JPH0979088A - Ram combustor - Google Patents
Ram combustorInfo
- Publication number
- JPH0979088A JPH0979088A JP23673795A JP23673795A JPH0979088A JP H0979088 A JPH0979088 A JP H0979088A JP 23673795 A JP23673795 A JP 23673795A JP 23673795 A JP23673795 A JP 23673795A JP H0979088 A JPH0979088 A JP H0979088A
- Authority
- JP
- Japan
- Prior art keywords
- fuel
- combustor
- swirler
- flame stabilizer
- type flame
- 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 160
- 239000003381 stabilizer Substances 0.000 claims abstract description 47
- 238000002485 combustion reaction Methods 0.000 claims abstract description 38
- 230000002093 peripheral effect Effects 0.000 claims abstract description 19
- 238000002347 injection Methods 0.000 claims abstract description 18
- 239000007924 injection Substances 0.000 claims abstract description 18
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 238000011144 upstream manufacturing Methods 0.000 description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000002411 adverse Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
Landscapes
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
(57)【要約】
【課題】 ラムジェットエンジンのラム燃焼器における
空気と燃料の混合を良くし、燃焼効率を向上させる。
【解決手段】 本発明のラム燃焼器は、燃焼器ダクトの
内部に配され供給された燃料の燃焼を行なう主燃焼器型
保炎器と、主燃焼器型保炎器の前端の中心位置に配され
下流に開口を有するとともに第１の燃料ノズルから燃料
が供給される副燃焼室と、副燃焼室と主燃焼器型保炎器
の周壁との間に円周方向に間隔を空けて配される複数の
旋回羽根を有し気流に旋回流を生じさせるスワーラと、
スワーラの内部に燃料を供給する第２の燃料ノズルとを
具備してなり、第２の燃料ノズルはスワーラ外周に配さ
れる円環状の燃料ヘッダと、旋回羽根の高さ方向に延び
て形成されていて、燃料ヘッダと連通する燃料供給通路
と、旋回羽根の高さ方向に間隔を空けて複数配置されて
いて、上記燃料供給通路と連通する燃料噴出孔とからな
る。
(57) Abstract: To improve the mixing efficiency of air and fuel in a ram combustor of a ramjet engine to improve combustion efficiency. A ram combustor according to the present invention has a main combustor type flame stabilizer disposed inside a combustor duct for combustion of a supplied fuel, and a central position of a front end of the main combustor type flame stabilizer. A secondary combustion chamber, which is arranged and has an opening downstream and to which fuel is supplied from the first fuel nozzle, and is circumferentially spaced between the secondary combustion chamber and the peripheral wall of the main combustor flame stabilizer. A swirler having a plurality of swirl vanes that generate swirl flow in the air flow,
A second fuel nozzle for supplying fuel to the inside of the swirler is provided. The second fuel nozzle is formed by an annular fuel header arranged on the outer circumference of the swirler and extending in the height direction of the swirl vanes. The fuel supply passage communicates with the fuel header, and a plurality of fuel injection holes are provided at intervals in the height direction of the swirl vanes and communicate with the fuel supply passage.
Description
【０００１】[0001]
【発明の属する技術分野】本発明はラム燃焼器に係り、
特に、ラムジェットエンジンを広い飛行マッハ数範囲に
おいて高い燃焼効率で作動させる技術に関するものであ
る。TECHNICAL FIELD The present invention relates to a ram combustor,
In particular, the present invention relates to a technique for operating a ramjet engine with high combustion efficiency in a wide flight Mach number range.
【０００２】[0002]
【従来の技術】ラムジェットエンジンは、ガスタービン
エンジンのような空気圧縮機を有していないものの、燃
焼器ダクト内に高速で流入する空気をラム圧を利用して
圧縮するようにしており、構造が単純であり、かつ、機
体の航行速度が大きくなるほど燃焼効率を向上させるこ
とができると考えられ、例えばマッハ数２．５〜５の航
行速度の超音速航空機や宇宙往還機への適用が研究され
ている。2. Description of the Related Art Although a ramjet engine does not have an air compressor like a gas turbine engine, it is designed to compress the air flowing into a combustor duct at high speed by using ram pressure. It is thought that combustion efficiency can be improved as the structure is simple and the navigation speed of the airframe becomes higher. For example, it is applicable to supersonic aircraft and space vehicles with navigation speeds of Mach number 2.5 to 5. Being researched.
【０００３】図５は、ラムジェットエンジンの概略構造
を示すもので、符号１はデイフューザ、２は燃焼器ダク
ト、３は燃焼室、４はジェットノズル、５は燃焼器（ラ
ム燃焼器）である。そして、燃焼器５としては、図６及
び図７に示すものが提案されている。FIG. 5 shows a schematic structure of a ramjet engine. Reference numeral 1 is a diffuser, 2 is a combustor duct, 3 is a combustion chamber, 4 is a jet nozzle, and 5 is a combustor (ram combustor). . As the combustor 5, those shown in FIGS. 6 and 7 have been proposed.
