JPS5810279B2 - Aircraft thrust booster - Google Patents
Aircraft thrust boosterInfo
- Publication number
- JPS5810279B2 JPS5810279B2 JP52141296A JP14129677A JPS5810279B2 JP S5810279 B2 JPS5810279 B2 JP S5810279B2 JP 52141296 A JP52141296 A JP 52141296A JP 14129677 A JP14129677 A JP 14129677A JP S5810279 B2 JPS5810279 B2 JP S5810279B2
- Authority
- JP
- Japan
- Prior art keywords
- exhaust hole
- main wing
- engine
- augmentation device
- item
- 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
Description
【発明の詳細な説明】 本発明は、航空機の推力増強装置に関する。[Detailed description of the invention] The present invention relates to an aircraft thrust augmentation device.
航空機、特に大推力を必要とする短距離離着陸機におい
ては、エンジン推力を何らかの方法で増強することが、
エンジン重量の軽減につながり、製造及び運航面での経
済性の改善にとって好ましい。In aircraft, especially short takeoff and landing aircraft that require large thrust, it is necessary to increase the engine thrust in some way.
This leads to a reduction in engine weight, which is favorable for improving manufacturing and operational economics.
この推力増強のための手段としては、たとえば、ファン
ジェットエンジンのファン流を導管により具申方向に導
ひいて、はぼ具申全体にわたって設けられたノズルから
噴出させ、この噴流を２枚のフラップ間に吹き込んで斜
め後下方に流すようにした、いわゆるオーギュメンター
ウイングがある。As a means for increasing the thrust, for example, the fan flow of a fan jet engine is guided in the direction of the engine through a conduit, jetted from a nozzle provided over the entire surface of the engine, and this jet is sent between two flaps. There is a so-called augmentor wing that blows air into the air and causes it to flow diagonally backward and downward.
この構造によれば、ノズルからの噴流と翼まわりの気流
との混合により、翼まわりの気流の一部がフラップ間に
吸引されて吸引流を発生し、いわゆるエジェクター効果
により推力の増強が達成される。According to this structure, by mixing the jet from the nozzle with the airflow around the blade, a part of the airflow around the blade is sucked between the flaps, generating a suction flow, and the thrust is increased by the so-called ejector effect. Ru.
この構造は、推力増強率が比較的大きいという利点はあ
るが、空気導管及びノズル等による重量増加が大きな欠
点とされている。Although this structure has the advantage of a relatively large thrust enhancement rate, it has a major drawback of increased weight due to air conduits, nozzles, etc.
本発明は、このような欠点を伴なわず推力増強効果を達
成できる航空機の推力増強装置を提供することを目的と
するもので、その構成上の特徴は、扁平な形状の排気孔
を有するジェットエンジンを、その排気孔の長辺が主翼
の具申方向に対しほぼ平行で且つ主翼上面の前縁部より
後方において該主翼上面から間隔を保つように配置し、
エンジンを排気孔の両側においてほぼ気流方向に延びる
支持板により前記主翼に支持して主翼表面と排気孔との
間に誘引気流の通路が形成されるようにしたことにある
。An object of the present invention is to provide a thrust augmentation device for an aircraft that can achieve a thrust augmentation effect without such drawbacks, and its structural features include a jet having a flat exhaust hole. The engine is arranged so that the long side of the exhaust hole is substantially parallel to the direction of application of the main wing and maintains a distance from the upper surface of the main wing behind the leading edge of the upper surface of the main wing,
The engine is supported on the main wing by support plates extending substantially in the airflow direction on both sides of the exhaust hole, so that a passage for induced airflow is formed between the main wing surface and the exhaust hole.
此処に「ジェットエンジン」という用語は、ファンジェ
ットエンジン等をも含む意味に用いるもので、排気孔は
主翼の上面及び下面のいずれに対応させて設けてもよい
。The term "jet engine" is used herein to include fan jet engines and the like, and the exhaust holes may be provided on either the upper or lower surface of the main wing.
