CN1042692A - The properller leaf of counter-rotating - Google Patents
The properller leaf of counter-rotating Download PDFInfo
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- CN1042692A CN1042692A CN89103688.1A CN89103688A CN1042692A CN 1042692 A CN1042692 A CN 1042692A CN 89103688 A CN89103688 A CN 89103688A CN 1042692 A CN1042692 A CN 1042692A
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- 239000002131 composite material Substances 0.000 claims abstract description 28
- 239000006260 foam Substances 0.000 claims abstract description 19
- 238000000034 method Methods 0.000 claims description 55
- 239000000463 material Substances 0.000 claims description 30
- 239000000835 fiber Substances 0.000 claims description 27
- 239000000853 adhesive Substances 0.000 claims description 12
- 239000011888 foil Substances 0.000 claims description 5
- 150000001875 compounds Chemical class 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 claims description 2
- 239000006185 dispersion Substances 0.000 claims 4
- 238000010438 heat treatment Methods 0.000 claims 2
- 230000001070 adhesive effect Effects 0.000 claims 1
- 230000001681 protective effect Effects 0.000 claims 1
- 229910052751 metal Inorganic materials 0.000 abstract description 6
- 239000002184 metal Substances 0.000 abstract description 6
- 239000010410 layer Substances 0.000 description 17
- 229920005989 resin Polymers 0.000 description 4
- 239000011347 resin Substances 0.000 description 4
- 230000003068 static effect Effects 0.000 description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000003822 epoxy resin Substances 0.000 description 2
- 239000003733 fiber-reinforced composite Substances 0.000 description 2
- 230000014509 gene expression Effects 0.000 description 2
- 239000003365 glass fiber Substances 0.000 description 2
- 239000002648 laminated material Substances 0.000 description 2
- 229920000647 polyepoxide Polymers 0.000 description 2
- 238000013517 stratification Methods 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- 229910052719 titanium Inorganic materials 0.000 description 2
- 238000005303 weighing Methods 0.000 description 2
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 229920000271 Kevlar® Polymers 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- -1 blade beam Substances 0.000 description 1
- 229910052796 boron Inorganic materials 0.000 description 1
- 238000007598 dipping method Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 229910002804 graphite Inorganic materials 0.000 description 1
- 239000010439 graphite Substances 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000004033 plastic Substances 0.000 description 1
- 230000001012 protector Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/20—Constructional features
- B64C11/26—Fabricated blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Moulding By Coating Moulds (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Invent a kind of properller leaf, it is made up of the shell of two composite lay, is bonded with a metal blade beam between two shells, and desired position is placed with the foam stuffing part between two shells.Yet blade is carried out radially and tangential balance.
Description
The invention relates to aircraft propelling system, specifically about mainly with the sweepback of composite material manufacturing height, wide chord of foil, as thin as a wafer the method for screw blade.
In the past, properller is made with structural materials always basically.These materials are only improving aspect one of them important structural behaviour parameter such as intensity or rigidity, and this has just lost the potentiality that they can be expected.These materials comprise steel, wood, aluminium and titanium etc.Because these shortcomings, aircraft industry has produced great interest to adopting advanced fiber reinforced composite.Suitably use these materials, can obtain higher intensity, and the structural weight of blade can reduce 50% more than.
The aircraft blade that the present invention considers uses in the propeller system of a counter-rotating, and there are a front propeller and the after screw with counter-rotating of 5-15 blade with 5-15 blade in this system.These blade height sweepback, chord of foil are wide, very thin.The aerofoil profile of screw blade is with transonic and hyprsonic work.
Screw blade design in the past is suitable for subsonic flight.Yet when these blades were used in high-subsonic flight, many structure problems caused its performance decrease.The structure problem that is operated in very high-revolving blade is because the power and the stress that act on the blade cause.The power that acts on the blade in-flight is thrust, centnifugal force and torsion.At first, thrust produces flexure stress at blade.The second, centnifugal force makes blade produce radial drawing.Last torsion makes blade reverse around its radial axle.Desirable blade has overcome these power, has reduced effective fuel discharge.