【０００４】図６例の燃焼器５は、円筒状の燃焼器ダク
ト２の内部に、燃料ノズル６を複数配置するとともに、
各燃料ノズル６の下流位置に環状のフレームホルダ（保
炎器）７を配し、該フレームホルダ７の近傍に点火栓８
を配した構成で、燃料ノズル６及びフレームホルダ７
は、燃焼器ダクト２の内面に周方向に間隔を空けて配し
た複数の片持ち梁状の支持梁９によって支持されてい
る。The combustor 5 shown in FIG. 6 has a plurality of fuel nozzles 6 arranged inside a cylindrical combustor duct 2.
An annular frame holder (flame stabilizer) 7 is arranged at a position downstream of each fuel nozzle 6, and a spark plug 8 is provided in the vicinity of the frame holder 7.
Fuel nozzle 6 and frame holder 7
Are supported on the inner surface of the combustor duct 2 by a plurality of cantilever-shaped support beams 9 arranged at intervals in the circumferential direction.
【０００５】そして、燃料ノズル６の複数の噴出孔６ａ
から、矢印で示す気流Ｇに燃料を噴射して混合流とし、
点火栓８で混合流に点火するとともに、フレームホルダ
７のＶ字状断面によりその後流に乱れの多い低流速域を
発生させて、燃焼状態を保持する保炎を行うようにして
いる。A plurality of ejection holes 6a of the fuel nozzle 6
From, the fuel is injected into the air flow G indicated by the arrow to form a mixed flow,
The spark plug 8 is used to ignite the mixed flow, and the V-shaped cross section of the frame holder 7 causes a low flow velocity region with a large amount of turbulence in the subsequent flow to perform flame holding for maintaining a combustion state.
【０００６】この図６例の燃焼器５では、高マッハ時の
ように適正なラム圧による空気の圧縮が行われると、空
気と燃料との混合流がフレームホルダ７の後方で低速域
となることに基づいて、燃焼状態の維持に加えて、空気
と燃料との混合攪拌が促進されて高い燃焼効率を得るこ
とができる。In the combustor 5 shown in FIG. 6, when air is compressed by an appropriate ram pressure as in high mach, the mixed flow of air and fuel becomes a low speed region behind the frame holder 7. Based on this, in addition to maintaining the combustion state, the mixing and stirring of air and fuel is promoted, and high combustion efficiency can be obtained.
【０００７】一方、図７例の燃焼器５は、円筒状の燃焼
器ダクト２の燃焼室３に、中空半球状の主燃焼器型保炎
器１０を配するとともに、主燃焼器型保炎器１０の下流
側外周に、ガッタ型保炎器１１を周方向に間隔を空けて
配し、主燃焼器型保炎器１０に燃料ノズル１２を接続し
た構成で、主燃焼器型保炎器１０及びガッタ型保炎器１
１の部分は、複数の片持ち梁状の支持梁９によって支持
されている。On the other hand, in the combustor 5 of the example in FIG. 7, a hollow hemispherical main combustor type flame stabilizer 10 is arranged in a combustion chamber 3 of a cylindrical combustor duct 2, and a main combustor type flame stabilizer is provided. The main combustor type flame stabilizer is configured so that the gutta type flame stabilizers 11 are circumferentially spaced on the downstream side outer periphery of the chamber 10 and the fuel nozzle 12 is connected to the main combustor type flame stabilizer 10. 10 and Gutta type flame stabilizer 1
The first portion is supported by a plurality of cantilever-shaped support beams 9.
【０００８】そして、燃料供給系１３の作動時に燃料ノ
ズル１２から燃料を噴射して、点火栓８で点火するとと
もに、主燃焼器型保炎器１０の形状に基づいて保炎を行
ないながら、ガッタ型保炎器１１のＶ字状断面により乱
れの多い低流速域を発生させて、燃焼炎と空気との混合
による完全燃焼を図るようにしている。尚、１０ａは空
気導入孔で、主燃焼器型保炎器１０内に気流の一部を導
入する。While the fuel supply system 13 is operating, fuel is injected from the fuel nozzle 12 to be ignited by the spark plug 8 and, while maintaining flame holding based on the shape of the main combustor type flame stabilizer 10, The V-shaped cross section of the flame stabilizer 11 generates a low flow velocity region with a large amount of turbulence to achieve complete combustion by mixing the combustion flame and air. Incidentally, 10a is an air introduction hole for introducing a part of the airflow into the main combustor type flame stabilizer 10.
【０００９】しかし、燃焼器５が図６例の構造である場
合には、マッハ数が小さい低超音速航行状態や亜音速航
行状態で、ラム圧を利用して燃焼器ダクト２の内部の気
流を十分に圧縮することができず、かつ空気温度の上昇
が不十分なものとなるため、燃焼効率が低下することや
燃料の着火性に悪影響を及ぼすことが起こり易くなる。However, in the case where the combustor 5 has the structure shown in FIG. 6, in the low supersonic navigation state or the subsonic navigation state in which the Mach number is small, the air flow inside the combustor duct 2 is utilized by using the ram pressure. Cannot be sufficiently compressed, and the rise in the air temperature becomes insufficient, so that the combustion efficiency is lowered and the ignitability of the fuel is adversely affected.
