JPS60153401A - Sweep-back rotary wing with upper wing - Google Patents
Sweep-back rotary wing with upper wingInfo
- Publication number
- JPS60153401A JPS60153401A JP59007021A JP702184A JPS60153401A JP S60153401 A JPS60153401 A JP S60153401A JP 59007021 A JP59007021 A JP 59007021A JP 702184 A JP702184 A JP 702184A JP S60153401 A JPS60153401 A JP S60153401A
- Authority
- JP
- Japan
- Prior art keywords
- wing
- blade
- centrifugal
- disc
- rotary
- 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.)
- Pending
Links
- 230000000630 rising effect Effects 0.000 abstract description 12
- 238000010586 diagram Methods 0.000 description 4
- 238000013459 approach Methods 0.000 description 2
- 230000001174 ascending effect Effects 0.000 description 2
- 241000272470 Circus Species 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002347 injection Methods 0.000 description 1
- 239000007924 injection Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/001—Flying saucers
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
【発明の詳細な説明】
本発明は航空機に用いる回転翼に関し、より詳細には羽
根車状の回転翼に於て、基盤である車を上方より見て、
軸心より遠心方向に下垂的となし該車の上面に所定数の
翼溝を遠心かつ後退的（回転方向に対して）に設けると
共に、該翼溝の前上端縁（回転方向の）より回転方向に
張り出す上翼を設け、翼溝の立上り壁と上翼と回転翼の
車上面との間の空間に流れる空気流により、浮力を得て
飛行せんとする航空機の上翼付後退回転翼に関する。DETAILED DESCRIPTION OF THE INVENTION The present invention relates to a rotor blade used in an aircraft, and more specifically, in an impeller-shaped rotor blade, when a wheel serving as a base is viewed from above,
A predetermined number of blade grooves are provided on the upper surface of the car centrifugally and retrogradely (with respect to the rotational direction) in a downward direction from the axis, and the blade is rotated from the front upper edge of the blade groove (in the rotational direction). A swept-swept rotor wing with an upper wing of an aircraft that has an upper wing that extends in the direction of the wing, and obtains buoyancy by the airflow flowing in the space between the rising wall of the wing groove and the upper wing and the upper surface of the rotor blade. Regarding.
従来、航空機は垂直上昇するハリヤー、ヘリコプター等
を含めても、プロペラ、回転半径の大な長い板状の回転
翼又は噴射エンジンによるものが実用に供されているだ
けで、羽根車状の回転翼を用いたものはなかつた。現在
知られている形式では（１）垂直上昇できる程の效率の
良いものが殆んどなく、たとえあつても（２）水平飛行
になると問題が多いためである。Until now, aircraft, including vertically ascending harriers, helicopters, etc., have only been put into practical use with propellers, long plate-shaped rotary blades with a large rotation radius, or injection engines; None of them used . This is because (1) most of the currently known types are not efficient enough to fly vertically, and even if they are (2) there are many problems when it comes to horizontal flight.
本発明はコンパクト、高場力かつ水平飛行にも效率的な
羽根車状の回転翼を提供せんとするもので、本発明を実
施例により詳述すると。The present invention aims to provide an impeller-shaped rotary blade that is compact, has high field force, and is efficient even in horizontal flight.The present invention will be described in detail with reference to examples.
実施例−１ （第１図より第３図参照）本実施例は回転
翼を機体上部に設けた垂直上昇機１で、その外周を回転
翼２に囲繞され、中央内部には円筒状の機体５を設け、
支持桿９を介してその外方のリング状の底盤９を前記機
体５に一体に固定し、該底盤９に静翼を９０度間隔で設
け、中心部の機体５は上方にエンジン、底部にキヤビン
が設けてある。Embodiment 1 (Refer to Figures 1 to 3) This embodiment is a vertical lift aircraft 1 with rotor blades installed on the upper part of the fuselage.The outer periphery of the aircraft is surrounded by rotor blades 2, and inside the center is a cylindrical fuselage. 5,
The outer ring-shaped bottom plate 9 is integrally fixed to the fuselage 5 via a support rod 9, and stator blades are provided on the bottom plate 9 at 90 degree intervals. A cabin is provided.
