Propeller blade of aircraft

专利摘要:
The invention relates to aeronautical engineering, in particular, to aircraft propellers, and to further improve the aerodynamics of blades. The purpose of the invention is to improve the performance characteristics of aircraft propellers by delaying the formation of shock waves and detaching the boundary layer with increasing relative Mach numbers. Lo Invention relates to aeronautical engineering, in particular, to the propellers of aircraft and Cachrcfl to further improve the aerodynamics of propeller blades. The development of propellers is related to their continuous improvement with the Purpose of increasing efficiency, reducing noise, which is the direct function of the propeller, has an aerodynamic profile, the relative thickness of which is 3-25%, formed by upper convex and lower convexo-concave contours. At the maximum value at the leading edge, the curvature of the upper, convex contour of the profile changes monotonically, decreasing towards the trailing edge, reaching a value of 4 by k% chord and 0 at the trailing edge of the profile. The curvature of the lower convex-concave profile also varies monotonically, decreasing towards the rear edge, and from the leading edge it first decreases rapidly, reaching a value of 8 by about 3.5% of the chord and then decreases slowly to zero at the point located in in the range of 10–60% of the chord and then monotonously decreases to a negative value, remaining almost constant at the trailing edge. The laws for changing the curvature of profiles for different thicknesses are determined by mathematical dependencies and tabular data in a rectangular coordinate system. 12 ep f-ly, 16 ill., 4 tab. The relative velocity at the end of the blade, reducing the mass of the blades, which can be achieved by reducing the chord lengths of the profiles of the blades. There is also a desire to create such profiles of the blades, which have high coefficients of J c Ј 00 CJ
公开号:SU1741608A3
申请号:SU864028591
申请日:1986-11-19
公开日:1992-06-15
发明作者:Родд Анн-Мари；Тибер Жан-Жак
申请人:Оффис Насьональ Д.Этюд Э Де Решерш Аэроспасьаль О.Н.Э.Р.А.(Фирма)；
IPC主号:

专利说明:

lift, especially in airplane takeoff and climb conditions.
At the same time, at high cruising flight speeds of aircraft, the relative flow velocities at the tips of the blades can reach Mach numbers of 0.8 - 0.9. Under these conditions, the profile of the blade should not cause any shock waves or breakdown of the boundary layer in order to limit the growth of the drag coefficient and to ensure high values of screw efficiency.
The aim of the invention is to simplify the operational characteristics of the propellers of aircraft by delaying the formation of shock waves and the separation of the boundary layer with increasing Mach numbers.
On the profile of the propeller blade; figure 2 - changing the curvature of the upper and lower contours of the profile; on fig.Z front edge profile; in fig. - the laws of thickness variation of four profiles, having relative thicknesses, respectively, 7, 12 and 20%; 5 shows the middle lines of four profiles, having respectively relative thicknesses A, 7, 12 and 20%; Fig 6 (a, b, c, d) are profiles having respectively relative thicknesses C, 7, 12, and 20%; 7 (a, b, c) are profiles having respectively relative thicknesses of 7, 12 and 20%, each of these three profiles being compared with known profiles; Figure 8 shows the pressure ratio distributions on a profile having a relative thickness of 7% and the pressure distribution distributions on a classic NACA profile 16707 for operating modes during takeoff; FIG. 9 is the same for operating modes during the climb phase; Figure 10 is the same for operating modes during cruising; 11 shows changes in the aerodynamic quality coefficient as a function of the lift coefficient during ascent and cruising, however, these changes are presented for a profile having a relative thickness of 7% and for a classic NACA profile 16707; Fig. 12 is a graph showing the change in the maximum lift coefficients of a profile having a relative thickness of 1% and a classic NACA profile 16707; Fig. 13 is a graph of change.
five
0
Coefficients of frontal resistance of a profile having a relative thickness of 1% and a classical profile of NACA 16707; in fig. And, the values of the maximum lift coefficients for profiles having, respectively, relative thicknesses C, 7, 12 and 20%, compared with the characteristics of the classic NACA profile 16707, during takeoff; in fig. 15. - the same during the climb; on Fig - the same, during the cruise flight.
The profile of the propeller blade of the aircraft has a relative thickness, referred to k.horda, concluded in the range between 3 and 25%. The back 1 of this profile has a convex shape between the front edge A and the rear edge F. The lower contour 2 of this profile has a shape first convex from the leading edge A, then concave at the approach to the trailing edge F.
The law of curvature change of the back 1 is as follows: the curvature, maximum on the leading edge A, decreases firstly rapidly to a value equal to approximately k at point B located on
 distance approximately% of chord length; then the curvature becomes zero,
The law of curvature change of the lower contour 3 profile is the following: curvature, maximum at the leading edge
5 Af first decreases rapidly to a value of approximately 8 at a point located at a distance of approximately 3.5% of the chord length; then the curvature decreases more slowly to zero at point E, which is between 10 and 60% of the chord length.
Further, the curvature decreases from this inflection point to a small negative value, which remains almost constant to the rear. edges F
five
0
five
 This law of curvature variation is represented in Fig. 2, where it is shown: along the abscissa and in the positive direction — the relative length X of the profile chord, represented as (X / L); on the abscissa axis in the negative direction - relative length X of the profile chord, represented as (X / L) 4; the y-axis is positive and the curvature is negative,
represented as C
Ml
The curve in the positive direction of the x-axis represents the change in the curvature of the back, and the curve in the negative direction of the absorbent axis represents the change in the curvature of the lower contour of the profile.
At the level of point B on the back there is a zone of conjugation of the curves of the curve (section В В), which passes by a relative distance of 2% on both sides of point B, and over which the curvature of the backrest varies slightly (points B and 8, therefore, are respectively about 2 and 6% of the chord length).
At the level of point D on the lower contour of the profile there is a zone of conjugation, which passes at a relative distance of 2% on both sides of this point D and over which the curvature of the profile varies only slightly. Points D and D, therefore, are respectively approximately 1.5 and 5.5% of the chord
The level of point E is not the inner surface, a zone of junction E E is provided, passing at a relative distance of 2% on either side of this point E, and over which the curvature of the inner surface varies slightly.
Point E is located on the abscissa X, referred to the chord L and defined by the equation X X / L 2 (e / L) + 0.08.
The curvature of the Smds profile at the leading edge A is determined by the equation
 Max
a (e / L) -a2 (e / L) +
+ a
3 (e / L))
where e is the thickness of the profile;
L а а „chord profile;.,
coefficient equal to + 2 "10;
coefficient equal to -, 576 | 4.
H
ten ,
a factor of + 3,
a - coefficient equal to - 8.5 "Ann
To build profiles, mathematical dependencies are given that define the average line of the profile and the thickness of the profile, located on either side of the middle line, perpendicular to the middle line.
For this, a rectangular coordinate system is used, so far, in the figure 1, on which the chord, the profile coincides with the axis 0
, In this coordinate system, where I abscissas X and ordinates Y are correlated
five