本発明によれば、ジェットエンジンの排気孔から噴出す
る噴流は、エンジンナセルと主翼表面との間の間隙を流
れる気体と混合を生じ、主翼前縁から上記間隙に流れ込
む吸引流を生じ、この吸引流のために主翼前縁部に負圧
が発生して、前縁推力の形で推力増強効果が達成される
。According to the present invention, the jet jet ejected from the exhaust hole of a jet engine mixes with the gas flowing in the gap between the engine nacelle and the main wing surface, and generates a suction flow that flows into the gap from the leading edge of the main wing. The flow creates negative pressure at the leading edge of the wing, achieving a thrust enhancement effect in the form of leading edge thrust.
この他、支持板の外側にも該支持板に沿った形で吸引流
が発生するが、この吸引流は推力増強に役立つことはな
く、むしろ主翼上面の境界層制御により大迎角での気流
の剥離防止に役立つ。In addition, a suction flow is generated along the support plate on the outside of the support plate, but this suction flow does not serve to increase thrust, but rather controls the boundary layer on the upper surface of the main wing to increase the air flow at a large angle of attack. Helps prevent peeling.
本発明は、通常型の航空機及びエンジン排気を利用した
短距離離着陸機のいずれにも応用できるもので、エンジ
ン噴流と気流との混合を大きくするために一般に採用さ
れている手段を組合わせることも勿論可能である。The present invention can be applied to both conventional aircraft and short takeoff and landing aircraft using engine exhaust, and may be combined with commonly used means for increasing the mixing of the engine jet and airflow. Of course it is possible.
以下、本発明の実施例を図について説明すると、第１図
において、本発明を実施した航空機は、主翼１と胴体２
とを包含し、胴体２の各側において、主翼１の前部上面
には一対のエンジン３が並んで配置されている。Hereinafter, an embodiment of the present invention will be explained with reference to the drawings. In Fig. 1, an aircraft in which the present invention is implemented has a main wing 1 and a fuselage 2.
On each side of the fuselage 2, a pair of engines 3 are arranged side by side on the front upper surface of the main wing 1.
エンジン３はそれぞれエンジンナセル４内に収められて
おり、扁平な排気孔３ａを有する。Each engine 3 is housed in an engine nacelle 4 and has a flat exhaust hole 3a.
エンジン３は、その排気孔３ａの長辺が主翼１の上面１
ａにほぼ平行に位置するように配置され、エンジンナセ
ル４は各排気孔３ａの両側において、流れ方向に延びる
支持板５により主翼１に取付けられる。The long side of the exhaust hole 3a of the engine 3 is located at the upper surface 1 of the main wing 1.
The engine nacelle 4 is attached to the main wing 1 by support plates 5 extending in the flow direction on both sides of each exhaust hole 3a.
排気孔３ａと主翼１の上面１ａとの間には、第２図に示
すように横方向に扁平な通路６が形成されている。A horizontally flat passage 6 is formed between the exhaust hole 3a and the upper surface 1a of the main wing 1, as shown in FIG.
第３図は上述した配置における作用を示すもので、扁平
な排気孔３ａから噴出した噴流７は、排気孔３ａの下面
と主翼上面１ａとの間の通路６を通る気体と混合を起し
、吸引流８を生じる。FIG. 3 shows the effect of the above arrangement, in which the jet 7 ejected from the flat exhaust hole 3a mixes with the gas passing through the passage 6 between the lower surface of the exhaust hole 3a and the upper surface 1a of the main wing. A suction flow 8 is generated.
また、第１図に示すように、支持板５の外側でも吸引流
９が生じる。Further, as shown in FIG. 1, a suction flow 9 is also generated outside the support plate 5.
吸引流８は、主翼前縁に負圧を発生して、前縁推力１０
の形で推力増強効果を達成する。The suction flow 8 generates negative pressure at the leading edge of the main wing, resulting in a leading edge thrust 10.
Achieve a thrust enhancement effect in the form of
吸引流９自体は推力増強には役立たない。The suction flow 9 itself is not useful for thrust enhancement.