【００１０】また、燃焼器５が図７例の構造である場合
には、マッハ数が大きい超音速航行状態で、燃料ノズル
１２からの燃料供給量の増加に、主燃焼器型保炎器１０
の内部に空気導入孔１０ａから導入する空気量の増加が
追従できなくなり、主燃焼器型保炎器１０の内部が燃料
過濃な状態となって、火炎の吹き消え現象が生じて燃焼
効率が低下してしまうことが考えられる。Further, in the case where the combustor 5 has the structure shown in FIG. 7, the main combustor type flame stabilizer 10 increases in the fuel supply amount from the fuel nozzle 12 in the supersonic navigation state in which the Mach number is large.
The increase in the amount of air introduced from the air introduction hole 10a into the interior of the main combustion chamber cannot be followed, the inside of the main combustor type flame stabilizer 10 becomes fuel rich, and the flame blow-out phenomenon occurs to increase the combustion efficiency. It is possible that it will decrease.
【００１１】本願の発明者らはかかる問題を解決すべく
鋭意研究を行いその成果を特許出願した（特願平６─１
７４６２９号（未公開））。図４は上記出願に開示され
たラム燃焼器の正断面図である。The inventors of the present application have earnestly studied to solve such a problem, and applied for a patent for the result (Japanese Patent Application No. 6-1).
74629 (unpublished). FIG. 4 is a front sectional view of the ram combustor disclosed in the above application.
【００１２】図４において、符号２０はラム燃焼器、２
１は第１の燃料ノズル、２２は副燃焼室、２３はスワー
ラ、２４は第２の燃料ノズル、２５は予混合室、２６は
燃料制御手段、２７は燃料制御部、２８は点火用燃料供
給手段、２９は主燃焼用燃料供給手段である。In FIG. 4, reference numeral 20 is a ram combustor, 2
1 is a first fuel nozzle, 22 is a secondary combustion chamber, 23 is a swirler, 24 is a second fuel nozzle, 25 is a premixing chamber, 26 is a fuel control means, 27 is a fuel control unit, 28 is a fuel supply for ignition. Means 29 is a main combustion fuel supply means.
【００１３】前記ラム燃焼器２０にあっては、燃焼器ダ
クト２の内壁に支持梁９によって支持された状態に例え
ば燃焼器ダクト２の周方向に間隔を空けて複数配される
主燃焼器型保炎器１０と、該主燃焼器型保炎器１０の下
流開口部の近傍位置に周方向に間隔を空けて複数配され
るガッタ型保炎器１１と、主燃焼器型保炎器１０の前端
（上流壁）に配され中心位置に燃料を供給する第１の燃
料ノズル２１と、主燃焼器型保炎器１０の前端の中心位
置に配され下流に開口を有するとともに第１の燃料ノズ
ル２１から燃料が供給される副燃焼室２２と、該副燃焼
室２２と主燃焼器型保炎器１０の上流端部近傍の周壁１
０ｂとの間に配され気流Ｇの一部を主燃焼器型保炎器１
０の内部に取り入れ旋回流を生じさせるスワーラ２３
と、該スワーラ２３の回りに配されスワーラ２３の内部
に燃料を供給する第２の燃料ノズル２４と、主燃焼器型
保炎器１０の周壁１０ｂと副燃焼室２２の周壁２２ａと
の間に形成される予混合室２５と、第１の燃料ノズル２
１及び第２の燃料ノズル２４に接続される燃料制御手段
２６とを具備している。In the ram combustor 20, a plurality of main combustor types are arranged in a state of being supported by the support beams 9 on the inner wall of the combustor duct 2, for example, with a plurality of intervals being provided in the circumferential direction of the combustor duct 2. A flame stabilizer 10, a plurality of gutter type flame stabilizers 11 arranged circumferentially at a position near the downstream opening of the main combustor type flame stabilizer 10, and a main combustor type flame stabilizer 10 The first fuel nozzle 21 arranged at the front end (upstream wall) of the main fuel and supplying fuel to the central position, and the first fuel nozzle 21 arranged at the central position of the front end of the main combustor type flame stabilizer 10 and having an opening at the downstream side. The auxiliary combustion chamber 22 to which fuel is supplied from the nozzle 21, and the peripheral wall 1 near the upstream end of the auxiliary combustion chamber 22 and the main combustor type flame stabilizer 10.
0b and a part of the air flow G to the main combustor type flame stabilizer 1
A swirler 23 that takes in a swirl flow inside 0
Between the second fuel nozzle 24 arranged around the swirler 23 and supplying fuel into the swirler 23, and the peripheral wall 10b of the main combustor type flame stabilizer 10 and the peripheral wall 22a of the auxiliary combustion chamber 22. The formed premixing chamber 25 and the first fuel nozzle 2
Fuel control means 26 connected to the first and second fuel nozzles 24.
【００１４】また、前記燃焼器型保炎器１０には、ガッ
タ型保炎器１１よりも若干上流にずれた位置に、例えば
円環状をなすガイド部１０ｃが、周壁１０ｂに対して一
体に、かつ半径外方向に突出した状態に配され、該ガイ
ド部１０ｃの内方位置に、周壁１０ｂを貫通した状態の
気流導入口１０ｄが複数配される。そして、主燃焼器型
保炎器１０の内部には、点火栓８が配される。Further, in the combustor type flame stabilizer 10, a guide part 10c having, for example, an annular shape is integrally formed with the peripheral wall 10b at a position slightly upstream of the gutta type flame stabilizer 11. In addition, a plurality of airflow inlets 10d are arranged so as to project radially outward and penetrate the peripheral wall 10b at inner positions of the guide portion 10c. The spark plug 8 is arranged inside the main combustor type flame stabilizer 10.