.
15
20
25
with the length L of the chord, the average line and the law of variation in the thickness of the profile are represented by mathematical dependences,
 The average line is represented as
Y ((X / LrZ + a (X / L) +. F + aЈ (X / I,) + a9tX / t) 3 + a4 (x / L)).
. The coefficients a0, a, a, a., A4 and a c have the following values in the range of relative thicknesses, concluded between 3 and 25%, 2G56 (e / L) -110 (e / L) 2+
+ Ш8.7 (еЛ,) з-2751.7 (е / ЬГ; a4 n, 537 (e / L) +500.8 (e / L) 2- –J 851,) + 13309 {e / l, ) "}
a, -1.236 (e / L), 27 (e / L) 2+ +2803 (e / L) 3-8315.2 (e / L) 4 $
aj 38.5 (e / L) -1t5M (e / L) 2+ +9988.3 (e / b) s-25693 (e / L) 4;
, 99 (e / L), 7 (e / L) 2-13768 (e / L) 3 + 35952 (e / L);
, (e / L) - 540,) 2+ y797.5 (e / s) s-124b7 (u, g.
The law of thickness variation is represented by Y (y / L) b, (X / Lr + b "(X / L) + + b, (X / L) 2 + b3 (X / L) 3 + b4 (X / L) 4 + bЈr (X / L).
The coefficients ba, b, b., B., B4 and bg- have the following values in the range of relative thicknesses between 3 and 25%:
, (e / L) -59, l6 (e / L) 2-b
 + 512, J3 (e / L) 3-i320, Me / L) 4;
35 b, -12.3 Me / L) +358.32 (e / L) 2-3097, 1 (e / L) 3 + 8017.9 (e / L) 4;
, 71 (e / L), 2 (e / L) 2+ + 132Q2 (e / L) (e / L);
, 88 (e / L) + 3o87. (E / L) 2 "-26339 (e / L) 3 + 67587 (e / L)
b4 93159 (e / L) -27H, 7 (e / L) 2+
+ 232b8 (e / L) 3-593foMe / LF;
bf-30.96 (e / L) +896.5 (e / L) 2
–7539.8 {e / L) 3 + i9093 (e / L),
The figure shows the curves, showing the change in the relative thickness of the profile e / L) along the chord, that is, depending on the abscissa (X / L),
Curves I, II, III, IV correspond to profiles of relative thickness, 1, 7, 12 and 20%,
Figure 6 shows the middle lines I, II, III, IV, corresponding to jj profiles of relative thickness 4, 7, 12 and 20%, while the coordinates used in figure 5 are abscissas (X / L) and ordinates (Y / L), chordized profile 0
thirty
45
50
717
The transfer on both sides of the midline and perpendicular to it the law of thickness, is thus obtained, the coordinates of the profiles according to the invention.
Figure 6 (a, 6, c, d) shows profiles, respectively, for values of the relative thickness C, 7, 12, and 20Јo
Fig. 7 (a, b, c) shows the differences between the profiles according to the invention and the classical profile m.
Fig. 7a shows in solid lines a profile having a relative thickness of 7%, and dashed lines show a classic profile of the type NACA 16707 with the same relative thickness of 7%.
The profile is presented in solid lines, having a relative thickness of 12%, and the dotted lines are a classic profile of the HSI-712 type with the same relative thickness of 12%.
Fig. 7c shows solid lines with a profile having a relative thickness of 20%, and dotted lines show a classic ARAD 20 type profile, with the same relative thickness of 20%.
A change in the curvature of the back between points A and B makes it possible to reduce in absolute value the coefficient of minimum pressure, related to the back, relative to the corresponding pressure coefficient of the classical profile type NACA 1b "
This is shown in Fig. 8, where the X / I value is plotted along the abscissa, and the distance coefficient Kp is plotted along the ordinate axis.
This figure shows the operating mode in the take-off phase, with the solid line curve corresponding to the profile according to the invention with a relative 1% HOR 07, and the dotted curve to the classical NACA profile 16707.
Operating modes related to the take-off phase correspond to a Mach number close to 0.55 and an increased lift coefficient.
The conjugation zone B, in which the curvature changes little, makes it possible to obtain, at the same operating conditions, the phenomenon of isentropic increase in the flow pressure, which makes it possible to limit the intensity of the shock wave at the back level and, consequently, to obtain higher values for
08ъ
maximum lift coefficient
Fig. 9 is represented under the same conditions as in Fig. 8, the change {
pressure ratio during climb operation.
The change in curvature in the back, enclosed between point B and
. trailing edge F allows a gradual increase in flow pressure to the trailing edge for any flight conditions, and especially during ascent. This pressure increase is very weak towards the trailing edge where the boundary layer is thick and has therefore Greater sensitivity to the effects of pressure.
0 This increase in pressure also avoids breakdown of the boundary layer and yields good aerodynamic quality coefficient values that are of interest.
5 during takeoff and climb,
Fig. 10 shows, under the same conditions as in Fig. 8, a change in the pressure ratio during cruising flight operating conditions.
A change in the curvature of the inner surface between points A and D makes it possible to obtain very small values of the pressure coefficient and, in any case, well below the absolute values obtained with the help of classical profiles.
The change in curvature between points D and E is the same as in the opposite zone 0
0
g / n
Nor does irD allow the increase in flow pressure to avoid the occurrence of shock waves.
A change in the curvature of the inner surface between point E and the trailing edge allows for a slight acceleration of the flow after the appearance of an increase in pressure to the rear crust. i
A change in the curvature of the lower profile contour allows flow control, which gives the profile good aerodynamic quality values during cruising.
Comparative tests carried out under the same conditions of the profiles according to the invention with relative thickness k, 7, 12 and 20% and with the NACA profile 16707 confirmed the high performance of the profiles according to the invention with respect to the mentioned NACA profile.
 9
In Fig. 11, the aerodynamic coefficient f Cr / C is plotted along the abscissa axis, where C-Ј is the lift coefficient, and C is the drag coefficient, and along the ordinate axis is the lift coefficient C,
Two curves I and II characterize the profile according to the invention with a relative thickness of 7%, corresponding to the operating conditions during climb (curve I) and in cruising flight (curve II).
Two curves I and II characterize the NACA profile, respectively, when climbing (curve I) and in cruising flight (curve II), respectively.
In Figs 12 and 13, the Mach numbers are plotted on the abscissa, and the ordinate on Fig. 12 is the maximum lift coefficient (C / cx), in Fig. 13, the drag coefficient (Cx).
In Fig. 12, curve I refers to a profile according to the invention with a relative thickness /, and curve II refers to a profile of NACA 16707.
In Fig. 13, curve I refers to a profile according to the invention with a relative thickness of 1%, and curve II refers to a profile of NACA 16707.
In this FIG. 13, the drag curves versus the Mach number are taken for a lift coefficient of approximately 0.5.
In FIG. 12, the Mach numbers are characteristic of the speeds encountered during operating modes during takeoff, and in FIG. 13, the Mach numbers occurring during operating modes of cruise flight.
As can be seen from the graphs, the gain of the maximum lift coefficient is 15% for a Mach number of 0.55. In this case, the drag coefficient is much lower than the drag coefficient of the NACA profile for any Mach number.