One of way that solves the blade problem is the bonded assembly structural composite material of exploitation fiber-reinforced resin.These materials have increased the new alerting ability of propeller design.Use fiber reinforced composite three major advantages are arranged.The first, can make complicated airfoil structure.The second, but the composite material expendable weight.The 3rd, the dynamic frequency response of blade element can be special for the working parameter that is fit to it.The present invention for the propeller system that reverses provides the actv. blade, has overcome the problem and the shortcoming of blade in the prior art by making blade with composite material, making blade have intensity and airfoil structure.
The purpose of this invention is to provide a kind of actv. screw blade made from the bonded assembly structural composite material of unidirectional ply fiber-reinforced resin.And a kind of properller leaf of counter-rotating is provided, this blade has overcome power and the stress in the blade high speed operation.
Another object of the present invention provides a kind of counter-rotating properller leaf that improves counter-rotating propulsion system efficient.
The present invention also have another purpose provide a kind of radially with tangential balance, with the blade of the flexural load that reduces system vibration and leaf root part.
In a word, this properller leaf includes the composite layer of some tiltedly folded (angle plied).These composite layers form the one the second shells.The one the second shells all have crossing at leading edge, trailing edge, root and blade tip.Leading edge and trailing edge are sweepback, with noise and because the aerodynamic losses that the compressibility influence of air produces that reduces tip segment.Between the one the second shells, be stained with a metal spar, to improve surperficial rigidity.Done the hole between two surfaces, to alleviate the weight of blade.Counterbalanced weight before and after the blade beam of adjustable positions can make blade obtain radially and tangential balance.
Blade is to be made of the blade model that provides.This blade model all has the equal thickness district of a blade cross-sectional plane to each case surface.Composite material is made the shape of model.First shell is that the composite layer with some moulding gathers into folds and makes.Composite material comprises that some are filled in the unidirectional fibre in the low modulus basis material.Each layer fiber arranged with different directions, to obtain the strength and stiffness of blade.Second shell constitutes in a similar fashion.The blade beam is fixed between the one the second shells.Then foam stuffing is placed preposition, between shell, to form the hole.In the inside face of blade beam, shell and foam-filled material, add adhesive agent.Suitable cure cycle according to the low modulus basis material is cured in autoclave then, and adhesive agent, blade beam, shell and foam stuffing are bonded together.And then utilize fastener that shell, blade beam and foam stuffing are pressed together.At last blade is carried out tangential and radial balance, with the vibration that reduces system and the flexural load of propeller shank.
Other purpose of the present invention and intrinsic advantage thereof have the relevant explanation of accompanying drawing below, and it is clearer to become.Wherein:
Fig. 1 illustrates the contrary turning propeller system that adopts blade of the present invention.
Fig. 2 explanation comprises the airfoil portion of the preceding blade of blade beam and fastener.
Fig. 3 illustrates the each several part of back blade, comprising front and rear surfaces, front and rear edge, blade tip, overview and blade beam,
Fig. 4 is the view of blade beam, and its front and back depression and counterbalanced weight is described.
Fig. 5 illustrates the blade model, and it has the equal thickness district of the cross-sectional plane of one first shell.
Fig. 6 illustrates the blade model, and it has the equal thickness district of the cross-sectional plane of one second shell.
With shell, blade beam, foam stuffing and adhesive agent compress to constitute the method for blade in mould in Fig. 7 explanation.
Fig. 8 illustrates that the blade overbalance causes system vibration.
Fig. 9 explanation is at the radial balance blade.
Figure 10 illustrates at chord of foil to the balance blade.
Fig. 1 illustrates a contrary turning propeller system of the present invention.Generally speaking, first screw propeller 100 comprises preceding blade 106, and it rotates with 102 directions, and after screw 104 comprises back blade 108, and it is with reversing sense 105 rotations.All blades on the front propeller 100 all are identical, and all blades on the after screw 104 also are identical.The size of preceding blade and back blade differs from one another.The US Patent that structure is disclosed on February 12nd, 1988, application number is S/N 157179 of blade is existing before and after the representative type introduces it and is entitled as " the properller leaf of counter-rotating ", this patent be on September 19th, 1986 open, application number be S/N 932427, the part continuation application of existing obsolete US Patent, for the purpose of reference, to mention it sometimes.
