• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    The invention relates to the field of aeronautical engineering, in particular to propellers, and relates specifically to fairings of blown propellers. The aim of the invention is to reduce the aerodynamic losses on the engine when the Mach numbers are greater than 0.65, by giving the wind deflector an optimal aerodynamic shape and providing the loops. The proposed propeller has a large number (more than eight) of blades 1 protruding from the flap 2, made in the form of a body of rotation of a complex geometric shape, providing braking of the flow in front of the blades of the blades. The curvature parameters of the meridional line — the windrower — are represented by the X and Y parameters in a flat rectangular Cartesian coordinate system by mathematical dependencies and are determined by specific parameter values obtained from these dependencies. Slowing flow before the propeller blades reduces the intensity of flow deceleration in the channels between propeller blades and the reflection of the onset of stallions. 2 hp f-ly, 2 ill. (L with
    公开号:SU1704622A3
    申请号:SU874203533
    申请日:1987-10-22
    公开日:1992-01-07
    发明作者:Буске Жан-Марк；Фобер Ален
    申请人:Оффис Насьональ Д,Этюд Э Де Решерш Аэроспасьаль О.Н.Э.Р.А. (Фирма)；
    IPC主号:
    专利说明:

    The invention relates to the field of aviation technology and relates specifically to propeller fairings. The purpose of the invention is the reduction of aerodynamic losses and the entrance to the engine with Mach numbers greater than 0.65 by giving the fairing of the propeller an optimal aerodynamic shape and providing local flow inhibition in front of the knots of the blades.
    In Figure 1, a propeller diagram with blades, a fairing and a nacelle is presented; on Lig.2 - a curve showing the change in the curvature of the generatrix of the fairing of the screw.
    The propeller contains a large number (more than eight) of the blades 1, protruding from the fairing 2, made in the form of a body of revolution of complex geometric shape, providing inhibition of the flow at the butt of the blades and the distant mode of occurrence of stall currents. The curvature parameters of the meridional line — the generatrix of the fairing are determined by the parameters X and Y in a flat rectangular Cartesian coordinate system, and these parameters are related to the diameter of the screw D and allow you to show the characteristic cross-section of the fairing, in which there are changes in the curvature of the generatrix determined by the following parameters: the maximum value of curvature, greater than 15, is in front in the center on the axis of rotation of the fairing; further downstream the curvature of the radome generatrix decreases and in the cross section X = = - - 0.05 it is equal to 7; at a distance X = 0.5-0.7, the curvature, linearly decreasing, reaches values close to zero; at a distance X = L, where L is the distance from the leading point on the generatrix to the trailing edge of the fairing along the axis of the screw, the curvature slowly decreases monotonously, reaching a minimum value of (-3) - (- 5), and at the end of the fairing at the trailing edge it again approaching zero.
    The transition from fairing 2 to the motorcycle race 3 is made by a smooth combination of surfaces in compliance with the conditions of continuous flow.
    The meridional line — the generatrix of the fairing — is composed of the segments of the curves shown in Lig. 2 with the following coordinates; for 0 <X £ 0.3 Y = 0, 3271995X , r - 2.522616X 2 + + 5.697O69X 3 ; for 0.3 ίχ <0.55 Υ = = 2.996639-38.211 7CHX + 2OO, 48Ο1χ 2 -538.7765X 3 + 794.8556X * -615.5586X + + 196.324bx
    Given the given dependencies, the radome generatrix is represented by the following parameters:
    10 X At0. about..125OOOOE — 01 . 362146 IE — 01.2500000Е-01 .5O3O9b7E-01.375OOOOE-O1 .6025554Е — 01 fifteen .5000000E-01 .6781963Е-О1 .6250000Е-П1 . 7372742E-01.7500000E-01 .7838351E-01.8750000Е-01 .82O5535E-O1. 1000000F.-UO .8494048Е-01 20 .1125000Е-00 .8719646E-01. 12β0000Ε + 00 . 889 5621E — 0-1. 1375OOOE + OO .9O33639E-01.1500000Е + 00 .9144257Е-01o 1625OOOOE + OO o9237234E — 01 25 . 175OOOOE + OO .9321749E — 01.1875000E + 00 .94O6537E-01.2000000E + 00 .9499998Е — 01.2125000and + 00 .961О265Е-01.225OOOOE + OO .9745259Е — 01 thirty <, 2375000E + 00 • 9912732E — 01 .2500000Е + 00  .1012030Е + 00.2625OOOOE + OO . Yu37544E + OO.2750000Е + 00 .1068558Е + 00.2875000E + 00 .1105801Е + 00 35 .ZOOOOOOE + OO . 1150000E + 00 .3104167Е + 00 .1192282E + OO.3208333Е + 00 4 . 1237836E + OO.3312500E + 0P .1284998Е + 00.3416667Е + О0 . 1332382E + OO 40 .352O833E + OO . 13 78875E + 00 • 3625000E + 00 . 1423614E + OO.3729167Е + ОО . 146595OE + OO.3833333Е + ОО .15O5422E + OO.39375OOE + ОО .1541728Е + ОО 45 „4О41667Е + ОО .15747 OZE + OO • 4145833Е + ОО . 16O4294E + OO.4250000Е + 00 . 1630536Е + 00.4354167Е + ОО . 1653538E + 00.4458333Е + ОО .1673461Е + 00 fifty .45625OOE + ОО .169О5ОЗЕ + ОО . 4666667E + OO .17O4886E + OO.477О833Е + ОО .171684OE + OO.4875OOOOE + OO .1726598Е + ОО.4979167Е + ОО .1734383Е + ОО 55 .5O83333E + OO . 1 740401Е + 00 .5187500] · + 00 . 1 744838E + OO.5291667Е + ОО .1747857Е + ОО.5395833Е + 00 . 1 749592E + OO.55OOOOOOE + OO . 1 750155E + OO
    704622
    In the preceding 11-ig .: fairing there was a significant slowdown in the flow in the region of the plane of the blades, which helps to reduce the rate of inhibition of flow in the droplets between the rotor blades and the separation of the beginning of stall phenomena.
    权利要求:
    Claims (3)
    [1]
    Claim
    1. A multi-vane propeller for the aircraft engine, containing a radome-shaped fairing for accommodating blades, characterized in that, in order to reduce aerodynamic losses at the engine inlet at Mach numbers greater than 0.65 by giving the aerodynamic propeller a fair aerodynamic shape and providing local flow inhibition in front of the knots of the blades, the fairing is made in the form of a body of revolution of complex geometric shape, having 25 the following curvature parameters: maximum value of visas in excess of 15, is in front, [in the center on the axis of rotation of the fairing; further downstream, the curvature βθ also decreases in the section determined by the coordinate X = - = 0.05, where x is the distance between the front point on the fairing and the section under consideration along the axis of the screw, I) is the diameter of the screw, it is 7; at distances X = 0, 5-O, 7, the curvature decreases linearly and reaches values close to zero; at a distance of X = L, where L is the distance between the front point on the axis of the screw and the plane of the blades, the curvature slowly decreases and reaches a value equal to (-3) - (- 5), and at the rear edge of the fairing it is again close to zero.
    [2]
    2. The propeller according to claim 1, characterized in that the meridional line forming the contours of the fairing is composed of separate segments of the curves characterized by the following coordinates in a rectangular Cartesian system X — Y, where for 0 <X <0.3, Υ = Ο , 32 71995χ * -2.422616X g + 5.697O69X ':
    for 0.3 £ ΧέΟ, 55 Υ = 2.996639 -38.21 174X + 20O, 48O1X 2 -538.7765X 3 + + 794.8556χ 4 -615.5586X ^ + 196.3246X 6
    [3]
    3. The propeller according to claim 1, with respect to the fact that the meridional line forming the contours of the fairing is defined by the following parameters:
    X (1.
    .12560008-61 .25000008-01 .37500008-01, 50000008-01 .62500008-01 .75OOOOOE-O1 .87500008-01 .10000008 + 00 .1125000Е + 00 .12500008 + 00 .13750008 + 00 .1500000Е + 00 .1625000Е +00 .17500008 + 00 .18750008 + 00 .20000008 + 00 .2125ОООЕ + ОО '.22500008 + 00 .23750008 + 00 .250000 (18 + 00 .26250008 + 00 .27500008 + 00 .28750008 + 00 .30000008 + 00. ZYU4167E + OO .32083338 + 00 .33125008 + 00 .3416667Е + 00 .35208338 + 00 .3625000Е + 00 .3729167Е + ОО .38333338 + 00 .39375008 + 00 .40416678 + 00 .4145833Е + ОО .42500008 +7. OO .4458333E + OO .45625008 + 00 .4666667Е + ОО .47708338 + 00 .48750008 + 00 .49791678 + 00 .5О83333Е + ОО .51875ОЕ + ОО .5291667Е + ОО .53938338 + 00 .55000008 + 00.
