JPS6115264B2 - - Google Patents
Info
- Publication number
- JPS6115264B2 JPS6115264B2 JP55038494A JP3849480A JPS6115264B2 JP S6115264 B2 JPS6115264 B2 JP S6115264B2 JP 55038494 A JP55038494 A JP 55038494A JP 3849480 A JP3849480 A JP 3849480A JP S6115264 B2 JPS6115264 B2 JP S6115264B2
- Authority
- JP
- Japan
- Prior art keywords
- combustion chamber
- nozzle
- injector
- secondary combustion
- primary combustion
- 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
- 238000002485 combustion reaction Methods 0.000 claims description 36
- 239000000446 fuel Substances 0.000 claims description 4
- 238000007664 blowing Methods 0.000 claims 1
- 239000004449 solid propellant Substances 0.000 description 6
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 239000000919 ceramic Substances 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
Landscapes
- Other Surface Treatments For Metallic Materials (AREA)
- Testing Of Engines (AREA)
Description
【発明の詳細な説明】
この発明は一次燃焼室で燃料を一次燃焼させる
ことにより生じた可燃ガスを、二次燃焼室に噴射
器を通して噴射するとともに、デイフユーザーか
ら取り入れた外気と混合して二次燃焼させ飛翔す
るタイプのラムロケツトに関する。[Detailed Description of the Invention] This invention injects combustible gas produced by primary combustion of fuel in a primary combustion chamber into a secondary combustion chamber through an injector, and mixes it with outside air taken in from a differential user. This invention relates to a type of ram rocket that uses secondary combustion to fly.
従来のラムロケツトとしては例えば第１図に示
すようなものが知られている。すなわち、１は前
述したタイプのラムロケツトであり、このラムロ
ケツト１のチヤンバ２は隔壁３によつて一次燃焼
室４と二次燃焼室５とに区切られている。隔壁３
には二次燃焼室５内に突出するカツプ形状の噴射
器６が取り付けられ、この噴射器６には前記一
次、二次燃焼室４，５を連通する多数のノズル孔
７が形成されている。１０はイグナイタである。
そして、このようなラムロケツト１は一次燃焼室
４に装填された燃料リツチな固体推進薬８をその
一端面から燃焼させることにより発生した高温高
圧の可燃ガスを噴射口６ａを介して噴射器６のノ
ズル孔７から二次燃焼室５内に分散して噴射する
とともに、デイフユーザー９から取り入れた外気
と混合し燃焼させることにより推力を得るように
していた。ところで、このようなラムロケツトに
あつては、噴射器６のノズル孔７は比較的長時間
にわたつて高温の可燃ガス（通常腐食性をもつ）
を高速で通過させるので、これによる侵食を防止
するために噴射器６の材料としてはグラフアイ
ト、セラミツク等の耐侵食性のあるものを使用し
たいわけであるが、一方においてこれらの材料は
引張強度と耐衝撃性に劣るため、一次燃焼室４内
の高圧あるいは両燃焼室４，５におけるダイナミ
ツクな圧力変動に対して高い信頼性を保持させる
ことが難しく、ために従来は専ら金属を用いざる
を得ず、またノズル孔７は可燃ガスを二次燃焼室
５へ分散して噴出させる必要からその径が小さい
故、ここへ前記のような耐食性のある材料を有効
にコーテイグすることも難しかつたのである。し
たがつて、従来の金属で作られた噴射器６のノズ
ル孔７は激しく侵食されてその口径が徐々に大き
くなるので、殊に一次燃焼室４の燃焼雰囲気を変
化せしめて設定したガス発生量とその性状を安定
に持続し得ないという問題があつた。 As a conventional ram rocket, one shown in FIG. 1, for example, is known. That is, 1 is a ram rocket of the type described above, and a chamber 2 of this ram rocket 1 is divided by a partition 3 into a primary combustion chamber 4 and a secondary combustion chamber 5. Bulkhead 3
A cup-shaped injector 6 protruding into the secondary combustion chamber 5 is attached to the injector 6, and a large number of nozzle holes 7 are formed in the injector 6 to communicate the primary and secondary combustion chambers 4 and 5. . 10 is an igniter.
The ram rocket 1 as described above burns the fuel-rich solid propellant 8 loaded into the primary combustion chamber 4 from one end thereof, and sends high-temperature, high-pressure combustible gas to the injector 6 through the injection port 6a. Thrust is obtained by injecting the fuel in a distributed manner into the secondary combustion chamber 5 from the nozzle hole 7, and by mixing it with outside air taken in from the differential user 9 and combusting it. By the way, in such a ram rocket, the nozzle hole 7 of the injector 6 is exposed to high temperature combustible gas (usually corrosive) for a relatively long period of time.