エンジンの上部の出力軸は回転キヤツプ３と連結してあ
る。回転キヤツプ３の内壁は回転翼２の上部外面に合わ
され、一体に固定してある。The upper output shaft of the engine is connected to a rotary cap 3. The inner wall of the rotary cap 3 is aligned with the upper outer surface of the rotor blade 2 and is fixed integrally therewith.
支持桿９の上方には静翼が設けてあり、回転翼の下方に
近接せしめ、吸入口６（後述）より導いた空気に対面し
、逆転トルクを得て機体を安定せしめている。Stator blades are provided above the support rod 9, and are placed close to the bottom of the rotor blades, facing the air introduced from the intake port 6 (described later), and stabilize the aircraft by obtaining reverse torque.
この回転翼は矢印方向に回転して機体を上昇せしめるが
、破線で示す翼溝の立上り壁８より回転方向の前方であ
る横線部分には立上り壁上部に連続せしめた上翼７が設
けてある。These rotor blades rotate in the direction of the arrow to raise the aircraft, and an upper wing 7 that is continuous with the upper part of the rising wall is provided in the horizontal line portion that is forward of the rising wall 8 of the wing groove shown by the broken line in the direction of rotation. .
立上り壁８は回転キヤツプ３より外周方向に次第に高く
構成されているので、回転翼上面と上翼の間の空隙も外
周に近づけばそれに応じて広い空間が形成されている。Since the rising wall 8 is configured to be gradually higher than the rotary cap 3 in the outer circumferential direction, the gap between the upper surface of the rotor blade and the upper blade also becomes wider as it approaches the outer circumference.
又、この上翼には柔構造がもたせてあり、通常の航空機
の如く、翼が撓んで、回転翼全体えの衝撃を緩和できる
構成となつている。Additionally, the upper wing has a flexible structure, so that the wing can flex, like a normal aircraft, to cushion the impact on the entire rotor.
回転翼３の上方、即ち中央の回転キヤツプ３より後退か
つ遠心的に設けた翼溝の下方端部には吸、入口６が設け
てあり、該口６は回転翼外周内に心かつ下方に向けた道
孔に連通せしめてある。A suction inlet 6 is provided at the lower end of the blade groove, which is provided above the rotor blade 3, that is, backward and centrifugally from the central rotary cap 3. It is connected to the road hole towards which it is directed.
本例に於ては既述の如く、回転翼は羽根車の変型的形状
で、車は翼溝と上翼を融合的に一体に構成してある
かく構成された本発明による上翼付後退回転翼に対する
空気流は後退的な立上り壁に衝突することがなく、接触
により誘導されつつ加速されて慣性力を附与されるので
、従来知られている羽根車例えば、ジエツトエンジンの
圧縮機に用いられる羽根車の放射的な立上り壁に衝突す
る空気流に生ずる圧縮抵抗は大きく、本例の後退壁で接
触的な加速によれば同じエネルギーでもより高速回転が
可能となり、より大量の空気を上翼の下面に取り込み、
かつ上翼下面の加速空気流は上翼が遠心方向に次第に下
垂しているので、上翼下面に接触しつつ圧縮されるが、
その際に上翼下面を押し上げ、下方の翼溝上面の直上で
は希薄となるため、回転翼全体の浮力が増大する。従つ
て、上翼の張り出しが一定以上ないと揚力も得られない
。そして本例の上翼は柔構造となつていて、強風圧には
撓くで緩衝的な作用をする。In this example, as described above, the rotor blade has a modified shape of an impeller, and the wheel has a blade groove and an upper blade integrated into one. The airflow to the rotor does not collide with a receding rising wall, but is guided and accelerated by contact and is given an inertial force. The compression resistance generated in the air flow that collides with the radial rising walls of the impeller used in into the underside of the upper wing,
In addition, the accelerated air flow on the lower surface of the upper wing is compressed while coming into contact with the lower surface of the upper wing, as the upper wing gradually descends in the centrifugal direction.