Referring to Fig. 2, preceding blade 106 has an airfoil portion 310, and it comprises blade tip 312 and leaf root part 302.Airfoil portion 310 comprises what front surface 309 between blade tip 312 and leaf root part 302 and rear surface 307(hid), the surface is made of long stapled tiltedly folded composite beds that some are filled in the basis material.Intersect at the trailing edge 316 of converx leading edge 314 and matrix front surface 309 and rear surface 307, forms a kind of swept-back blade that radial axle 322 is as shown in Figure 2 arranged.Front surface 309 is protruding, and the rear surface is recessed.Two shells form the surface.Metal blade beam 318 in the surface is inserted between front surface 309 and the rear surface 307 and is glued on two shells, the surface is connected to root 302.The foam-filled preceding depression 324 and the adjacent leading edge of beam 318.Foam-filled back pocket 326 is adjacent with the trailing edge of beam 318.The leading edge of blade 106 is equipped with skins front edges (sheath) 311 to prevent etch.Surface, shell and blade beam are installed with one or more fasteners 320, disintegrate under heavy duty to prevent blade.The leading edge and the trailing edge of some fastener and blade beam are adjacent, so that surface pressure is tightened on the blade beam.
Referring to Fig. 3, it is that back blade structure is described.Generally speaking, in that back blade 108 is similar to preceding blade 106 in shape.Back blade 108 has an airfoil portion 410 that comprises blade tip 412 and leaf root part 402.Airfoil portion 410 comprises what front surface 409 between blade tip 412 and leaf root part 402 and rear surface 407(hid), it is made of the long fiber composites layers that are filled in the basis material of some tiltedly folded (angleplied).The long fibre of composite bed extends whole aerofoil.Intersect in convex leading edge 414 and spill trailing edge 416 front surface 409 and rear surface 407, is formed with the sweepback blade of radial axle 422, as shown in Figure 3.Front surface 409 is protruding, and rear surface 407 is recessed.Two surfaces form a shell complex.Metal blade beam 418 in the complex is embedded between front surface 409 and the rear surface 407, and utilizes the bonding material of structure, as the AF 3109-2K bonding material that utilizes 3M company to produce, and beam is bonded on the shell.People it should be noted that, blade and back blade before adhesive agent is used for boning.Foam-filled preceding hole 424 is adjacent with the trailing edge of beam 418.The skins front edges that is connected to leading edge 411 shields.Shell and beam embed that to have fastener 420 to carry out clamping tight, in case blade disintegrates.Shell and blade beam are compressed with second group of fastener in the place that is close with the blade beam.
Before each, back blade constitutes by unidirectional fiber layers.That fiber is that unidirectional, flat raft is filled in abreast is plastic, in the low-intensity, low horizontal amount basis material.This material can pass to load fiber and the load of inefficacy fiber end can be re-assigned to adjacent fiber from fiber by shearing, and the effect that the single fiber inefficacy is produced is restricted.The typical fibers of using in the present invention's practice is the composite material of 80% graphite and 20%S-glass fibre.Yet, can use many kinds of fiber combinations, comprise fiber, natural boron fiber and glass fibre combination as Kevlar.
Though the preceding blade of concrete reference illustrates in the introduction of the present invention of back, just is appreciated that in the beginning that illustrates, then also plan apparatus and method of the present invention are used on the blade of back.And every layer or layer combination can be with more than a kind of fiber.
Lamination (lamimate) is used the multi-layer fiber stratification.Every layer of fiber and 322 one-tenth of longitudinal axis+80, the staggered patterns of+35 ,-10 and+35 degree are arranged.Be to be understood that the angle stratification that two adjacent layers can be identical.But, when changing the angle of one deck, abide by said sequence.Be understood that for a those of ordinary skill, be the composite layer of realizing that the blade all directions all have desired strength characteristics, can change the angle order.
