporized liquid hydrogen, a fuel nozzle that feeds liquid fuel into a jet stream ejected from the hydrogen nozzle to atomize it, and a fuel nozzle for atomizing the liquid fuel. and a liquid oxygen nozzle configured as a coaxial nozzle.
そして、特に有利に実施されるのは、物性値の
異なる２種類の燃料、例えばケロシンと液体水素
及び液体酸素を推進薬とし、まず主として第１の
燃料と液体酸素を燃焼させ、次いで第２の燃料に
切り替えて同一の燃焼器で燃焼させる液体ロケツ
トエンジンの燃焼器としてであつて、第１の主燃
料例えばケロシンと液体酸素を燃焼させる場合、
気化した第２の従燃料例えば水素の噴流中に第１
の燃料を送入し、該噴流によつて上記第１の燃料
を微粒化し、液体酸素と混合燃焼させることを特
徴とする。 A particularly advantageous method is to use two types of fuels with different physical properties, such as kerosene, liquid hydrogen, and liquid oxygen, as propellants, and first mainly burn the first fuel and liquid oxygen, and then burn the second fuel. As a combustor for a liquid rocket engine that switches to fuel and burns it in the same combustor, when the first main fuel, for example, kerosene and liquid oxygen are burned,
The vaporized second fuel, e.g.
The first fuel is atomized by the jet stream, and mixed with liquid oxygen and combusted.
上記燃料の微粒化用ガスは、例えばロケツトノ
ズル及びロケツト燃焼室を冷却した燃料の気化ガ
スであつてもよく、或いは高温ガス発生器の燃焼
ガスであつてもよい。 The fuel atomization gas may be, for example, vaporized fuel gas that has cooled the rocket nozzle and rocket combustion chamber, or may be combustion gas from a high-temperature gas generator.
（実施例）
以下、図面を参照して本発明を実施例によつて
詳細に説明する。この実施例においては、SSTO
用のロケツトエンジンとして本発明を実施した場
合を示し、燃料の組合せの１例として、モード１
の推進薬として酸化剤に液体酸素を、燃料にケロ
シン類及び従燃料として水素を、モード２に対し
て液体酸素と液体水素を用いる場合を示す。(Examples) Hereinafter, the present invention will be described in detail by examples with reference to the drawings. In this example, SSTO
This shows the case where the present invention is implemented as a rocket engine for
The case is shown in which liquid oxygen is used as an oxidizing agent as a propellant, kerosene is used as a fuel, and hydrogen is used as a secondary fuel, and liquid oxygen and liquid hydrogen are used for mode 2.
すなわち、第１図１に示すモード１の作動時に
は、従燃料として用いられる液体水素４は、ポン
プ８によつてロケツトノズル９及びロケツト燃焼
室を冷却し、その１部は噴射器１から燃焼器５中
に噴出すると共に、高温ガス発生器６に送入され
る。一方、液体酸素２は同様にポンプ８′によつ
て燃焼器５に送入されると共にその１部は高温ガ
ス発生器６に送られ、上記の水素を燃焼させて高
温ガスを発生する。この高温ガスはタービン７，
７′によつてポンプ８，８′，８″を駆動した後、
ノズル９に排出される。又、主燃料３はポンプ
８″で燃焼室５に圧送される。 That is, during operation in mode 1 shown in FIG. At the same time, the gas is ejected into the high temperature gas generator 6. On the other hand, the liquid oxygen 2 is similarly sent to the combustor 5 by the pump 8', and a portion of it is sent to the high temperature gas generator 6, where the hydrogen is combusted to generate high temperature gas. This high temperature gas is transferred to the turbine 7,
After driving pumps 8, 8', 8'' by 7',
It is discharged into the nozzle 9. Further, the main fuel 3 is pumped into the combustion chamber 5 by a pump 8''.
第１図２に示すモード２時には、液体水素４の
みが燃料として使用され、各部の作動は同図１の
場合と同じである。 In mode 2 shown in FIG. 1, only liquid hydrogen 4 is used as fuel, and the operations of each part are the same as in the case of FIG. 1.