In order to prevent the erosion caused by this, it is desirable to use a corrosion-resistant material such as graphite or ceramic for the injector 6, but on the other hand, these materials have low tensile strength. Because of their poor impact resistance, it is difficult to maintain high reliability against high pressure in the primary combustion chamber 4 or dynamic pressure fluctuations in both combustion chambers 4 and 5, and for this reason, conventionally only metal has been used. Moreover, since the diameter of the nozzle hole 7 is small because it is necessary to disperse and eject the combustible gas into the secondary combustion chamber 5, it is difficult to effectively coat the nozzle hole with the above-mentioned corrosion-resistant material. It is. Therefore, the nozzle hole 7 of the conventional injector 6 made of metal is severely eroded and its diameter gradually increases, so the combustion atmosphere in the primary combustion chamber 4 is changed to reduce the set gas generation amount. There was a problem that the properties could not be maintained stably.
この発明はこのような従来の問題点に着目して
なされたもので、噴射器と一次燃焼室との間にノ
ズルスロートを設置することにより、上述の問題
点を解決することを目的としている。 The present invention was made in view of these conventional problems, and aims to solve the above-mentioned problems by installing a nozzle throat between the injector and the primary combustion chamber.
以下、この発明を図面に基づいて説明する。第
２，３図はこの発明の一実施例を示す図である。
まず、構成を説明すると、第２，３図において、
１１はラムロケツトであり、このラムロケツト１
１は円筒状のモータチヤンバ１２の軸方向中間部
内面に形成されたノズル１３により一次燃焼室１
４と二次燃焼室１５とに分けられている。ノズル
１３はモータチヤンバ１２内面から内方に突出す
るよう形成され、その内端に滑らかな曲面で形成
されたモータチヤンバ１２と同軸の所定径の開口
部、すなわちノズルスロート１６を有している。
そして、ノズルスロート１６の面積は従来の噴射
器におけるノズル孔７の合計面積に相応するよう
に定められ後述するノズル孔２４の合計面積はノ
ズルスロート面積に等しいかあるいはそれ以上に
設定される。２１は前記ノズル１３の一次燃焼室
１４側に取り付けられたフイルターであり、この
フイルター２１には多数の孔２２が形成されてい
る。また、ノズル１３の二次燃焼室１５側にはカ
ツプ形状の噴射器２３が取り付けられており、こ
の噴射器２３には多数のノズル孔２４が形成され
ている。したがつて、前記ノズルスロート１６は
一次燃焼室１４と噴射器２３との間に設置されて
いることになる。 The present invention will be explained below based on the drawings. FIGS. 2 and 3 are diagrams showing an embodiment of the present invention.
First, to explain the configuration, in Figures 2 and 3,
11 is a ram rocket, and this ram rocket 1
1 is a primary combustion chamber 1 formed by a nozzle 13 formed on the inner surface of an axially intermediate portion of a cylindrical motor chamber 12.
4 and a secondary combustion chamber 15. The nozzle 13 is formed to protrude inward from the inner surface of the motor chamber 12, and has at its inner end an opening of a predetermined diameter coaxial with the motor chamber 12 formed with a smooth curved surface, that is, a nozzle throat 16.
The area of the nozzle throat 16 is determined to correspond to the total area of the nozzle holes 7 in a conventional injector, and the total area of the nozzle holes 24, which will be described later, is set to be equal to or larger than the nozzle throat area. 21 is a filter attached to the primary combustion chamber 14 side of the nozzle 13, and this filter 21 has a large number of holes 22 formed therein. Further, a cup-shaped injector 23 is attached to the secondary combustion chamber 15 side of the nozzle 13, and a large number of nozzle holes 24 are formed in this injector 23. Therefore, the nozzle throat 16 is installed between the primary combustion chamber 14 and the injector 23.
次に、作用を説明する。 Next, the effect will be explained.
まず、ラムロケツト１１は二次燃焼室１５に装
填されていた図示していない固体推進薬が燃焼さ
れることにより、ラム圧を得るに必要な速度まで
高められる。次いで、イグナイタ１９によつて固
体推進薬１８に着火される。この結果、固体推進
薬１８はその端面から比較的長時間にわたつて燃
焼し、一次燃焼室１４内に不完全燃焼の高温高圧
可燃ガスが発生する。次いで、この可燃ガスはフ
イルター２１を介してノズル１３のノズルスロー
ト１６を通り、噴射器２３から二次燃焼室１５内
に噴射され外気と混合して燃焼する。このとき、
二次燃焼室１５に噴射される可燃ガス量はノズル
スロート１６で決定され、ほぼ一定量が二次燃焼
室１５に噴射される。 First, the ram rocket 11 is increased to a speed necessary to obtain ram pressure by burning solid propellant (not shown) loaded in the secondary combustion chamber 15. Next, the solid propellant 18 is ignited by the igniter 19. As a result, the solid propellant 18 burns from its end face for a relatively long period of time, and incompletely burned high-temperature, high-pressure combustible gas is generated in the primary combustion chamber 14. Next, this combustible gas passes through the nozzle throat 16 of the nozzle 13 via the filter 21, is injected from the injector 23 into the secondary combustion chamber 15, mixes with outside air, and burns. At this time,
The amount of combustible gas injected into the secondary combustion chamber 15 is determined by the nozzle throat 16, and a substantially constant amount is injected into the secondary combustion chamber 15.