Blade resin dipping strengthens a kind of moving learning of air with good tuned vibration pattern of laminated material (layup) generation and goes up stable blade.Referring to Fig. 4, each blade comprises a center blade beam 318, and it uses high duty metal, and for example titanium is made.Metal blade beam 318 is inserted between front surface and the rear surface by dress and with suitable adhesive agent it is bonded on each surface.Adhesive agent provides extra bond strength, prevents that blade from disintegrating.Blade beam 318 has also improved blade rigidity and the transmission medium that load is passed to the root that comprises dovetail form tenon (not shown) from aerofoil is provided.As everyone knows, the dovetail form tenon locks onto beam on the rotating hub.
One of many functions of beam 318 are that blade and rotating hub are linked up.Shown in 304 and 306 dotted lines, beam has the hollow hole that falls in.It is in order to hold counterbalanced weight, to the static balancing of blade around longitudinal axis 322 and tangential axis that this depression is set.Front-axle beam depression 304 includes one and is limited to the counterbalanced weight 340 that moves in the groove 341.Because mould 341 and longitudinal axis and tangential angle is arranged all, so counterbalanced weight 340 includes along component motion tangential and radially.In addition, the back balances in the groove 346 weigh 342 tangential and a component motion radially also arranged.
Forward horizontal stand weigh 340 and back balance weigh 342 place respectively before in depression 304 and the back pocket 306.It is radial balance and tangential balance in order to realize blade that counterbalanced weight moves in groove.This moving can be realized in groove by counterbalanced weight is made screw element.But other way that also can adopt the those of ordinary skill of this professional domain all to know realizes the motion of counterbalanced weight.Also can increase extra counterbalanced weight to realize the bigger mass change of blade.Counterbalanced weight mainly is the barycenter or the centre of moment that changes blade.
When making blade, prepare the template of recessed side 501 of blade and protruding side 503, as shown in Figure 5 and Figure 6.With unidirectional, side by side parallel be filled in easily mould, the fibrage of low-intensity, low modulus basis material is laid on the template and be cut into the shape of this layer template.The low modulus basis material that uses in the present invention's practice is an epoxy resin.Referring to Fig. 5 and Fig. 6, they show the template of recessed side of blade and protruding side respectively.These contour representations the equal thickness district of each areal cross-section of blade.Say that in essence these profiles are consistent with the template of a single layer fibre material.For example, line 500 is represented the template of blade penetralia fire, and the outer template of line 502 expression blades.When making blade, with unidirectional, parallel being filled in easily moulded low-intensity, the low modulus basis material is laid on the template and is cut into the shape of template along predetermined machine direction side by side.In practice of the present invention, be with 322 one-tenth of longitudinal axis+80 ,+35 ,-10 ,+35 the degree staggered template fiber arranged.The two halves of blade or two surfaces are will whenever gather into folds layer by layer each other to constitute.Because the epoxy resin-impregnated layer is heavy-bodied, each layer can be adhered to one another.Like this, the shape of blade just is made up of two halves or two shells, and one forms nonreentrant surface, and one forms recessed surface.
Referring to Fig. 7, first shell is introduced in the mould 510, has preform like this to this shell shape.Paddle beam 318 is ways of utilizing general relevant those of ordinary skill all to know, utilize blade beam 318 is pressed in the aligning guide on the mould, with its radially axis 322 aim at.The leading edge depression is to place the nearly blade beam of dust 318 leading edge places to form by the foam element 512 with a depression type.The trailing edge depression is to place with close blade beam 318 trailing edge places by the foam element 514 with a depression type to form.Every side at beam 318 is additionally added some adhesive agents, so that reliably the blade beam is fixed on first shell 502.Aim at and be enclosed in the mould with second shell, 503 location and with first shell, blade beam and foam stuffing.According to the cure cycle of the epoxy resin that uses in making, the temperature that mold heated to is predetermined also is incubated a preset time.Blade is cooled off from the mould taking-up.Unnecessary resin is all trimmed from blade edge and root.Those of ordinary skill to this professional domain is known, and the leading edge protector is fixing with the vacuum bagging method.Then, fastener is fixed to another surface by blade from a surface,, prevented that the blade element from separating under loading to obtain extra intensity.Certainly, other method that has quite a lot of desirable making composite structure.Producing the method for making of a large amount of blades will utilize automatic technology to finish.But obviously, automatic technology will be abideed by the method for discussing above fully.
