• 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 aeronautical engineering, in particular, to propellers, and relates specifically to the aerodynamic profiles of blades and screw holes. The aim of the invention is to increase the efficiency of the propeller and reduce aerodynamic losses at flight speeds exceeding the M number of 0.65 by ensuring a continuous flow around the propeller. The proposed propeller contains a large number (more than eight) of the blades 1, protruding from the flap 2, ё (L § § :: G & OU l S
    公开号:SU1711664A3
    申请号:SU874203534
    申请日:1987-10-22
    公开日:1992-02-07
    发明作者:Буске Жан-Марк；Фобер Ален；Вэнгю Жорж
    申请人:Оффис Насьональ Д Этюд Э Де Решерш Аэроспасьаль О.Н.Э.Р.А. (Фирма)；
    IPC主号:
    专利说明:

    having a complex spatial shape, with the end of the OTOI blades being backwards in relation to the direction of rotation and relative to the plane of rotation. The middle line F of the blade is represented in the spatial Cartesian coordinate system by mathematical dependencies and determined by specific values obtained from the proposed dependencies. The thickness of the blade profiles and their distribution over the radius of the screw, as well as the spinner configuration with specific values of the coordinates of the generator points and dependencies to determine them. 5 hp; f-ly, 9 ill.
    The invention relates to aeronautical engineering and specifically relates to the aerodynamic profiles of the blades and the wing of the propeller of an aircraft engine.
    The aim of the invention is to increase the efficiency of the propeller and to reduce the aerodynamic losses at flight speeds of the aircraft exceeding the M number of 0.65 by ensuring a continuous flow around the propeller.
    FIG. 1 shows a multi-blade propeller, a general view: in FIG. 2 — the position of the center line of the blade in the OXYZ spatial coordinate system; in FIG. 3, a diagram of the proposed blade without twisting; figure 4 - the view and location. cylindrical sections of the blade at different radii; Fig. 3 is a diagram of a propeller with a fairing and a engine nacelle; in Fig. 6, a graph of the change in curvature of the generator of the propeller shown in Fig. 5; Fig. 7 is a graph showing the variation in the relative thickness of the propeller blade; Fig. 8 is a graph showing the variation in the relative chords of the propeller blade; Fig. 9 is a curve illustrating the law of twisting of the propeller blade.
    The propeller contains a large number (more than eight) of the blades 1 protruding from the flap 2, having an intricate spatial shape, with the end of the blades turned back towards the direction of rotation and relative to the plane of rotation.
    The center line F of the blade is represented in the spatial rectangular Cartesian coordinate system OXYZ (Fig.), Where the axis OX coincides with the axis of rotation; and the axes OY and OZ are located at a right angle in the plane of rotation of the screw. The ends of each blade are bent away from this plane (OZ - OY)
    back against the flight direction.
    To determine the position of the midline F, the angle F0 is introduced into the plane OZ - OY., Which forms the angle F0 with the axis OY. Thus, the current system can be connected to each point M
    coordinates MX ,,, MY, MZ4, obtained from the basic coordinate system GYfi, OZ0 by transferring the origin to the current point M, which allows each blade profile to determine
    in the MX plane - MY4.
    The middle line F of the propeller blade is a continuous, flat curve located in the plane OZ - OY6, forming an angle of $ 0 with the plane of rotation of the screw equal to 35-55 ° (mainly AP-50 °), with the middle line F of the blade defined at the base negative values of the Y0 coordinate and positive values of the Z coordinate, and at the end of the blade, positive values of the Y0 coordinate and Z coordinates. The point with the coordinate Ye 0 is determined by the values of the Z coordinate, comprising (0.75-0.85) R, where R is the radius of the screw, and is tangent to this curve on the co The nce blade forms an angle fl with the axis OZ; equal to 30-50 ° (mostly).
     The average line F of the propeller blade is defined in the plane OZ - OY0 by the equation
    Y0 / R M0 + M (Z / R) + MZ (Z / R) 2 + + M (Z / R) 3 + M4 (Z / R) 4;
    where 0, Ј 0,015; ., Ј0,2;
    -2 -1.0; 3.0; -1, Ј-0,5.