すなわち、本発明に係るノズルスロート１６は
その口径が従来のノズル孔７よりも格段に大きい
故、その形状を可燃ガスの流線に沿わせる如く現
想的に形成することが容易となり、これによつて
生じる境界層に保護されて従来一般のロケツトノ
ズルと同様に侵食を受けることが少く、かつ要す
ればこのノズルスロートにセラミツク等のコーテ
イングを有効に施こすことも可能となつて、更に
耐食性を高めることができる。またここがたとえ
侵食を受けたとしても従来の小径のノズル孔の場
合に比べ面積変化率が格段に小さいことになる。 That is, since the nozzle throat 16 according to the present invention has a much larger diameter than the conventional nozzle hole 7, it is easy to creatively form the shape so as to follow the flow line of the combustible gas. Protected by the resulting boundary layer, it is less susceptible to corrosion like conventional rocket nozzles, and if necessary, it is also possible to effectively coat the nozzle throat with ceramic or the like, further improving corrosion resistance. can be increased. Furthermore, even if this area is eroded, the area change rate will be much smaller than in the case of a conventional small-diameter nozzle hole.
したがつて本発明によつて設置したノズルスロ
ートは固体推進薬１８に関してノズル係数をほぼ
一定に維持するので、ノズル孔２４が従来同様に
侵食を受けても、一次燃焼室１４の燃焼雰囲気を
定常的に保持する結果、可燃ガス発生量とそのガ
ス性状を安定に持続させうるのである。 Therefore, the nozzle throat installed according to the present invention maintains the nozzle coefficient approximately constant with respect to the solid propellant 18, so that even if the nozzle hole 24 is eroded as in the conventional case, the combustion atmosphere in the primary combustion chamber 14 is kept constant. As a result, the amount of combustible gas generated and its gas properties can be maintained stably.
第１図は従来のラムロケツトを示す一部破断正
面図、第２図はこの発明に係るラムロケツトの一
実施例を示す一部破断正面図、第３図は第２図に
示したノズルスロート近傍の拡大断面図である。
１４……一次燃焼室、１５……二次燃焼室、１
１……ラムロケツト、１６……ノズルスロート、
１８……固体推進薬、２５……デイフユーザー、
２３……噴射器。
FIG. 1 is a partially cut-away front view showing a conventional ram rocket, FIG. 2 is a partially cut-away front view showing an embodiment of the ram rocket according to the present invention, and FIG. 3 is a front view showing a part near the nozzle throat shown in FIG. It is an enlarged sectional view. 14...Primary combustion chamber, 15...Secondary combustion chamber, 1
1... Ram rocket, 16... Nozzle throat,
18...Solid propellant, 25...Diff user,
23... Injector.
Claims (1)
り発生した可燃ガスを二次燃焼室に噴射器に設け
た多数のノズル孔を通して分散して噴射するとと
もに、デイフユーザーを介して二次燃焼室に外気
を吹き込んで二次燃焼させるラムロケツトにおい
て、前記噴射器と一次燃焼室との間にノズルスロ
ートを設置したことを特徴とするラムロケツト。1 The combustible gas generated by primary combustion of fuel in the primary combustion chamber is dispersed and injected into the secondary combustion chamber through a number of nozzle holes provided in the injector, and is also injected into the secondary combustion chamber via a differential user. A ram rocket for secondary combustion by blowing in outside air, characterized in that a nozzle throat is installed between the injector and the primary combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3849480A JPS56135735A (en) | 1980-03-25 | 1980-03-25 | Ram rocket |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP3849480A JPS56135735A (en) | 1980-03-25 | 1980-03-25 | Ram rocket |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS56135735A JPS56135735A (en) | 1981-10-23 |
| JPS6115264B2 true JPS6115264B2 (en) | 1986-04-23 |
Family
ID=12526812
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP3849480A Granted JPS56135735A (en) | 1980-03-25 | 1980-03-25 | Ram rocket |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS56135735A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01317962A (en) * | 1988-06-14 | 1989-12-22 | Fujitsu Ltd | Bellows medium formation device |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4091731A (en) * | 1976-07-06 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Fuel injection with flameholding |
| US4133173A (en) * | 1976-01-12 | 1979-01-09 | The United States Of America As Represented By The Secretary Of The Navy | Ducted rockets |
-
1980
- 1980-03-25 JP JP3849480A patent/JPS56135735A/en active Granted
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4133173A (en) * | 1976-01-12 | 1979-01-09 | The United States Of America As Represented By The Secretary Of The Navy | Ducted rockets |
| US4091731A (en) * | 1976-07-06 | 1978-05-30 | The United States Of America As Represented By The Secretary Of The Navy | Fuel injection with flameholding |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH01317962A (en) * | 1988-06-14 | 1989-12-22 | Fujitsu Ltd | Bellows medium formation device |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS56135735A (en) | 1981-10-23 |
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