At this time, the lower surface of the upper blade is pushed up, and the air becomes thinner just above the upper surface of the lower blade groove, increasing the buoyancy of the entire rotor blade. Therefore, lift cannot be obtained unless the upper wing overhangs beyond a certain level. The upper wing in this example has a flexible structure, which flexes and acts as a buffer against strong wind pressure.
尚、上述の例では上翼が４枚であるが、その他の複数、
例えば３，５，６…等適宜に選ぶが、以下に３条の翼溝
による３枚の上翼を設けた回転翼の上翼をダブルデルタ
状に形成した実施例を縮小略図で示すと。In addition, in the above example, there are four upper wings, but there are other multiple,
For example, 3, 5, 6, etc. may be selected as appropriate, but the following is a reduced schematic diagram of an embodiment in which the upper blade of a rotary blade is formed in a double delta shape, with three upper blades formed by three blade grooves.
実施例−２ （第４、第５図参照）
本例は上翼が３枚で、各々がダブルデルタ形状である点
で異るが、その他の点では前例とほぼ同じで、回転翼は
矢印Ｐ方向に回転し、破線で示す翼溝８′の立上り壁８
より回転方向の前方である横線部には立上り壁上部に連
続せしめた上翼７が設けてある。Example 2 (See Figures 4 and 5) This example differs in that there are three upper wings, each of which has a double delta shape, but in other respects it is almost the same as the previous example, and the rotor blades are indicated by the arrows. The rising wall 8 of the blade groove 8' rotates in the P direction and is indicated by a broken line.
An upper wing 7 that is continuous with the upper part of the rising wall is provided in the horizontal line portion that is further forward in the rotational direction.
立上り壁は回転キヤツプ３より外周方向に次第に高く構
成されているので、回転翼上面と上翼の間の空気も外周
に近づけば、それに応じて広い空間が形成されている。Since the rising wall is configured to be gradually higher than the rotating cap 3 in the outer circumferential direction, as the air between the upper surface of the rotor blade and the upper blade approaches the outer circumference, a correspondingly wider space is formed.
上翼は外周と立上り壁位置の破線と実線で示す遠心かつ
後退的な上翼前縁とに囲まれた横線部分である。The upper wing is a horizontal line portion surrounded by the outer periphery, a broken line at the position of the rising wall, and a distal and receding leading edge of the upper wing shown by a solid line.
上述の構成はより詳しくは１点鎖線ｌで示される位置で
の縦断面部分展開略図（第５図）に示す如く、回転翼２
は矢印Ｐの方向に回転するが、その正面は水平的で抵抗
を小とし、上面は車面２、翼溝底８′、上翼面７と流線
的に連続して空気抵抗の小な形状に構成してあり、この
流線的な連続面は回転方向の前縁より後方に移るに従つ
て下方に傾斜し、翼溝底よりカーブして立上り壁を構成
し更に上翼下面に連つている。More specifically, the above-mentioned configuration is as shown in a partial exploded vertical cross-sectional diagram (FIG. 5) at the position indicated by the dashed line l, where
rotates in the direction of arrow P, but its front surface is horizontal to reduce resistance, and its upper surface is streamlined and continuous with the car surface 2, the blade groove bottom 8', and the upper blade surface 7 to reduce air resistance. This streamlined continuous surface slopes downward as it moves rearward from the leading edge in the rotating direction, curves from the bottom of the blade groove to form a rising wall, and is further connected to the lower surface of the upper blade. It's on.
上述の構成による本例の回転翼の作用効果は実施例１と
ほぼ同じであり、上昇時にはダブルデルタ形状の上翼の
效率が高くなる。The effects of the rotary blade of this example with the above-described configuration are almost the same as those of the first embodiment, and the efficiency of the double delta-shaped upper blade is increased when ascending.
尚、図示しなかつたが、上翼に通常の翼に見られるスポ
イラーその他の補助翼を設けて回転翼の機能の多様化を
図ることができる。Although not shown in the drawings, the upper wing may be provided with a spoiler or other auxiliary wing that is found on a normal wing to diversify the functions of the rotary wing.