Blade will carry out static balancing to two axiss of torque after making.It is minimum that the rotation imbalance that the centre of moment because of unregulated revolution blade will be caused reduces to.For example, explanation two blades rotate around line of centers 12 among Fig. 8.If the centre of moment of blade 24 22 does not align radial and axial with the centre of moment 25 of blade 26, will cause the revolution overbalance.For example, radial distance 28 radially overbalance will occur greater than radial distance 30.Equally, if two blades do not align at same axial location, also can produce overbalance.Axial location is defined as and crossing axis (line of centers 12) position of the vertical line that passes through the centre of moment.Any overbalance all can produce the vibration of propeller system, causes loss in efficiency, perhaps under extreme case, can destroy propeller system.Therefore, in order to reduce vibration, this rotation imbalance (MW
1-MW
2) want minimum.MW wherein
1Be the quality and weight (Fig. 8) of first blade, MW
2It is the quality and weight of second blade.
In order to eliminate these problems, blade is wanted balance at radial and axial (tangential).Primary shaft is a radial axle, and second is chordwise axes.Referring to Fig. 9, blade is clamped by a weighting apparatus 10.This weighting apparatus can be a kind of simple balance Weighing apparatus, and it has the weights 12 and a scale of measuring blade weight that will install zeroing.At first measure the deadweight of blade with well-known mode.
Determine the square heavy (moment weight) of radial axle then.Radially square heavily equals WX
1, W is deadweight (pan weight), X
1Be the distance of fulcrum to the centre of moment 32.Square heavy (moment weight) is by scale 14 expressions.Because radially square weight and deadweight are known, so X
1Can determine.So X of some blades on the propeller
1Can determine that wherein I is represented an I blade.Next step is the distribution of determining the tangential square distance of screw blade.
Referring to Figure 10, adopt same Weighing apparatus 10 to determine tangential square.Blade is rotated 90 degree, make it to determine the axial location of the centre of moment 32.Tangential square heavily equals WY
1, wherein W is the deadweight of blade sheet, Y is the axial location of the 1st the blade centre of moment.Axial location Y can heavily change by mobile anterior-posterior balance.For one group of blade, select a predetermined Y
1Revise each blade then, make each blade of axial location of the centre of moment all identical.This is heavily to realize adjusting Y by anterior-posterior balance is carefully located, added and subtracted to every blade
1.Blade after the overbalance correction makes the axial location of the centre of moment identical, the radial position of calibrating the centre of moment then.This work is by keeping under the axial location unmodified situation of the centre of moment, the weight of root added and subtracted finished.For example, suppose root is increased two ounces of Lu, heavily increase by one ounce, back balance is heavily increased by one ounce to forward horizontal stand.With the method,, change the radial position of the centre of moment keeping centroidal axis under the invariant position situation.The applicator finds that this diaxon (two coordinate) static balancing method can obtain to rotate enough dynamical equilibriuies of blade.
Like this, just illustrated that structure has the method for the counter-rotating properller system of height sweepback, wide chord of foil, very thin blade.Blade is made by two shells that a kind of compound laminated material constitutes.This composite laminates is made of the unidirectional fibre that some are filled in the low modulus basis material.The blade beam assigns between two shells.Add that between blade beam and shell adhesive agent is to improve bond strength.Foam stuffing is placed desired location between two shells, to form the hole in the blade.Suitable cure cycle according to basis material utilizes the autoclave cured method, and shell, blade beam, foam stuffing and adhesive agent are bonded together.The fastener of nut, bolt and so on is connected by blade,, blade still is fixed together under loading so that added strength to be provided.Leading edge is loaded onto skins front edges with the protection leading edge.
Such scheme only illustrates a kind of embodiment of the present invention, concerning the people who is familiar with this professional domain, can make amendment to it.Therefore, the present invention is not confined to embodiment described here, but the scope of claims defined of being applied for limits.