【００１５】前記副燃焼室２２にあっては、円筒状に形
成されるとともに、主燃焼器型保炎器１０の前端に、上
流が閉塞された状態でかつ下流が開口された状態に取り
付けられ、内部に第１の燃料ノズル２１の先端が挿入状
態に配される。そして、副燃焼室２２の内部には、点火
栓８が配され、副燃焼室２２の周壁２２ａの下流縁部
は、スワーラ２３よりも下流まで突出した状態に設定さ
れる。The auxiliary combustion chamber 22 is formed in a cylindrical shape, and is attached to the front end of the main combustor type flame stabilizer 10 in a state in which the upstream side is closed and the downstream side is opened. , The tip of the first fuel nozzle 21 is placed inside. Then, the spark plug 8 is arranged inside the auxiliary combustion chamber 22, and the downstream edge of the peripheral wall 22 a of the auxiliary combustion chamber 22 is set so as to project further downstream than the swirler 23.
【００１６】前記第２の燃料ノズル２４は、主燃焼用燃
料供給手段２９からの燃料を主燃焼器型保炎器１０に供
給するための燃料供給管２４ａと、該燃料供給管２４ａ
に接続されスワーラ２３の回りの周壁１０ｂに配され燃
料を周方向に導く円環状の燃料ヘッダ２４ｂと、該燃料
ヘッダ２４ｂと後に述べるスワーラ２３の各旋回羽根２
３ａの間とを複数箇所で接続し燃料を並列的に吹き込む
ための燃料噴出孔２４ｃとを有している。The second fuel nozzle 24 has a fuel supply pipe 24a for supplying the fuel from the main combustion fuel supply means 29 to the main combustor type flame stabilizer 10, and the fuel supply pipe 24a.
Connected to the peripheral wall 10b around the swirler 23, which guides the fuel in the circumferential direction, and an annular fuel header 24b, and the swirler vanes 2 of the swirler 23 described later and the fuel header 24b.
3a is connected at a plurality of points, and a fuel injection hole 24c for injecting fuel in parallel is provided.
【００１７】前記予混合室２５は、スワーラ２３の下流
に位置した状態に、かつ主燃焼器型保炎器１０の周壁１
０ｂと副燃焼室２２の周壁２２ａとで囲まれた状態に配
される。The premixing chamber 25 is located downstream of the swirler 23, and the peripheral wall 1 of the main combustor type flame stabilizer 10 is arranged.
0b and the peripheral wall 22a of the auxiliary combustion chamber 22 are arranged.
【００１８】図８はスワーラ２３近傍の横断面図であ
る。図８に示すようにスワーラ２３は副燃焼室２２の周
壁２２ａと主燃焼器型保炎器１０の上流端部近傍の周壁
１０ｂとの間に前後方向に貫通する通路２３ｂを形成す
るように円周方向に間隔を空けて配され放射方向に延び
る複数の旋回羽根２３ａを有している。旋回羽根２３ａ
は主燃焼器型保炎器１０の軸芯に対して傾斜していてス
ワーラ２３内を流れる気流に旋回流を生じさせる。FIG. 8 is a cross-sectional view of the vicinity of the swirler 23. As shown in FIG. 8, the swirler 23 forms a circular passage 23b between the peripheral wall 22a of the auxiliary combustion chamber 22 and the peripheral wall 10b near the upstream end of the main combustor type flame stabilizer 10 so as to penetrate in the front-rear direction. It has a plurality of swirl vanes 23a arranged at intervals in the circumferential direction and extending in the radial direction. Swirl vane 23a
Is inclined with respect to the axis of the main combustor type flame stabilizer 10 and produces a swirling flow in the air flow flowing in the swirler 23.
【００１９】前記燃料制御手段２６にあっては、点火時
または飛行マッハ数の維持に必要とする燃料供給量を算
出するとともに、第１の燃料ノズル２１及び第２の燃料
ノズル２４への燃料配分比を点火モード及び飛行モード
のマッハ数に応じて設定するための燃料制御部２７と、
第１の燃料ノズル２１及び第２の燃料ノズル２４との間
に介在状態に配され燃料制御部２７の指令により燃料配
分比に応じた燃料供給を行なう点火用燃料供給手段２８
及び主燃焼用燃料供給手段２９とを有している。In the fuel control means 26, the fuel supply amount required for ignition or for maintaining the flight Mach number is calculated, and the fuel is distributed to the first fuel nozzle 21 and the second fuel nozzle 24. A fuel control unit 27 for setting the ratio according to the Mach number in the ignition mode and the flight mode,
Ignition fuel supply means 28 arranged in an intervening state between the first fuel nozzle 21 and the second fuel nozzle 24 and supplying fuel according to a fuel distribution ratio in accordance with a command from the fuel control unit 27.
And a main combustion fuel supply means 29.
【００２０】このように構成されているラム燃焼器２０
において、点火モードの選択がなされている場合には、
第１の燃料ノズル２１のみに燃料を供給して燃焼させる
ことが行なわれる。The ram combustor 20 having the above structure
In, if the ignition mode is selected,
Fuel is supplied and burned only to the first fuel nozzle 21.