支持板５は、吸引流８を増加し、吸引流９を減少させる
のに役立つ。The support plate 5 serves to increase the suction flow 8 and reduce the suction flow 9.
また、２基のエンジン３をその排気孔３ａが密接するよ
うに配置した図示の構成も吸引流８の増加に効果的であ
る。Further, the illustrated configuration in which two engines 3 are arranged so that their exhaust holes 3a are in close contact with each other is also effective in increasing the suction flow 8.
本発明においては、翼面とエンジン排気孔との間を通る
気流と、エンジン噴流との混合の度合が大きい程、推力
増強率が大きい。In the present invention, the greater the degree of mixing between the airflow passing between the wing surface and the engine exhaust hole and the engine jet flow, the greater the thrust enhancement rate.
従って、混合を高めるための手段を組合わせると一層効
果がある。Therefore, it is even more effective to combine means for increasing mixing.
第４図はその一例を示すもので、排気孔３ａの下面は、
長手方向に延びる山１２及び谷１３が交互に形成された
波形を有し、エンジン噴流と一般気流との接触面積を増
大させるようになっている。FIG. 4 shows an example, in which the lower surface of the exhaust hole 3a is
The waveform has alternating longitudinal peaks 12 and troughs 13 to increase the contact area between the engine jet and the general air flow.
この場合、最外方の溝１４の巾を適当に定めることによ
り、外側吸引流９を減少させ、推力増強率を一層高める
ことができる。In this case, by appropriately determining the width of the outermost groove 14, the outer suction flow 9 can be reduced and the thrust enhancement rate can be further increased.
第５図の例においては、エンジン排気孔３ａの下面には
、巾方向に間隔をもって複数の長手方向切込み１５が設
けられ、また第６図の例においては交互に斜上方及び斜
下方に彎曲させられた複数の舌状片１６．１７が形成さ
れている。In the example shown in FIG. 5, a plurality of longitudinal notches 15 are provided on the lower surface of the engine exhaust hole 3a at intervals in the width direction, and in the example shown in FIG. A plurality of tongues 16, 17 are formed.
また、これらの手段を組合わせることも可能で、たとえ
ば第４図の構造の山部１２及び谷部１３に第５図の切込
み１５又は第６図の舌状片１６．１７を設けてもよい。It is also possible to combine these means; for example, the notches 15 in FIG. 5 or the tongues 16, 17 in FIG. 6 may be provided in the peaks 12 and troughs 13 of the structure in FIG. 4. .
さらに、本発明を翼上面吹出し型（ＵＳＢ）短距離離着
陸機に適用する場合には、７図に示すように、排気孔３
ａの上下に排気制御ベーン１８，１９を取付け、着陸時
にこれを破線のように動かせばよい。Furthermore, when the present invention is applied to a wing top blowout type (USB) short takeoff and landing aircraft, as shown in Figure 7, the exhaust hole 3
Exhaust control vanes 18 and 19 may be attached to the top and bottom of a, and these may be moved as shown by the broken line during landing.
以上の説明によって明らかなように、本発明においては
、ジェットエンジンの扁平な排気孔が、その長辺を主翼
表面に対しはぼ平行にして、該表面との間に間隙を有す
るように配置され、エンジンは排気孔の両側はおいてほ
ぼ気流方向に延びる支持板により支持されているため、
エンジン排気孔下面と主翼表面との間に強い吸引流が生
じ、推力増強効果が達成でき、しかもこの構成のために
重量か増加する恐れもない。As is clear from the above description, in the present invention, the flat exhaust hole of a jet engine is arranged with its long side substantially parallel to the main wing surface, with a gap between it and the surface. , since the engine is supported by support plates extending substantially in the airflow direction, leaving both sides of the exhaust hole,
A strong suction flow is generated between the lower surface of the engine exhaust hole and the surface of the main wing, achieving a thrust enhancement effect, and there is no risk of weight increase due to this configuration.