    The fairing 2 is made in the form of a body of rotation of a complex geometric

    5. I 17П664
    a shape that provides a local slowdown of the flow at the butt of the blades, which makes it possible to remove stalling properties and reduce aerodynamic losses. At the same time, the parameters of the curvature of the meridional line - the generator of the fairing - are defined as pa; X and Y diameters, related to the screw diameter D, and curvature values in certain parts of the generatrix from the beginning (front point on the axis of the fairing) to the end of the fairing defined by its trailing edge; the maximum value of the curvature, exceeding 15, is in front in the center on the axis of rotation of the fairing; further back downstream, the curvature of the spinner is also reduced in cross section
    X 0.05 is equal to 7; at a distance
    X - 0.5-0.7 curvature, linearly decreasing, reaches values close to zero; at a distance X L, where L is the distance from the front point on the generatrix to the given edge of the spinner along the axis of the screw, the curvature slowly monotonously decreases, the minimum value (3) - (- 5) is reached, and at the end of the fairing it again approaches zero. The transition from the fairing to the engine nacelle was carried out by smoothly combining the surfaces with observance of the conditions of the continuous flow around.
    The meridional line — the forming of a fairing — is composed of segments of curves with the following coordinates in a rectangular coordinate system X - Y:
    for 0 xl, 3
    Y 0.3271995Х1 - 2.422616Х2 + + 5.697069Х;
    for 0.3 6 X Ј 0.55
    Y 2,996639 - 38,21174Х +
    + 200.4801Х1 - 538.7765Х +
    G + 794,8556Х4 - 615,5586ХЬ + + 196.3246Х -
    As a result, the framing is defined by the following parameters:
    0
    ABOUT,

    .362TA61E-01 .5030967E-P1 .6P2555 + E-01
    .5000000Е-01 .6250000Е-01 .750000ПЕ-01 .87500 ПОЕ-01
    .SOOOOOOOE + OO .112500PE + OS
    .1250000E + 00
    .13750POE + 00 L500000E + 00 .161625000E + 00 L750000E + 00 .1875000E + 00 .2000000E-SO
    ..1;: 5000E + oo
    .2250000ЕЧ-00
    .2375000Е + 00
    .250f) OOOE + 00
    .2625000Е + 00
    .2750000Е-ЮО
    .2875000Е + 00
    .ZOOOOOOE + 00
    .Su 167E + 00
    .3208333E + 00
    .3312500E + 00
    .3 16667E + 00
    .3520833E + 00
    .3625000Е + 00
    .3729167E + 00
    3833333Е + 00
     3937500Е-ЮО
    DOM667E + 00
    L1 5833E + 00
    L250000E + 00
    .i 351H67E + 00
    Dg 58333E + 00
    .45625OOE + 00
    .46666b7E + cb
    L7708.33E + 00
    L875000E + 00
    .6781963Е-01 .7372742Е-П1. 7838351Е-01
    .8205535Е-01
    . .8719646Е-01
    .889567.1 E-01
    .9033639Е-01
    .91 257Е-01
    .9237234Е-01
    .9321749Е-01
    .9406537Е-01
    .9499998Е-01
    .9610265E-01
    .9745259Е-01
    .9912732Е-01
    .1012030E + 00
    . 103 75M E + 00
    .1068558E + 00
    .1105801E + 00
    .11500SOE + 00
    .1192282E-fOO
    .1237836E + 00
    .1284998Е + 00
    .1332382E + OP
    .1378875E + 00
    .1423614E + 00
    .1465950Е + 00
    .1505422E + 00
    .1541728E + 00
    .1574703Е + 00
    .1604294Е + 00
    .1630536Е + 00
    .1653538Е + 00.
    .1673461E + 00
    .1690503E + OQ
    . 17С4886Е + 00
    L716840E + 00
    .1726598E + 00
    .9791b7e + 00 .5083333e + 00
    .5187500Е + 00 .5291667Е + 00 .5395833Е + 00 .550000UE + 00
    The following profiles are available: distance. 0.3R. from the axis of rotation, relative thickness e / C 13%, at a distance of 0.5R e / C 9%; at a distance of 0.7R e / C of 6%; at a distance of Q, 9R e / C 3.5% T, the profile with thickness e / C 13% is smoothly transformed into the butt of the blade.