第１図より第３図は実施例−１を設けた垂直上昇機の縮
小略図で。
第１図はその平面図、
第２図はその底面図、
第３図はその側面図、
第４図、第５図は実施例−２の回転翼の縮小略図で、
第４図はその平面図
第５図は第４図中１点鎖線ｌで示す部分の縦断部分展開
略図である。
１−−−垂直上昇機、２−−−車 ３−−−回転キヤツ
プ、４−−−底盤、５−−−キヤビン ６−−−吸入口
７−−−上翼８−−−立上り壁 ９−−−翼溝底。
特許出願人 津田勝Figures 1 to 3 are scaled-down schematic diagrams of a vertical lift machine equipped with Embodiment-1. Figure 1 is a plan view thereof, Figure 2 is a bottom view thereof, Figure 3 is a side view thereof, Figures 4 and 5 are reduced schematic diagrams of the rotor blade of Example-2, and Figure 4 is a plane view thereof. FIG. 5 is a schematic longitudinal partially developed view of the portion indicated by the dashed-dotted line l in FIG. 1---Vertical lift machine, 2---Car 3---Rotating cap, 4---Bottom plate, 5---Cabin 6---Intake port 7---Upper wing 8---Rising wall 9 --- Wing groove bottom. Patent applicant Masaru Tsuda
Claims (1)
心より遠心かつ、下垂的な車に遠心かつ後退的な複数の
翼溝を上面に設け、該溝の回転方向前上端縁より、回転
方向に張り出す上翼を設けた上翼付後退回転翼。 （２） 複数の上翼が、遠心方向に移るに従い、回転方
向えの張り出しを長く構成して成る特許請求の範囲第１
項記載の上翼付後退回転翼。 （３） 複数の上翼の回転方向えの張り出しが、回転軸
心部より僅かづつ長くなり、遠心方向えの中程所定位置
より急角度にダブルデルタ翼状に長く構成して成る特許
請求の範囲第１項記載の上翼付後退回転翼。 （４） 翼溝が軸心より遠心方向に移るに従い、次第に
深く構成して成る特許請求の範囲第１項又は第２項又は
第３項記載の上翼付後退回転翼。[Scope of Claims] In an impeller-shaped rotor blade provided on an aircraft, (1) a plurality of centrifugal and receding blade grooves are provided on the upper surface of a wheel that is centrifugal and downward from the rotation axis, and the direction of rotation of the grooves is A swept-back rotary wing with an upper wing that has an upper wing that extends in the direction of rotation from the front upper edge. (2) Claim 1, in which the plurality of upper wings extend in the direction of rotation longer as they move in the centrifugal direction.
A swept-back rotor with an upper wing as described in Section 1. (3) A claim in which the overhang of the plurality of upper blades in the rotational direction is slightly longer than the rotational axis, and is elongated in the shape of a double delta blade at a steeper angle than a predetermined middle position in the centrifugal direction. A swept-back rotor with an upper wing as described in item 1. (4) A swept-back rotary blade with an upper blade according to claim 1, 2, or 3, wherein the blade groove is configured to become gradually deeper as it moves from the axis in the centrifugal direction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59007021A JPS60153401A (en) | 1984-01-20 | 1984-01-20 | Sweep-back rotary wing with upper wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP59007021A JPS60153401A (en) | 1984-01-20 | 1984-01-20 | Sweep-back rotary wing with upper wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPS60153401A true JPS60153401A (en) | 1985-08-12 |
Family
ID=11654379
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP59007021A Pending JPS60153401A (en) | 1984-01-20 | 1984-01-20 | Sweep-back rotary wing with upper wing |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPS60153401A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111677689A (en) * | 2020-06-23 | 2020-09-18 | 东方电气集团东方电机有限公司 | Design method of vibration and noise reduction mixed flow pump or axial flow pump |
-
1984
- 1984-01-20 JP JP59007021A patent/JPS60153401A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111677689A (en) * | 2020-06-23 | 2020-09-18 | 东方电气集团东方电机有限公司 | Design method of vibration and noise reduction mixed flow pump or axial flow pump |
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