第１図は本発明の一実施例を示す平面図、第２図は雪の
Ａ−Ａ線矢視図、第３図はＢ−Ｂ線矢視図、第４図ない
し第６図は他の実施例を示す斜視図、第７図は本発明を
翼上面吹出し型航空機に適用した例を示す概略断面図で
ある。
１・・・・・・主翼、２・・・・・・胴体、３・・・・
・・エンジン、３ａ・・・・・・排気孔、４・・・・・
・エンジンナセル、５・・・・・・支持板。Fig. 1 is a plan view showing one embodiment of the present invention, Fig. 2 is a view of snow taken along the line A-A, Fig. 3 is a view taken along the line B-B, and Figs. 4 to 6 are other views. FIG. 7 is a perspective view showing an embodiment of the present invention, and FIG. 7 is a schematic cross-sectional view showing an example in which the present invention is applied to a wing top blow-out type aircraft. 1... Main wing, 2... Fuselage, 3...
...Engine, 3a...Exhaust hole, 4...
・Engine nacelle, 5...Support plate.
Claims (1)
その排気孔の長辺が主翼の具申方向に対しほぼ平行で且
つ主翼上面の前縁部より後方において該主翼上面から間
隔を保つように配置し、エンジンを排気孔の両側におい
てほぼ気流方向に延びる支持板により前記主翼に支持し
て主翼表面と排気孔との間に誘引気流の通路が形成され
るようにしたことを特徴とする航空機の推力増強装置。 ２ 前記第１項において、排気孔の下面は長手方向に延
びる複数の山谷からなる波形に形成されたことを特徴と
する航空機の推力増強装置。 ３ 前記第１項において、排気孔の下面は巾方向に間隔
をもって複数の長手方向切込みが形成されたことを特徴
とする航空機の推力増強装置。 ４ 前記第１項において、排気孔の下面には交互に斜上
方向及び斜下方向に彎曲した複数の舌状片が形成された
ことを特徴とする航空機の推力増強装置。 ５ 前記第１項において、排気孔には上下可動な排気制
御ベーンが設けられたことを特徴とする航空機の推力増
強装置。[Claims] 1. A jet engine having a flat exhaust hole,
The long side of the exhaust hole is approximately parallel to the direction of development of the main wing, and the engine is arranged so as to maintain a distance from the upper surface of the main wing behind the leading edge of the upper surface of the main wing, and the engine extends approximately in the airflow direction on both sides of the exhaust hole. A thrust augmentation device for an aircraft, characterized in that it is supported on the main wing by a support plate so that a passage for induced airflow is formed between the main wing surface and the exhaust hole. 2. The thrust augmentation device for an aircraft according to item 1, wherein the lower surface of the exhaust hole is formed in a corrugated shape consisting of a plurality of peaks and valleys extending in the longitudinal direction. 3. The thrust augmentation device for an aircraft according to item 1, wherein a plurality of longitudinal notches are formed at intervals in the width direction on the lower surface of the exhaust hole. 4. The thrust augmentation device for an aircraft according to item 1, characterized in that a plurality of tongue-shaped pieces are formed on the lower surface of the exhaust hole, the tongues being curved alternately in an upward direction and a downward direction. 5. The thrust augmentation device for an aircraft according to item 1, wherein the exhaust hole is provided with an exhaust control vane that is movable up and down.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP52141296A JPS5810279B2 (en) | 1977-11-25 | 1977-11-25 | Aircraft thrust booster |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP52141296A JPS5810279B2 (en) | 1977-11-25 | 1977-11-25 | Aircraft thrust booster |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS5475798A JPS5475798A (en) | 1979-06-16 |
| JPS5810279B2 true JPS5810279B2 (en) | 1983-02-24 |
Family
ID=15288573
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP52141296A Expired JPS5810279B2 (en) | 1977-11-25 | 1977-11-25 | Aircraft thrust booster |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS5810279B2 (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA3034776A1 (en) * | 2016-08-25 | 2018-03-01 | Jetoptera, Inc. | Variable geometry thruster |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS52108412U (en) * | 1976-02-13 | 1977-08-18 |
-
1977
- 1977-11-25 JP JP52141296A patent/JPS5810279B2/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5475798A (en) | 1979-06-16 |
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