本発明においては、上記のモード１、モード２
の何れにおいても、同じ噴射器を用いようとする
ものであるが、その詳細を第２図に示す。同図１
において、モード１では、主推進薬であるケロシ
ン３は噴口１３から、液体酸素２は噴口１４の中
心に設けられた酸素噴口１２から燃焼器中に噴出
する。燃料噴口１４の上流側壁には、水素の噴出
口１４′が開いており、従燃料としてのガス化し
た水素が燃料噴口１４中で噴出する。 In the present invention, the above mode 1, mode 2
The same injector is used in both cases, the details of which are shown in FIG. Figure 1
In mode 1, kerosene 3, which is the main propellant, is ejected from the nozzle 13 and liquid oxygen 2 is ejected from the oxygen nozzle 12 provided at the center of the nozzle 14 into the combustor. A hydrogen ejection port 14' is opened in the upstream side wall of the fuel injection port 14, and gasified hydrogen as a secondary fuel is ejected from the fuel injection port 14.
モード１では、液体酸素、ケロシンが質量比で
約2.6：0.9の比率で噴射され、水素は気体状態で
質量比約0.1が噴射される。噴射される気体推進
薬の質量割合は、液体状態の主推進薬の質量と比
して少ないが、体積比は約10〜100倍となる。第
２図２，３は水素の噴出口１３部位での断面を示
す。高速で噴射される気体状態の水素噴流は、円
孔又はスリツト状流路を通じて流れに直交又は傾
斜し或いは接線方向に流入する液体推進薬である
ケロシンを、この水素噴流のエネルギによつてａ
位置で微粒化する。さらにこの微粒子を含む高速
流が同軸噴口の中心部から噴射される液体酸素と
ｂ位置で接触し、液体酸素の微粒化及び燃料との
良好な混合状態を実現する。 In mode 1, liquid oxygen and kerosene are injected at a mass ratio of approximately 2.6:0.9, and hydrogen is injected in a gaseous state at a mass ratio of approximately 0.1. Although the mass proportion of the injected gaseous propellant is small compared to the mass of the main propellant in the liquid state, the volume ratio is approximately 10 to 100 times greater. 2 and 3 show a cross section at the hydrogen ejection port 13. The gaseous hydrogen jet that is injected at high speed causes the liquid propellant kerosene, which flows perpendicularly, obliquely, or tangentially to the flow through a circular hole or slit-like channel, to be a
Atomize in position. Furthermore, this high-speed flow containing fine particles contacts the liquid oxygen injected from the center of the coaxial nozzle at position b, thereby realizing atomization of the liquid oxygen and a good mixing state with the fuel.
モード２への切り替えに当つては、ケロシンの
噴射が止められ、ヘリウムガス等によつて残留ケ
ロシンをパージする。その後、水素の高速流と液
体酸素噴流の相互作用によつて微粒化、混合がな
されるが、これは従来の液体酸素、液体水素用同
軸型噴口と同じとなる。 When switching to mode 2, the injection of kerosene is stopped and residual kerosene is purged with helium gas or the like. Thereafter, the interaction between the high-speed flow of hydrogen and the jet of liquid oxygen causes atomization and mixing, which is the same as with conventional coaxial nozzles for liquid oxygen and liquid hydrogen.
上記の噴口１１を18ケ配置した推力10kN（約１
トンの推進力）の噴射器を第３図に示す。この燃
焼器の燃焼実験を液体酸素（密度1142Kg／m3、粘
度0.166mm2／ｓ、何れも−183℃での値）、ケロシ
ン熱料（密度860Kg／m3、粘度５mm2／ｓ、何れも
15℃での値）及び水素（密度7.8Kg／m3、粘度
1.12mm2／ｓ、何れも15℃、圧力100気圧での値）
を用いて行つた。噴射質量比は液体酸素：ケロシ
ン：水素＝2.6：0.9：0.1、燃焼圧力10MPa（約
100Kg／cm2）の条件で良好な燃焼、すなわち燃焼
効率約98％以上で安定な燃焼が実証された。な
お、図中１５は点火用トーチガスの流路を示す。 Thrust of 10kN (approximately 1
Figure 3 shows an injector with a propelling force of 10,000 tons. Combustion experiments using this combustor were conducted using liquid oxygen (density 1142Kg/m 3 , viscosity 0.166mm 2 /s, both values at -183°C) and kerosene heating material (density 860Kg/m 3 , viscosity 5mm 2 /s, both values at -183°C). too
value at 15℃) and hydrogen (density 7.8Kg/m 3 , viscosity
1.12mm 2 /s, all values at 15℃ and 100atm pressure)
I did it using The injection mass ratio is liquid oxygen: kerosene: hydrogen = 2.6:0.9:0.1, combustion pressure 10 MPa (approx.