Claims (24)
1, a kind of method of making blade with composite material, composite material have be filled in easily mould, in the fiber of the unidirectional high-modulus in the basis material of low-intensity, low modulus, this blade is included in first second surface that blade tip and leaf root part sweepback leading edge and sweepback trailing edge intersect, and blade also comprises the blade beam.This method comprises the following steps:
(a) make template, the equal thickness district of each areal cross-section of template representation blade;
(b) according to template with composite material forming, to form first and second shells;
(c) stationary blade beam between the one the second shells.
(d) foam stuffing is placed into a desired location, so that between shell, form depression.
(e) according to the suitable cure cycle of low modulus basis material, to the blade heating, make blade beam, foam stuffing, first and second shells bond together.
2, method according to claim 1 is characterized in that: adhesion step wherein (e) also comprise with adhesive agent be applied to the inner face of blade beam, foam stuffing and first and second shells, with the step of the globality that keeps the blade structure.
3, method according to claim 1 is characterized in that: this method also comprises the blade beam is clamped between first and second shells, reverses or break away from the step of shell to prevent the blade beam.
4, method according to claim 1 is characterized in that, this method also comprises such step: one or more fasteners is inserted the one the second shells by the blade beam, so that the blade beam is fixed on the shell.
5, method according to claim 4 is characterized in that, this method also comprises such step: with one or more fasteners inserting in the shell, so that between beam and shell, obtain the globality of structure with the contiguous position of the trailing edge of paddle beam and leading edge.
6, method according to claim 5 is characterized in that, this method also comprises the step of loading onto a leading edge protective cover along the paddle leading edge.
7, method according to claim 5 is characterized in that, blade wherein also comprise can radially with the tangential first and second mobile counterbalanceds weight, counterbalanced weight is to move for the centre of moment of determining blade.This method also comprises the following steps:
(f),, make the centre of moment by adjusting the one the second counterbalanceds weight in the first tangential desired location;
(g) with radially second desired location,, make the centre of moment by revising first and second counterbalanceds weight.
8, method according to claim 7 is characterized in that: this method also comprises the following steps:
(h) in the tangential centroid position of measuring one group of blade;
(i) centroid position of the tangential standard of selection is to reduce the dispersion of centroid position;
(j), make the centre of moment of each blade according to the centroid position of standard.
9, method according to claim 8 is characterized in that: this method also comprises the following steps:
(k) position of mensuration radial centroid;
(l) keep under the centroid position unmodified situation in the tangential centroid position with standard, selection one is the standard centroid position radially, to reduce the dispersion of radial centroid position.
(m), make the centre of moment of each blade of one group of blade according to radially standard centroid position.
10, a kind of method that is used to keep composite material paddle structural integrity, this composite material contain to be filled in easily moulds low-intensity, the interior parallel side by side fiber of unidirectional high-modulus of low modulus basis material, and blade is the height sweepback, wide chord of foil and very thin.This method comprises the following steps:
(a) provide first, second shell of blade, each shell is represented blade half, and each shell all has one group corresponding to the composite lay of blade profile and have the fiber that representative is arranged in the composite bed of all directions;
(b) inside face at shell applies adhesive agent;
(c) device paddle beam between first and second shells;
(d) cure cycle predetermined according to basis material by being cured at autoclave or the similar devices basis material to low modulus, bonds together the blade beam and the one the second shells.
11, method according to claim 10 is characterized in that, this method also comprises such step: shell and paddle beam are clamped together, to keep the structural integrity of blade.
12, method according to claim 11 is characterized in that, clamping step wherein comprises: the one the second shells and blade beam are fixed together shell and paddle beam by one or more fasteners.
13,, it is characterized in that this method also comprises such step according to the described method of claim 12: with the contiguous place of paddle beam leading edge, the one the second shells are fixed by one or more fasteners.
14, method according to claim 13 is characterized in that this method also comprises such step: locating with the contiguous of blade beam trailing edge, first, second shell is fixed by one or more fasteners.
15, method according to claim 12 is characterized in that this method also is included in radially the step with tangential balance blade.