【００２１】飛行モードの選択がなされると、第１の燃
料ノズル２１への燃料供給に、第２の燃料ノズル２４へ
の燃料供給を付加した状態で、燃焼させることが行なわ
れる。When the flight mode is selected, the fuel is supplied to the first fuel nozzle 21 and the fuel is supplied to the second fuel nozzle 24, and the fuel is burned.
【００２２】スワーラ２３を経由して主燃焼器型保炎器
１０の内部に取り入れられる空気は、図４に示すよう
に、気流Ｇの一部を取り込むことになるため、スワーラ
２３の下流には、鎖線の矢印で示すように旋回渦Ａが生
じ、第１の燃料ノズル２１及び第２の燃料ノズル２４か
らの燃料を巻き込んだ状態として、燃料と空気との混合
を促進させる。The air taken into the main combustor type flame stabilizer 10 via the swirler 23 takes in a part of the air flow G as shown in FIG. , A swirling vortex A is generated as indicated by a chain line arrow, and the fuel from the first fuel nozzle 21 and the second fuel nozzle 24 is entrained to promote the mixing of the fuel and the air.
【００２３】また、主燃焼器型保炎器１０に供給される
燃料は、第１の燃料ノズル２１及び第２の燃料ノズル２
４を経由して行なわれるから、第１の燃料ノズル２１に
よる主燃焼器型保炎器１０の中心部への燃料供給に、ス
ワーラ２３を経由した旋回流状態の燃料供給が付加され
る。したがって、スワーラ２３を経由した燃料は、旋回
渦Ａの中心に生じる破線で示す渦Ｂにより、主燃焼器型
保炎器１０の中心部に送り込まれて混合促進が図られ
る。The fuel supplied to the main combustor type flame stabilizer 10 is the first fuel nozzle 21 and the second fuel nozzle 2.
4, the fuel is supplied to the central portion of the main combustor type flame stabilizer 10 by the first fuel nozzle 21, and the fuel is supplied in a swirling flow state via the swirler 23. Therefore, the fuel that has passed through the swirler 23 is sent to the central portion of the main combustor type flame stabilizer 10 by the vortex B shown by the broken line generated in the center of the swirling vortex A, and mixing is promoted.
【００２４】さらにガッタ型保炎器１１により燃料と空
気の混合が図られ燃焼炎Ｆとなる。Further, the fuel and air are mixed by the gutta type flame stabilizer 11 to form the combustion flame F.
【００２５】[0025]
【発明が解決しようとする課題】以上述べた第２の燃料
ノズル２４にあってはメタンガスなどの燃料はスワーラ
２３の回りの外周壁１０ｃに穿設された燃料噴出孔２４
ｃから旋回羽根２３ａの間の空気通路２３ｂに向って噴
出するが、スワーラにおける空気と燃料の半径方向の混
合が十分行なわれないおそれがある。特に燃料の噴射量
の少ない場合には噴出の流速が小さいので、スワーラ２
３の外周近くでは燃料濃度が高く内周側では燃料濃度が
低い状態となるおそれがある。In the above-described second fuel nozzle 24, fuel such as methane gas is injected into the outer peripheral wall 10c around the swirler 23 through the fuel injection hole 24.
Although it is jetted from c toward the air passage 23b between the swirl vanes 23a, there is a possibility that the air and the fuel in the swirler are not sufficiently mixed in the radial direction. Especially when the fuel injection amount is small, the flow velocity of the jet is small, so swirler 2
There is a possibility that the fuel concentration is high near the outer circumference of No. 3 and is low on the inner circumference side.
【００２６】本発明はこのような問題点に鑑みてなされ
たもので、スワーラ内で空気と燃料が均一に混合するよ
うな第２の燃料ノズルを提供することを目的とするもの
である。The present invention has been made in view of the above problems, and an object of the present invention is to provide a second fuel nozzle in which air and fuel are uniformly mixed in a swirler.
【００２７】[0027]
【課題を解決するための手段】上記目的を達成するた
め、本発明のラム燃焼器は、ラムジェットエンジンの燃
焼器ダクトの内部に搭載されるラム燃焼器であって、燃
焼器ダクトの内部に配され供給された燃料の燃焼を行な
う主燃焼器型保炎器と、該主燃焼器型保炎器の前端の中
心位置に配され下流に開口を有するとともに第１の燃料
ノズルから燃料が供給される副燃焼室と、該副燃焼室と
主燃焼器型保炎器の周壁との間に前後方向に貫通する通
路を形成するように円周方向に間隔を空けて配され、放
射方向に延びる複数の旋回羽根を有し気流の一部を主燃
焼器型保炎器の内部に取り入れ旋回流を生じさせるスワ
ーラと、該スワーラの内部に燃料を供給する第２の燃料
ノズルとを具備してなり、該第２の燃料ノズルは上記ス
ワーラ外周に配される円環状の燃料ヘッダと、上記旋回
羽根の高さ方向に延びて形成されていて、該燃料ヘッダ
と連通する燃料供給通路と、上記旋回羽根の高さ方向に
間隔を空けて複数配置されていて、上記燃料供給通路と
連通する燃料噴出孔とからなることを特徴とするもので
ある。In order to achieve the above object, a ram combustor according to the present invention is a ram combustor mounted inside a combustor duct of a ramjet engine, and is provided inside the combustor duct. A main combustor type flame stabilizer which is arranged and burns the supplied fuel, and which has an opening arranged at the central position of the front end of the main combustor type flame stabilizer and which has a downstream opening and is supplied with fuel from a first fuel nozzle. And the auxiliary combustion chamber and the circumferential wall of the main combustor type flame stabilizer between the auxiliary combustion chamber and the peripheral wall of the main combustor type flame stabilizer, so as to form a passage that penetrates in the front-rear direction. A swirler having a plurality of extending swirl vanes for introducing a part of the air flow into the main combustor type flame stabilizer to generate a swirl flow; and a second fuel nozzle for supplying fuel into the swirler. And the second fuel nozzle is located around the swirler. A fuel header having an annular shape, a fuel supply passage formed to extend in the height direction of the swirl vane, communicating with the fuel header, and a plurality of fuel supply passages arranged at intervals in the height direction of the swirl vane. And a fuel injection hole communicating with the fuel supply passage.