100Kg/cm 2 ), stable combustion was demonstrated with a combustion efficiency of approximately 98% or higher. Note that 15 in the figure indicates a flow path for ignition torch gas.
第４図は、別の実施例を示し、第２図示の実施
例を更に改良したものである。すなわち、第２図
に示した円形断面噴口から液柱状態で噴射される
液体酸素の微粒化及び燃料との混合を更に促進さ
せるために、噴口１２に円環状の側路１２′を設
け、ここから薄膜状態で液体酸素を噴射するよう
にしたものである。薄膜状態で噴射される液体酸
素の微粒化特性は、単位時間当たりの噴射流量に
対し、高速水素ガス流との接触面積が拡大する程
良好となる。モード１では、従燃料である水素の
高速流によつて主燃料であるケロシンをａの位置
で微粒化し、更にこの高速噴霧流はｂの位置で薄
膜状の液体酸素を効率よく微粒化し、両者の混合
を促進させるものである。モード２では、ケロシ
ンの噴射が止められ、ヘリウムガス等によつて残
留ケロシンをパージした後、水素の高速流と薄膜
状液体酸素噴流との相互作用によつて微粒化、混
合を行わせるものである。 FIG. 4 shows another embodiment, which is a further improvement on the embodiment shown in FIG. That is, in order to further promote the atomization of the liquid oxygen injected in the form of a liquid column from the circular cross-section nozzle shown in FIG. The device is designed to inject liquid oxygen in a thin film form. The atomization characteristics of liquid oxygen injected in a thin film state become better as the contact area with the high-speed hydrogen gas flow increases with respect to the injection flow rate per unit time. In mode 1, the main fuel, kerosene, is atomized at position a by a high-speed flow of hydrogen, which is the secondary fuel, and this high-speed spray flow efficiently atomizes the thin film of liquid oxygen at position b, so that both This promotes the mixing of In mode 2, the injection of kerosene is stopped, residual kerosene is purged with helium gas, etc., and then atomization and mixing are performed by the interaction between the high-speed flow of hydrogen and the thin film-like liquid oxygen jet. be.
第５図は、第１図に示した高温ガス発生器６と
燃焼器５の噴射器１の詳細を示すもので、モード
１において低温気体水素を直接噴射するものでは
なく、一旦、予燃焼室１６において、主推進薬で
ある液体酸素２から分岐した液体酸素２′と燃焼
室冷却後の低温気体水素４を燃焼させ、300〜800
℃の範囲の高温ガスを発生させて微粒化用作動ガ
ス流量の増大をはかる。 FIG. 5 shows details of the high-temperature gas generator 6 and the injector 1 of the combustor 5 shown in FIG. 1. In mode 1, low-temperature gaseous hydrogen is not directly injected; In step 16, liquid oxygen 2' branched from liquid oxygen 2, which is the main propellant, and low-temperature gaseous hydrogen 4 after cooling the combustion chamber are combusted.
The flow rate of the working gas for atomization is increased by generating high-temperature gas in the temperature range of ℃.
この場合、微粒化用高温ガスの発生は、次の２
通りによるものである。第１の方法は、従推進薬
である水素質量１に対し、分岐する液体酸素２′
の質量流量を0.3〜0.8の範囲に制御し、いわゆる
燃料過濃燃焼によつて300〜800℃の高温ガスを発
生させる方法である。第２の方法は、従推進薬で
ある水素質量流量１に対し、分岐する液体酸素
２′の質量流量を180〜90の範囲に制御し、いわゆ
る酸素過濃燃焼によつて300〜800℃の高温ガスを
発生させる方法である。第２の方法では第１の方
法に比して約100倍まで微粒化用高温ガス量の増
大が図れる。第１の方法で微粒化特性が満足でな
いことが見込まれる場合には、第２の方法による
ことが望ましい。主燃料噴口と微粒化用気体噴口
の構造は、第２図、第４図に示したものと同じで
ある。モード２では、上記の実施例と同じであ
る。 In this case, the generation of high-temperature gas for atomization is as follows:
It depends on the street. The first method uses 1 mass of hydrogen, which is a secondary propellant, and 2' branched liquid oxygen.