    权利要求:
    Claims (2)
    [1]
    Invention Formula
    1 "Multi-propeller propeller of an aircraft engine that energizes blades of complex aerodynamic shape with the ends bent back towards the direction of rotation and radome with radial holes for accommodating the butt blades, in order to increase the efficiency of the propeller and reduce aerodynamic losses / flight speeds of the aircraft, exceeding the M numbers of 0.65, by providing a continuous propeller flow, the middle line of the blades is a continuous flat-4 curve, The angle in the OZ – OY6 plane that forms an angle of 35–55 ° with the plane of rotation of the screw (mostly 0–50), the middle line of the blade is determined at its base by negative values of the Y0 coordinate and positive values of the Z coordinate, and at the end of the blade this line is determined by the positive values of the coordinates Y0 and the positive values of the coordinates Z, while the point with the coordinate Y0 0 is determined by the values of the coordinates Z, which are (0.75-0.85) R, where R is the screw radius and tangent to this curve at the end of the blade forms an angle of 30-50 ° with the OZ axis ( property).
    2. The screw according to claim 1, about tl and, h and u and with the fact that the average line of its blades is determined from the plane OZ-OY by the equation
    [2]
    and 1 by the fact that the contours of its oblique are made in the form of a body of rotation of a complex geometric shape with the following curvature parameters: the maximum curvature greater than 15 is in front in the center, on the axis of rotation of the fairing; further downstream, the curvature decreases and in section
    ordinate
    x g 0.05,
    the defined distance is where x is the distance between the first point on the axis of the fairing and the section considered, a D is the diameter of the screw, it is equal to 7 on the distance X 0.5-0.7 the curvature decreases linearly, reaches close to zero; at distance XL, where L is the distance from the first front point on the axis of the spinner to the plane of the blades, the curvature slowly decreases, reaches the minimum value (-3) - (- 5), and at the tip of the spinner at the trailing edge it approaches again to zero. B. The screw according to claim 3, wherein the meridional line — forming a spinner — is composed of segments of curves with the following coordinates in the rectangular coordinate system X - Y, where X is
    S. y
    D
     Z.
    .D
    dl o: x Ј0.3
    , C2
    Y, 3271995Х -., 42.2b1bH +
    + 5.697069Х3; long 0.3Ј, 55
    Y 2,996639 - 38, 4 -I- 2PO, 801Х2 - 538.7765Х3 + + 79М556Х4 - 615.5586Х + + 1-9b, 3246Х6,
    5. The screw according to claim 3, differing from the fact that the meridional line — the forming of the fairing — is determined by the following parameters:
    . .1250000Е-01
    .2500000Е-01 .3750000Е-01 .5000000Е-01 .6250000Е-01 .7500000Е-01 .8750000Е-01 .1000000Е + 00 .1125000ЕЕ 00. 17.5 000 OU + 00 .137500OE + 00 .1500000Е + 00 .1.625000Е + 00 .1750000Е + ПО .1875000Е + 00 .2000000EJ-00 .212500LE + ОП .2250000Е 00 .2375000Е + 00 .25001ШЕ + О .2625QOOE + OG. 2750000E + OQ -.2875000E + 00. ZOOOOOOE + OP. ZII167Ј + 00 .3208333E + 00. 3312500E + OP
    0. .362Й61Е-01
    .5030967E-01 .602555 E-01 .6781963E-01 .73727 / 2E-01 .7838351E-01 .8205535E-01 .8 9 048E-01 .87196IE-01 .8895621E-01 .9033639E-01 .91 257Е-01 .923723 Е-01 .93217 9Е-01 .91гВб537Е-01 9499998Е-01 .96Ю265Е-01 97 5259Е-01 .9912732Е-01 J012030E + 00 .10375i I E + Ofl. Ю68558Е + 00 ... 1105801 E + OU- .115COOOE + DO .1192282E + 00 .1237836E + 00 .128499 & E + 00
    0
    five
    0
    five
    0
    .3 16667E + OG)
    3520833E + 00
    .3625000Е + ОП
    .3729167E + 00
    .3833333Е + 00
    .3937500Е + 00
    TO P667E + 00
    .4U5833E + 00
    D250000E + 00
     I 35itl67E + 00
    .58333E + 00
    -.4562500Е + 00
    . “Bbb b e + OO
    .770833Е + 00
    L8750POE + 00
    .4979167E + 00
    .5083333E + 00
    .5187500Е + 00
    .5291667Е + 00
    5395833E + 00
    .5500QOOE + 00
    .1332382E + 00
    .13-78875 E + OP
    .1423614E + 00
    .146595СЁ + 00
    .15P5422E + 00
    .1541728E + 00
    .1574703Е + 00
    .1604294Е + 00
    .1630536Е + 00
    .1653538Е-ЮО
    .1673461 echo about
    .1690503E + 00
    .170Ш6Е + 00
    .1716840Е + 00
    .1726598E + 00
    .1734383E + software
    .1740401Е + 00
    .1744838Е + 00
    .1747857E + 00
    .1749592E + 00
    .1750155Е + 00
    6. A screw as claimed in claim 1 or 2, in which the blades are formed by the following profiles: at a distance P, H from the axis of rotation, the relative thickness e / C is 13% by distance 0.5 r e / s -9x; at a distance of 0.7R e / C at a distance of 0.9R e / C 3.5%, while the profile with thickness e / C 13% is smoothly transformed into the butt of the blade.