five
0
608
ten
five
0
In these figures, the curves are constructed from four operating points correspondingly to the profile m according to the invention with a relative thickness of 4% (point HOR 04), 7% (point HOR 07), 12 (point HOR 12) and 20% (point HOR 20) about
In these figures, the point represented by the cross corresponds to the NACA 16707 profile.
These figures clearly show that for all operating modes (during take-off, climb and in cruise flight), the characteristics of the profiles according to the invention are higher than those of the classical profiles.
Tables can also be used to build profiles according to the invention. 1 - 4 coordinates, referring to profiles m with relative thickness C, 7, 12 and 20%, in which the coordinates assigned to the chord, i.e., are given for the back and for the lower contour of the profile. (X / L) and (Y / L) in the rectangular coordinate system O, OQ (Fig. 1), on which the chord coincides with the axis Od for the points located on the back and on the lower contour of the profiles.
TaBl01 (LJ 04) characterizes a profile with a relative thickness of 4% "
Table 1 HOR 04

35
40
45
FIG. And, 15 and 16 are plotted on the abscissa axis of the Mach number, corresponding to the cruising flight, and on the axis of the ordinate in Fig. 14 - the maximum lift coefficient of the profile during takeoff, in FIG. 115 is the coefficient of aerodynamic quality when climbing, in FIG. 16 is the coefficient of aerodynamic quality during cruising m flight.
50
55
eleven
Continuation of table 1
17 41608
12 Continued table. 2
13
HOR 12
Table3
one
15
Continuation tabj 4
The curvature of the upper profile contour in the vicinity of point B, located at a relative distance equal to Ц% chord, varies very little, depending on the profile thickness (e / L) in the area from point B located at a distance of 2% chord to point B, the curvature of the upper contour is determined by the equation
H -287.91 (e / L) -5l72, l (e / L) 2+ +3959 4 (e / L) 3-93582 (e / L) 4, and in the area from point B to point B. located at a relative distance of 6% of the chord, the curvature of the upper
the contour is defined by the equation C 71,595 (e / L) -1193.3 (e / L) 4 + 10Ь61 {e / L). s-300 8 (e / L).
Curvature of the lower contour of the profile in. vicinities of point D, located at a relative distance of 3, the chord, varies very little, and depending on the relative thickness of the profile e / L in the area from point D, located at a distance of 1.5% of the chord, to point D cree30
7 L608tb
lower contour visibility is defined by the equation
Cl, 62 (e / L) -17922 e / L) + 5 - AND 50080 (e / L) 3-388830 (e / L) 4,
and on the section from point D to point D located at a relative distance of 5.5% of the chord, the curvature of the lower contour to the profile is determined by the equation
Yu
Sdu -93,), 5 (e / L) 2-40076 (e / L) -I 06020 {e / L).
The blade in the range of lengths from 0.20N to Q, 35R is formed by profiles with a relative thickness of 20%, and in the range from 0.65R to 0.75R - by profiles with a relative thickness of 12%.
The blade in the range of lengths from 0.20R to 0.3 $ R is formed by profiles with a relative thickness of 20%, in the range from 0.35R to 0.35R — profiles with a relative thickness of 12%, in the range from G.55R to 0,70R - profiles with a relative thickness of 7% and in the range
25 from 0.80R to 0.95R — profiles with relative thickness%.
For a blade that has a span of R according to the invention, it is preferable to carry out blade profiles that are in the range between 0.2 K and R.
five
0
five
0
five