In this method, the mass flow rate of the fuel is controlled within the range of 0.3 to 0.8, and high-temperature gas of 300 to 800°C is generated through so-called rich fuel combustion. The second method is to control the mass flow rate of branched liquid oxygen 2' to a range of 180 to 90 with respect to the hydrogen mass flow rate 1, which is a secondary propellant, and to achieve a temperature of 300 to 800℃ by so-called oxygen-enriched combustion. This method generates high-temperature gas. In the second method, the amount of high-temperature gas for atomization can be increased by about 100 times compared to the first method. If it is expected that the atomization characteristics will not be satisfactory with the first method, it is desirable to use the second method. The structures of the main fuel nozzle and the atomizing gas nozzle are the same as those shown in FIGS. 2 and 4. In mode 2, it is the same as the above embodiment.
（発明の効果）
この発明のロケツト噴射器は、上記のように簡
単な構造でありながら、燃料と酸化剤の混合条件
を改善し、特に２種類の燃料に対する２種類のモ
ードで高性能かつ安定燃焼が達成可能となり、二
元燃料用ロケツトエンジンの噴射器として極めて
有効なものである。(Effects of the Invention) Although the rocket injector of this invention has a simple structure as described above, it improves the mixing conditions of fuel and oxidizer, and achieves high performance and stability especially in two types of modes for two types of fuel. This makes it possible to achieve combustion, making it extremely effective as an injector for dual-fuel rocket engines.
しかも、微粒化用気体は、燃焼器冷却後の低温
ガス状態の水素、又はターボポンプのタービン駆
動後の水素又は酸素濃度過濃な高温ガスで、二元
燃料ロケツトのサイクルを構成する上で必然的に
発生するものであり、そのためにロケツトの構成
が複雑となる訳ではないという、顕著な効果を奏
する。 Furthermore, the atomization gas is hydrogen in a low-temperature gas state after cooling the combustor, or hydrogen or high-temperature gas with an excessively high concentration of oxygen after driving the turbine of a turbo pump, which is necessary when configuring the cycle of a dual-fuel rocket. This has the remarkable effect that the structure of the rocket does not become complicated because of this.
第１図は二元燃料ロケツトエンジンの作動系統
概念図、第２図はこの発明のロケツト噴射器の１
実施例の噴口構造を示す断面図、第３図はその噴
口を用いた噴射器を示す断面及び正面図、第４図
は噴口構造の他の実施例を示す断面図、第５図は
高温ガス発生器の構造及び本発明噴射器の断面
図、第６図は従来の液体酸素、ケロシン燃料推進
薬の噴射器構造を示す断面図であり、図中の符号
はそれぞれ
１：噴射器、２：液体酸素、３：ケロシン、
４：液状水素、５：燃焼器、６：高温ガス発生
器、７：タービン、８：ポンプ、９：ロケツトノ
ズル、１０，１４：燃料噴口、１１，１２：液体
酸素噴口、１３：水素噴出口、１５：点火用トー
チガス出口、１６：予燃焼室を示す。
Figure 1 is a conceptual diagram of the operating system of a dual-fuel rocket engine, and Figure 2 is a diagram of a rocket injector of the present invention.
3 is a cross-sectional view and a front view showing an injector using the nozzle structure, FIG. 4 is a sectional view showing another example of the nozzle structure, and FIG. 5 is a high-temperature gas Figure 6 is a cross-sectional view showing the structure of a conventional injector for liquid oxygen and kerosene fuel propellants, and the symbols in the figure are 1: injector, 2: Liquid oxygen, 3: Kerosene,
4: Liquid hydrogen, 5: Combustor, 6: High temperature gas generator, 7: Turbine, 8: Pump, 9: Rocket nozzle, 10, 14: Fuel nozzle, 11, 12: Liquid oxygen nozzle, 13: Hydrogen nozzle , 15: ignition torch gas outlet, 16: pre-combustion chamber.