    fttt.f
    t - /
    Phage. 2
    FIG.
    /
    01
    "AND
    Q
    at
    L
    ABOUT
    , "L
    "about
    go
    ъ
    -about
    V
     Q
    TO
    R
    FIG. 9
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    同族专利:
    公开号 | 公开日
    EP0265335B1|1990-02-07|
    DE3761646D1|1990-03-15|
    US4790724A|1988-12-13|
    EP0265335A1|1988-04-27|
    FR2605588A1|1988-04-29|
    FR2605588B1|1989-04-28|
    引用文献:
    公开号 | 申请日 | 公开日 | 申请人 | 专利标题
    US1658438A|1925-08-13|1928-02-07|Hall Charles Ward|Propeller|
    FR684161A|1929-01-04|1930-06-23|Belge Const Aeronautiques|Propeller|
    US1929690A|1930-11-13|1933-10-10|Charles B Huntman|Aircraft propulsion|
    US2043736A|1935-02-07|1936-06-09|Hartzell Industries|Ventilating fan|
    US3972646A|1974-04-12|1976-08-03|Bolt Beranek And Newman, Inc.|Propeller blade structures and methods particularly adapted for marine ducted reversible thrusters and the like for minimizing cavitation and related noise|
    FR2315001A1|1975-06-18|1977-01-14|Entat Marcel|PROCESS FOR REALIZING PROPELLER BLADES AND IMPROVED PROPELLER BLADES OBTAINED BY IMPLEMENTING THIS PROCESS|
    US4171183A|1976-09-24|1979-10-16|United Technologies Corporation|Multi-bladed, high speed prop-fan|
    US4370097A|1979-07-16|1983-01-25|United Technologies Corporation|Noise reduction means for prop-fan|
    US4358246A|1979-07-16|1982-11-09|United Technologies Corporation|Noise reduction means for prop-fan and the construction thereof|
    CA1270802A|1985-02-07|1990-06-26|Edward A. Rothman|Prop-fan with improved stability|US4941803A|1989-02-01|1990-07-17|United Technologies Corporation|Airfoiled blade|
    US5114313A|1990-04-10|1992-05-19|501 Michigan Wheel Corp.|Base vented subcavitating marine propeller|
    US5597138A|1991-09-30|1997-01-28|Arlton; Paul E.|Yaw control and stabilization system for helicopters|
    US6071077A|1996-04-09|2000-06-06|Rolls-Royce Plc|Swept fan blade|
    US5749540A|1996-07-26|1998-05-12|Arlton; Paul E.|System for controlling and automatically stabilizing the rotational motion of a rotary wing aircraft|
    US20110158808A1|2009-12-29|2011-06-30|Hamilton Sundstrand Corporation|Method for propeller blade root flow control by airflow through spinner|
    CN113022849A|2021-05-28|2021-06-25|北京三快在线科技有限公司|Propeller and rotor craft|
    法律状态:
    优先权:
    申请号 | 申请日 | 专利标题
    FR8614826A|FR2605588B1|1986-10-24|1986-10-24|IMPROVEMENTS ON AIR PROPELLERS, ESPECIALLY FOR AIRCRAFT PROPELLERS|
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