【００２８】上記燃料噴出孔は上記旋回羽根の側面に開
口しており、燃料を上記スワーラ内を流れる気流に交叉
する方向に噴出するようにしてもよい。The fuel injection hole may be opened on the side surface of the swirl vane, and the fuel may be injected in a direction intersecting with the air flow flowing in the swirler.
【００２９】また上記燃料噴出孔は、上記旋回羽根の後
縁に開口しており、燃料を上記スワーラを出た気流と同
じ方向に噴出するようにしてもよい。Further, the fuel injection hole may be opened at the trailing edge of the swirl vane, and the fuel may be injected in the same direction as the air flow exiting the swirler.
【００３０】燃料噴出孔がスワーラの旋回羽根の高さ方
向、即ちスワーラの半径方向に間隔を空けて複数配列さ
れているのでスワーラにおいて半径方向にも十分な空気
と燃料の混合が行われる。燃料噴出孔は旋回羽根の側面
に設けても後縁に設けてもよいが、側面に設けた場合に
は空気流の方向に対し燃料が交叉する方向に流れて、ス
ワーラ内で空気と燃料の混合が行なわれるので、旋回羽
根の後縁に燃料噴出孔を設ける場合よりも混合がよく行
なわれると考えられる。Since the plurality of fuel injection holes are arranged at intervals in the height direction of the swirl vanes of the swirler, that is, in the radial direction of the swirler, the air and fuel are sufficiently mixed in the radial direction in the swirler. The fuel injection holes may be provided on the side surface or the trailing edge of the swirl blade, but when they are provided on the side surface, the fuel flows in a direction intersecting with the direction of the air flow, and the air and the fuel are separated in the swirler. Since the mixing is performed, it is considered that the mixing is performed more frequently than in the case where the fuel injection hole is provided at the trailing edge of the swirling blade.
【００３１】[0031]
【発明の実施の形態】以下、本発明のラム燃料器につい
て図面を参照しつつ説明する。尚、本発明は図４で説明
した従来（未公開）のラム燃焼器の第２の燃料ノズル
（主燃焼用燃料を供給するノズル）の改良に関するもの
であり、その他の部分については図４のラム燃焼器と同
じなので説明を省略する。BEST MODE FOR CARRYING OUT THE INVENTION A ram fuel device according to the present invention will be described below with reference to the drawings. The present invention relates to the improvement of the second fuel nozzle (nozzle for supplying the fuel for main combustion) of the conventional (unpublished) ram combustor described with reference to FIG. 4, and the other parts of FIG. The description is omitted because it is the same as the ram combustor.
【００３２】図１はラム燃焼器のスワーラ２３部分の横
断面図である。図２はスワーラ２３の旋回羽根２３ａの
斜視図である。スワーラ２３は図に示すように、副燃焼
室２２の周壁２２ａの外面と主燃焼器型保炎器１０の上
流端近傍の周壁１０ｂ内面との間を形成される円環状の
空間に円周方向に間隔を空けて配され、放射方向に延び
る複数の旋回羽根２３ａが設けられていて旋回羽根２３
ａの間に前後方向に貫通する空気通路２３ｂが形成され
ている。旋回羽根２３ａは図２に示すようにひねれてお
り、スワーラ２３内を流れる空気流に旋回を与える。FIG. 1 is a cross-sectional view of the swirler 23 portion of the ram combustor. FIG. 2 is a perspective view of the swirl vane 23 a of the swirler 23. As shown in the drawing, the swirler 23 is circumferentially arranged in an annular space formed between the outer surface of the peripheral wall 22a of the auxiliary combustion chamber 22 and the inner surface of the peripheral wall 10b near the upstream end of the main combustor type flame stabilizer 10. A plurality of swirl vanes 23a are provided at a distance from each other and extend in the radial direction.
An air passage 23b penetrating in the front-rear direction is formed between a. The swirl vane 23a is twisted as shown in FIG. 2, and swirls the air flow flowing in the swirler 23.