    Y
    0.
    .36214618-01 .50309678-01 .60255548-01 .67819638-01 .7372742Е-О1 .78383518-01 .82055358-01 .84940488-01 .87196468-01 .88956218-01 .90336398-01 .91442578-01 .92372348 -01 .93217498-01 .94O6S378-01 .84999988-01 .96SH265E-01 .97452598-01 .99127328-01 .10120308 + 00 .10375448 + 00 .10685588 + 00. 1 1058018 + 00 .11500008 + 00 .11922828 + 00 .1237836Е + ОО .12849988 + 00. 1332382E + OO .1E78875E + OO. 1423614Е + 00 .14659508 + 00 .15054228 + 00 .15417288 + 00 .15747ОЗЕ + ОО. 16O4 294E + OO .16305368 + 00. 16535388 + 00 .1673461Е + ОО .16905038 + 00 .17О4886Е + ОО. 171684OE + OO. 1726598E + OO .17343838 + 00. 17404018 + 00. 1 7448388 + 00. 1 74 78578 + 0 (1 .1749592Б + ОО .17501558 + 00
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    同族专利:
    公开号 | 公开日
    FR2605587B1|1989-06-16|
    US4790725A|1988-12-13|
    EP0266263B1|1989-09-20|
    DE3760575D1|1989-10-26|
    FR2605587A1|1988-04-29|
    EP0266263A1|1988-05-04|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1402539A|1917-09-14|1922-01-03|Oscar A Ross|Aeroplane propeller or the like|
    GB172997A|1920-06-25|1921-12-28|Alexander Albert Holle|Improvements in screw propellers and the like|
    US1929690A|1930-11-13|1933-10-10|Charles B Huntman|Aircraft propulsion|
    US2408677A|1942-03-23|1946-10-01|Rotol Ltd|Propeller spinner|
    US2637403A|1949-12-06|1953-05-05|United Aircraft Corp|Propeller spinner construction with boundary layer control|
    US2924282A|1955-06-21|1960-02-09|Curtiss Wright Corp|Aircraft propeller spinners|
    US2934150A|1955-12-21|1960-04-26|United Aircraft Corp|Pressure-contoured spinner|
    GB858706A|1957-02-18|1961-01-11|United Aircraft Corp|Drag-reducing devices for aircraft propellers|
    GB1524908A|1976-06-01|1978-09-13|Rolls Royce|Gas turbine engine with anti-icing facility|
    US4171183A|1976-09-24|1979-10-16|United Technologies Corporation|Multi-bladed, high speed prop-fan|
    US4419053A|1981-11-20|1983-12-06|Fairchild Swearingen Corporation|Propeller spinner|GB8904478D0|1989-02-28|1989-04-12|Rolls Royce Plc|Gas turbine engine air intake|
    US5224833A|1989-02-28|1993-07-06|Rolls-Royce Plc|Fan for a gas turbine engine air intake|
    US5167489A|1991-04-15|1992-12-01|General Electric Company|Forward swept rotor blade|
    US5695370A|1996-02-21|1997-12-09|Lin; Solas Y.J.|Motorboat propeller|
    GB2314384A|1996-06-18|1997-12-24|Lin Solas Yun Jin|Motorboat Propeller|
    WO2004090346A1|2003-04-11|2004-10-21|Karl Maurenbrecher|Method and apparatus for modifying the flow properties of a fluid medium in the vicinity of a propeller, fan, turbine or engine|
    US20050254957A1|2004-05-14|2005-11-17|Datech Technology Co., Ltd.|Fan hub with a rocket shaped end|
    DE102008055631A1|2008-11-03|2010-05-06|Rolls-Royce Deutschland Ltd & Co Kg|Hub cone for an aircraft engine|
    US10670040B2|2017-02-22|2020-06-02|Honeywell International Inc.|Core-protecting fan modules and turbofan engines containing the same|
    US11040767B2|2017-11-30|2021-06-22|General Electric Company|Systems and methods for improved propeller design|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR8614722A|FR2605587B1|1986-10-23|1986-10-23|IMPROVEMENTS ON AIR PROPELLERS, ESPECIALLY FOR AIRCRAFT PROPELLERS|
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