16, a kind of method of utilizing the plurality of compound material layer to make blade, each layer all have be filled in easily mould, the fiber of the unidirectional parallel high-modulus side by side in the low modulus, low-intensity basis material.This blade comprises the one the second shells that are made of composite layer, and two shells are before blade tip and leaf root part and band sweepback, and intersect at the trailing edge place, and blade also comprises the blade beam.This method comprises the following steps:
(a) provide a template, the equal thickness district of the cross-sectional plane of every layer of blade of the every shell of template representation for each layer;
(b) according to template forming composite layer, to form first, second shell, each shell is represented blade half;
(c) the blade beam is installed between the one the second shells;
(d) place foam stuffing at preposition, between shell, to form the hole.
(e) give the inner face filling adhesive of blade beam, foam stuffing and first, second shell, to keep the globality of blade structure.
(f) cure cycle suitable according to the low modulus woof, the heating blade, with the blade beam, first, second shell bonds together.
17, method according to claim 16 is characterized in that this method also comprises such step: shell and blade beam are clamped together, to keep the globality of blade structure.
18, method according to claim 17 is characterized in that: clamping step wherein comprises that first shell, blade beam and second shell are passed one or more fasteners is fixed together them.
19, method according to claim 18 is characterized in that this method also comprises such step: at the contiguous place of blade beam leading edge, first, second shell is passed one or more fasteners fix.
20, method according to claim 19 is characterized in that this method also comprises such step: at the contiguous place of blade beam trailing edge, the one the second shells are passed one or more fasteners fix.
21, method according to claim 17 is characterized in that this method also is included in radially the step with tangential balance blade.
22, a kind of method that is used for the multiple material paddle of balance, this composite material contains unidirectional parallel side by side high modulus fibre, and fiber is filled in easily and moulds, in the basis material of low-intensity, low modulus.Blade includes each other at blade tip and leaf root part sweepback leading edge and the first crossing second surface of sweepback trailing edge.Blade also comprise can radially with tangential first, second mobile counterbalanced weight, counterbalanced weight is used in order to determine the blade centroid position, this method comprises the following steps:
(a) with tangential first desired location, adjust the one the second counterbalanceds weight, determine the centre of moment.
(b) with second desired location radially, revise the one the second counterbalanceds weight, determine the centre of moment.
23, method according to claim 22 is characterized in that this method also comprises the following steps:
(c) measure one group of centroid position that paddle is tangential.
(d) select a tangential standard centroid position, to reduce the dispersion of centroid position.
(e), make the centre of moment of each blade according to the standard centroid position.
24, method according to claim 23 is characterized in that this method also comprises the following steps:
(f) measure the radial centroid material;
(g) keep selecting the radial centroid position of a standard, to reduce the dispersion of radial centroid position under the centroid position unmodified situation in tangential centroid position with standard;
(h), make the centre of moment of one group of each paddle in the blade according to standard centroid position radially.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US27056588A | 1988-11-14 | 1988-11-14 | |
| US270,565 | 1994-07-05 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN1042692A true CN1042692A (en) | 1990-06-06 |
Family
ID=23031826
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN89103688.1A Pending CN1042692A (en) | 1988-11-14 | 1989-05-27 | The properller leaf of counter-rotating |
Country Status (7)
| Country | Link |
|---|---|
| JP (1) | JPH02155721A (en) |