权利要求:
Claims (4)
[1]
Invention Formula
1. The propeller blade of an aircraft, having an aerodynamic profile in section, the relative thickness of which is 3-25%, formed by the upper convex contour and the lower convex-concave, convex at the leading edge and concave at the trailing lower edge, while the said contours the profile of the blade is asymmetrical with respect to the midline and the chord of the profile, characterized in that, in order to improve the screw performance characteristics by delaying the formation of shock waves and tearing off the boundary layer with increasing major Mach numbers, the curvature of the upper convex contour monotonously decreases in the direction of the trailing edge of the profile, reaches 4% chord and 0 at the trailing edge, and the curvature of the lower convex-concave contour of the profile also monotonously decreases in the direction of its trailing edge, reaches b by 3.5% of the chord of the magnitude O at a distance of 10 - 60% of the chord, depending on the radius of the blade section and then monotonously decreasing, reaches a negative value of -0.5 remaining constant to the trailing edge of the profile
2. The blade pop. 1, differs from the fact that the curvature on the leading edge of the profile is determined by the equation
[2]
CMeKc
.
(e / L) - if576-10 (e / L) 43.5-105 (e / L) 3-8, (e / L) 4,
where e is the thickness of the profile; L - chord profile
3. The blade popl, due to the fact that the point of the chord of its profile, where the curvature of the lower contour is zero, has an abscissa X, referred to the chord of the profile defined by the equation
[3]
(e / L) + 0.08.
4. The blade pop. 1, I differ from the fact that its average line is determined by the equation
[4]
Y Y / L Q0 {X / L) +0 (X / U ×
where Qe-3, 2056 (e / L) -110 (e / L) 2+ f10l8.7 (e / L) 3-275U7 (e / L) 4;
-4851, 6 (e / L) 3rd 33U9 (e / L) 4;
 , 286 (e / L) -242.27 (e / L) 2+ + 28-03 (e / L) 3-8315.2 (e / L) 4; 2
, 5 (e / L) -11 $ 4,) +9988.3 (e / L) 3-25693 (e / L);
, 9 (e / L) +154 7.7 (e / L) 2--13768 (e / L) 3 + 35952 (e / L) 4;
, 546 (e / L) -540.04 {e / L) 2+ +4797.5 (e / L) 3-i2467 (e / Lr; and the law of thickness variation is expressed by the equation
(X / L) f / Z + b, (X / L) + (X / L) + b 3 (X / L) where, We / L) 59, l6 (e / L) 2+
b, -12.3 (e / L) +358.32. (e / L) 2 - 3097.1 (e / L) 3 + 8017.9 (e / L);
, 88 (e / L) +3087.6 (e / L) 2 -263 jy (e / L) 3 + 67587 (e / L) 4;
+ 2326b (e / L) 3 -59364 (e / L) 4;
bfi- 30.96 (e / L) + 896.5ie / L) a5. The blade according to claim 1, wherein the profile having a relative thickness of k% determines with the relative values of the coordinates X / L and Y / L for the inner surface and the back of the profile shown in the table: iHOR 04
ten
15
20
thirty
35
40
4S
50
55
19 m
Table continuation
&. Joining Pot1, from the fact that the profile, having a relative thickness of 1%, is determined by the relative values of the coordinates X / L and Y / L for the internal surface and the back of the profile shown in the table:
HOR Oh
1608
20 Continuation of the table
25
7. A blade as claimed in claim 1, characterized in that the profile having a relative thickness of 12% is determined by the relative values of the coordinates X / L and Y / L for the inner surface and the back of the profile given in the table:
HOR 12
ABOUT
FIG. one .
01U035 F
FIG. four
I jl
rv
GO trt
00
oh oh
Jt
GSh O4
V-w
"Ci
I
a
a
t "
SU
Si
A
&
s
eight"
X
O4
WITH
cc
50HOR12
HOR20
0.5 0.6. 0.7 0.8 Thebes. sixteen
HQR07 HOR04
MLSL 16707
0.9 M

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同族专利:

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EP0227524B1|1991-12-27|

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法律状态:

优先权:

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申请号 | 申请日 | 专利标题

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FR8517080A|FR2590229B1|1985-11-19|1985-11-19|IMPROVEMENTS ON AIR PROPELLERS WITH REGARD TO THE PROFILE OF THEIR BLADES|

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