【００３３】第２の燃料ノズル３０は、燃料を主燃焼器
型保炎器１０に供給するための燃料供給管３０ａと、該
燃料供給管３０ａに接続され、スワーラ２３の回りの周
壁１０ｂを囲繞して配され燃料を周方向に導く円環状の
燃料ヘッダ３０ｂと、旋回羽根２３ａの高さ方向に延び
て形成されていて上記燃料ヘッダ３０ｂに周壁１０ｂに
穿設された孔３０ｅを介して連通する燃料通路３０ｃ
と、旋回羽根２３ａの側面２３ｃに開口していて、旋回
羽根２３ａの高さ方向に間隔を空けて複数配置されてお
り、上記燃料通路３０ｃと通過する燃料噴出孔３０ｄと
を有している。The second fuel nozzle 30 is connected to the fuel supply pipe 30a for supplying fuel to the main combustor type flame stabilizer 10 and the fuel supply pipe 30a, and surrounds the peripheral wall 10b around the swirler 23. And an annular fuel header 30b arranged in the circumferential direction to guide the fuel in the circumferential direction, and communicates with the fuel header 30b through a hole 30e formed in the circumferential wall 10b and extending in the height direction of the swirl vane 23a. Fuel passage 30c
And a plurality of them are opened at the side surface 23c of the swirl vane 23a, are arranged at intervals in the height direction of the swirl vane 23a, and have the fuel passage 30c and the fuel ejection hole 30d passing therethrough.
【００３４】次に本実施形態の作用を説明する。図２に
示すように燃料噴出孔３０ｄは旋回羽根２３ａの側面２
３ｃに開口しており、旋回羽根２３ａの高さ方向に間隔
を空けて複数配置されているので、スワーラ２３の半径
方向に均一に燃料（メタンガス等）が噴出する。燃料の
噴出方向はスワーラ２３内を流れる空気流Ｇに対して直
交する方向である。スワーラ２３の旋回羽根２３ａの間
の間隔は旋回羽根２３ａの高さよりも狭いこともあり、
スワーラ２３内で半径方向にも円周方向にも空気と燃料
の混合が均一に行なわれる。Next, the operation of the present embodiment will be described. As shown in FIG. 2, the fuel injection hole 30d is formed on the side surface 2 of the swirl vane 23a.
Since it is opened in 3c and a plurality of swirl vanes 23a are arranged at intervals in the height direction, fuel (methane gas or the like) is uniformly ejected in the radial direction of the swirler 23. The jet direction of fuel is a direction orthogonal to the air flow G flowing in the swirler 23. The interval between the swirl vanes 23a of the swirler 23 may be narrower than the height of the swirl vanes 23a,
In the swirler 23, the air and the fuel are uniformly mixed both in the radial direction and in the circumferential direction.
【００３５】尚、図２では燃料噴出孔３０ｄは旋回羽根
２３ａの片側の面にのみ穿設されているように画かれて
いるが、両面に穿設してもよい。In FIG. 2, the fuel injection holes 30d are drawn so as to be formed only on one surface of the swirl vane 23a, but they may be formed on both surfaces.
【００３６】次に本発明の他の実施形態について説明す
る。図３は本発明の他の実施形態を示す、スワーラ２３
の旋回羽根２３ａの斜視図である。この場合には燃料噴
出孔３０ｆは旋回羽根２３ａの後縁２３ｄに開口してい
て、旋回羽根２３ａの高さ方向に間隔を空けて複数配置
されている。燃料は空気流Ｇと同一方向に噴出する。Next, another embodiment of the present invention will be described. FIG. 3 shows another embodiment of the present invention, a swirler 23.
It is a perspective view of the turning blade 23a. In this case, the fuel ejection holes 30f are opened at the trailing edge 23d of the swirl vane 23a, and a plurality of fuel spout holes 30f are arranged at intervals in the height direction of the swirl vane 23a. The fuel jets out in the same direction as the air flow G.
【００３７】本発明は以上説明した実施形態に限定され
るものではなく、特許請求の範囲内で種々の変更が可能
である。The present invention is not limited to the embodiments described above, and various modifications can be made within the scope of the claims.
【００３８】[0038]
【発明の効果】以上述べたように本発明のラム燃焼器は
主燃料ノズルの燃料噴出孔がスワーラの旋回羽根の高さ
方向に間隔を空けて複数配置されているのでスワーラ内
で燃料と空気の混合がさらに良くなりラムジェットエン
ジンの燃焼効率が向上するなどの優れた効果がある。As described above, in the ram combustor of the present invention, a plurality of fuel injection holes of the main fuel nozzle are arranged at intervals in the height direction of the swirler vanes of the swirler. It has an excellent effect such as that the mixing of is improved and the combustion efficiency of the ramjet engine is improved.
【図１】本発明のラム燃焼器のスワーラ部分の横断面図
である。1 is a cross-sectional view of a swirler portion of a ram combustor of the present invention.
【図２】本発明のラム燃焼器のスワーラの旋回羽根の斜
視図である。FIG. 2 is a perspective view of swirl vanes of a swirler for a ram combustor of the present invention.
【図３】本発明の他の実施形態のスワーラの旋回羽根の
斜視図である。FIG. 3 is a perspective view of swirl vanes of a swirler according to another embodiment of the present invention.
【図４】従来のラム燃焼器（未公開）のブロック図を併
記した正断面図である。FIG. 4 is a front sectional view in which a block diagram of a conventional ram combustor (unpublished) is also shown.