| CN (1) | CN1042692A (en) |
| DE (1) | DE3922455A1 (en) |
| FR (1) | FR2639021A1 (en) |
| GB (1) | GB2224784A (en) |
| IT (1) | IT1230305B (en) |
| SE (1) | SE8903784L (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101203374B (en) * | 2005-06-30 | 2011-02-02 | 空中客车德国有限公司 | Process for producing a substantially shell-shaped component |
| CN104514785A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Blade big adjustment sheet gluing method |
| CN104655081A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Method for measuring pre-fastened angle of blade structure |
| CN109131832A (en) * | 2017-06-28 | 2019-01-04 | 通用电气公司 | Open rotor and its aerofoil profile |
| CN109458901A (en) * | 2018-12-07 | 2019-03-12 | 中国航发南方工业有限公司 | A kind of blade subsidiary pedestal manufacturing device |
| CN110815859A (en) * | 2019-11-29 | 2020-02-21 | 株洲时代新材料科技股份有限公司 | Design and manufacturing method of composite material blade and composite material blade |
Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5042968A (en) * | 1989-11-02 | 1991-08-27 | United Technologies Corporation | Propeller blade subassembly and method for making a propeller blade subassembly |
| GB2293631B (en) * | 1994-09-30 | 1998-09-09 | Gen Electric | Composite fan blade trailing edge reinforcement |
| US6290895B1 (en) * | 1997-10-14 | 2001-09-18 | General Electric Company | Selectively flexible caul and method of use |
| GB2450936B (en) | 2007-07-13 | 2010-01-20 | Rolls Royce Plc | Bladed rotor balancing |
| FR2970943B1 (en) | 2011-01-31 | 2014-02-28 | Eurocopter France | BLADE AND METHOD FOR MANUFACTURING THE SAME |
| FR3124216B1 (en) * | 2021-06-21 | 2023-10-20 | Safran Aircraft Engines | METHOD FOR BALANCING FAN BLADE WITH MACHINING THE TRAILING EDGE |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1038707B (en) * | 1957-07-20 | 1958-09-11 | Costa Vasiljevic Dr Ing | Process for the production of wings for gyroscopes |
| US3799701A (en) * | 1972-02-28 | 1974-03-26 | United Aircraft Corp | Composite fan blade and method of construction |
| DE3738785A1 (en) * | 1986-11-19 | 1988-05-26 | Gen Electric | CONTRA-ROTATING AIRPLANE DRIVE BLADES |
| US4810167A (en) * | 1986-12-08 | 1989-03-07 | Hartzell Propeller Inc. | Composite aircraft propeller blade |
-
1989
- 1989-05-27 CN CN89103688.1A patent/CN1042692A/en active Pending
- 1989-07-07 DE DE3922455A patent/DE3922455A1/en not_active Withdrawn
- 1989-07-07 IT IT8921119A patent/IT1230305B/en active
- 1989-07-10 GB GB8915764A patent/GB2224784A/en not_active Withdrawn
- 1989-07-11 JP JP1177306A patent/JPH02155721A/en active Pending
- 1989-07-11 FR FR8909286A patent/FR2639021A1/en active Pending
- 1989-11-10 SE SE8903784A patent/SE8903784L/en not_active Application Discontinuation
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101203374B (en) * | 2005-06-30 | 2011-02-02 | 空中客车德国有限公司 | Process for producing a substantially shell-shaped component |
| CN104514785A (en) * | 2013-09-30 | 2015-04-15 | 哈尔滨飞机工业集团有限责任公司 | Blade big adjustment sheet gluing method |
| CN104514785B (en) * | 2013-09-30 | 2016-12-07 | 哈尔滨飞机工业集团有限责任公司 | Blade big tab adhering method |
| CN104655081A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Method for measuring pre-fastened angle of blade structure |
| CN109131832A (en) * | 2017-06-28 | 2019-01-04 | 通用电气公司 | Open rotor and its aerofoil profile |
| CN109458901A (en) * | 2018-12-07 | 2019-03-12 | 中国航发南方工业有限公司 | A kind of blade subsidiary pedestal manufacturing device |
| CN110815859A (en) * | 2019-11-29 | 2020-02-21 | 株洲时代新材料科技股份有限公司 | Design and manufacturing method of composite material blade and composite material blade |
| CN110815859B (en) * | 2019-11-29 | 2022-03-29 | 株洲时代新材料科技股份有限公司 | Design and manufacturing method of composite material blade and composite material blade |
Also Published As
| Publication number | Publication date |
|---|---|
| SE8903784D0 (en) | 1989-11-10 |
| IT1230305B (en) | 1991-10-18 |
| GB8915764D0 (en) | 1989-08-31 |
| SE8903784L (en) | 1990-05-15 |
| DE3922455A1 (en) | 1990-05-17 |
| JPH02155721A (en) | 1990-06-14 |
| IT8921119A0 (en) | 1989-07-07 |
| GB2224784A (en) | 1990-05-16 |
| FR2639021A1 (en) | 1990-05-18 |
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| AD01 | Patent right deemed abandoned | ||
| C20 | Patent right or utility model deemed to be abandoned or is abandoned |