Claims (1)
進薬とするロケツトにおいて、気体状態で噴口か
ら噴出する従燃料の噴流中に液体主燃料を送入し
微粒化する燃料噴口、該燃料噴口と同軸型噴口と
して構成された液体酸素噴口とを有することを特
徴とするロケツト噴射器。 ２ 上記燃料の微粒化用ガスは、ロケツトノズル
及びロケツト燃焼室を冷却した燃料の気化ガスで
あることを特徴とする特許請求の範囲第１項記載
のロケツト噴射器。 ３ 上記燃料の微粒化用ガスは、高温ガス発生器
の燃焼ガスであることを特徴とする特許請求の範
囲第１項記載のロケツト噴射器。 ４ 上記燃料の微粒化用ガスは、高温ガス発生器
の燃料過濃燃焼ガスであることを特徴とする特許
請求の範囲第３項記載のロケツト噴射器。 ５ 上記燃料の微粒化用ガスは、高温ガス発生器
の酸素過濃燃焼ガスであることを特徴とする特許
請求の範囲第３項記載のロケツト噴射器。 ６ 物性値の異なる２種類の燃料と液体酸素を推
進薬とし、まず主として第１の燃料と液体酸素を
燃焼させ、ついで第２の燃料に切り替えて同一の
燃焼器で燃焼させる液体ロケツトエンジンの燃焼
器であつて、第１の燃料と液体酸素を燃焼させる
場合、気化した第２の燃料の噴流中に第１の燃料
を送入し、該噴流によつて上記第１の燃料を微粒
化し、液体酸素と混合燃焼させることを特徴とす
るロケツト噴射器。[Scope of Claims] 1. In a rocket using two types of fuel with different physical properties and liquid oxygen as propellants, a fuel in which liquid main fuel is atomized by feeding it into a jet of secondary fuel ejected from a nozzle in a gaseous state. A rocket injector, characterized in that it has a nozzle and a liquid oxygen nozzle configured as a coaxial nozzle with the fuel nozzle. 2. The rocket injector according to claim 1, wherein the fuel atomization gas is a vaporized fuel gas that has cooled the rocket nozzle and the rocket combustion chamber. 3. The rocket injector according to claim 1, wherein the fuel atomization gas is combustion gas from a high-temperature gas generator. 4. The rocket injector according to claim 3, wherein the fuel atomization gas is fuel-rich combustion gas from a high-temperature gas generator. 5. The rocket injector according to claim 3, wherein the fuel atomization gas is oxygen-enriched combustion gas from a high-temperature gas generator. 6 Combustion of a liquid rocket engine using two types of fuel with different physical properties and liquid oxygen as propellants, first burning mainly the first fuel and liquid oxygen, then switching to the second fuel and burning it in the same combustor. When burning the first fuel and liquid oxygen, the first fuel is fed into a jet of vaporized second fuel, and the jet atomizes the first fuel, A rocket injector characterized by mixed combustion with liquid oxygen.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62249617A JPH0192560A (en) | 1987-10-02 | 1987-10-02 | Rocket launcher |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP62249617A JPH0192560A (en) | 1987-10-02 | 1987-10-02 | Rocket launcher |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0192560A JPH0192560A (en) | 1989-04-11 |
| JPH0323745B2 true JPH0323745B2 (en) | 1991-03-29 |
Family
ID=17195693
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP62249617A Granted JPH0192560A (en) | 1987-10-02 | 1987-10-02 | Rocket launcher |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0192560A (en) |
Families Citing this family (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH0229357U (en) * | 1988-08-15 | 1990-02-26 | ||
| JP2882938B2 (en) * | 1992-06-05 | 1999-04-19 | 三菱重工業株式会社 | Rocket engine injector |
| US6082098A (en) * | 1998-04-29 | 2000-07-04 | United Technologies Corporation | Ignition system for rocket engines |
| KR20040009473A (en) * | 2002-07-23 | 2004-01-31 | 현대모비스 주식회사 | Coaxial shear injector |
| DE10353423B3 (en) * | 2003-11-15 | 2005-04-14 | Eads Space Transportation Gmbh | Injector |
| KR100674118B1 (en) * | 2006-07-07 | 2007-01-24 | (주)씨앤스페이스 | Methane Engines for Rocket Propulsion |
| US9528479B2 (en) | 2011-03-07 | 2016-12-27 | Snecma | Injector for mixing two propellants comprising at least one injection element with a tricoaxial structure |
| JP2016509550A (en) * | 2012-12-28 | 2016-03-31 | ゼネラル・エレクトリック・カンパニイ | Aircraft and embedded cryogenic fuel systems |
| JP6287034B2 (en) | 2013-10-11 | 2018-03-07 | 株式会社Ihi | Gas generator |
| US20230028449A1 (en) * | 2019-12-30 | 2023-01-26 | Shell Oil Company | Compositions and methods of producing rocket propellants with enhanced cryogenic cooling, thermal stability, and thrust efficiency performance |
-
1987
- 1987-10-02 JP JP62249617A patent/JPH0192560A/en active Granted
Also Published As
| Publication number | Publication date |
|---|---|
| JPH0192560A (en) | 1989-04-11 |
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