【図５】ラムジェットエンジンの概略構造を示す正断面
図である。FIG. 5 is a front sectional view showing a schematic structure of a ramjet engine.
【図６】ラム燃焼器の従来構造例を示す正断面図であ
る。FIG. 6 is a front sectional view showing a conventional structure example of a ram combustor.
【図７】ラム燃焼器の他の従来構造例を示す正断面図で
ある。FIG. 7 is a front cross-sectional view showing another conventional structure example of a ram combustor.
【図８】図４における気流導入口近傍の横断面図であ
る。8 is a cross-sectional view of the vicinity of the airflow introducing port in FIG.
１ ラムジェットエンジン ２ 燃焼器ダクト １０ 主燃焼器型保炎器 １０ｂ 周壁 ２１ 第１の燃料ノズル ２２ 副燃焼室 ２３ スワーラ ２３ａ 旋回羽根 ２３ｂ 気流通路 ２３ｃ 旋回羽根の側面 ２３ｄ 旋回羽根の後縁 ３０ 第２の燃料ノズル ３０ｂ 燃料ヘッダ ３０ｃ 燃料供給通路 ３０ｄ 燃料噴出孔 ３０ｆ 燃料噴出孔 1 ramjet engine 2 combustor duct 10 main combustor type flame stabilizer 10b peripheral wall 21 first fuel nozzle 22 auxiliary combustion chamber 23 swirler 23a swirl vane 23b airflow passage 23c swirl vane side face 23d swirl vane trailing edge 30 second Fuel nozzle 30b Fuel header 30c Fuel supply passage 30d Fuel injection hole 30f Fuel injection hole
Claims (3)
内部に搭載されるラム燃焼器であって、燃焼器ダクトの
内部に配され供給された燃料の燃焼を行なう主燃焼器型
保炎器と、該主燃焼器型保炎器の前端の中心位置に配さ
れ下流に開口を有するとともに第１の燃料ノズルから燃
料が供給される副燃焼室と、該副燃焼室と主燃焼器型保
炎器の周壁との間に前後方向に貫通する通路を形成する
ように円周方向に間隔を空けて配され、放射方向に延び
る複数の旋回羽根を有し気流の一部を主燃焼器型保炎器
の内部に取り入れ旋回流を生じさせるスワーラと、該ス
ワーラの内部に燃料を供給する第２の燃料ノズルとを具
備してなり、該第２の燃料ノズルは上記スワーラ外周に
配される円環状の燃料ヘッダと、上記旋回羽根の高さ方
向に延びて形成されていて、該燃料ヘッダと連通する燃
料供給通路と、上記旋回羽根の高さ方向に間隔を空けて
複数配置されていて、上記燃料供給通路と連通する燃料
噴出孔とからなることを特徴とするラム燃焼器。1. A ram combustor mounted inside a combustor duct of a ramjet engine, the main combustor type flame stabilizer being arranged inside the combustor duct to burn the supplied fuel. A sub-combustion chamber that is arranged at the center of the front end of the main combustor type flame stabilizer and has an opening downstream and is supplied with fuel from a first fuel nozzle; and the sub combustion chamber and the main combustor type flame stabilizer. Has a plurality of radially extending swirl vanes arranged in a circumferential direction so as to form a passage penetrating in the front-rear direction with the peripheral wall of the main combustion chamber flame holding part of the air flow. And a second fuel nozzle for supplying fuel to the inside of the swirler, the second fuel nozzle being provided on the outer circumference of the swirler. The fuel header and the swirl vane are formed to extend in the height direction. And a plurality of fuel supply passages communicating with the fuel header and a plurality of fuel injection holes arranged at intervals in the height direction of the swirl vanes and communicating with the fuel supply passages. Ram combustor.
おり、燃料をスワーラ内を流れる気流に交叉する方向に
噴出するようになっている請求項１記載のラム燃焼器。2. The ram combustor according to claim 1, wherein the fuel injection hole is opened on a side surface of the swirl vane, and the fuel is injected in a direction intersecting with an air flow flowing in the swirler.
ており、燃料をスワーラを出た気流と同じ方向に噴出す
るようになっている請求項１記載のラム燃焼器。3. The ram combustor according to claim 1, wherein the fuel injection hole is opened at the trailing edge of the swirling vane, and the fuel is ejected in the same direction as the air flow exiting the swirler.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP23673795A JP3785656B2 (en) | 1995-09-14 | 1995-09-14 | Ram combustor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP23673795A JP3785656B2 (en) | 1995-09-14 | 1995-09-14 | Ram combustor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPH0979088A true JPH0979088A (en) | 1997-03-25 |
| JP3785656B2 JP3785656B2 (en) | 2006-06-14 |
Family
ID=17005044
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP23673795A Expired - Fee Related JP3785656B2 (en) | 1995-09-14 | 1995-09-14 | Ram combustor |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JP3785656B2 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103542429A (en) * | 2012-07-10 | 2014-01-29 | 阿尔斯通技术有限公司 | Axial swirler for a gas turbine burner |
| CN104165521A (en) * | 2014-09-09 | 2014-11-26 | 苏州新协力环保科技有限公司 | Biomass smelting furnace burner |
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