CN101649844B - Fan blade based on hollow metal/composite material structure - Google Patents
Fan blade based on hollow metal/composite material structure Download PDFInfo
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- CN101649844B CN101649844B CN2009100922747A CN200910092274A CN101649844B CN 101649844 B CN101649844 B CN 101649844B CN 2009100922747 A CN2009100922747 A CN 2009100922747A CN 200910092274 A CN200910092274 A CN 200910092274A CN 101649844 B CN101649844 B CN 101649844B
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Abstract
The invention discloses a fan blade based on a hollow metal/composite material structure. The inner base body of the fan blade is in a rib structure with discrete space. The fan blade comprises a hollow metal/composite material structure; the structure comprises a rib structure and inner holes; the rib structure is formed by combining and optimizing arbitrary space structures; the hole ratio is directly displayed by the space arranging mode of ribs and the rib diameter distribution; the rib structure and the surface of the blade are fixedly connected into a whole; the rib structure can be combined and optimized by a diamond structure, a tetrahedron unit structure, a hexahedron unit structure, a honeycomb structure or other arbitrary space structures; in regard to the space arrangement mode of the ribs and the rib diameter distribution, the rib diameters are gradually reduced and the space arrangement is gradually sparse following the radial increase of the blade along the radial direction of the blade; the thickness of the surface of the blade is controlled by pneumatic loads and technological conditions and the blade of the metal structure can be formed and processed quickly by high energy beams. The fan blade is directly and quickly formed and has simple technology. The structure shape has strong design performance.
Description
Technical field
The present invention relates to a kind of fan blade, especially relate to the modern big duct fan blade of super large bypass ratio civil aviation motor when, belong to aeroengine and high-speed rotating machine technical field based on hollow structure metal/composite material framework.
Background technique
The designs of adopting wide string not have middle convex shoulder of the fan blade of modern civilian big Bypass Ratio Turbofan Engine more, this is the design of extensively adopting in the motor of new generation, compare with shouldered narrow string blade, not only performance is good for wide string blade, efficient is high, and is improving to some extent aspect processing and the intensity.Square being directly proportional of the centrifugal load of fan blade and leaf quality distribution, rotating speed and mass distribution place radius product, wide string blade since chord length strengthen, the corresponding increasing of vane thickness, the centrifugal load that acts on root of blade strengthens; The fan diameter of high Bypass Ratio Turbofan Engine is generally bigger, fan as latest generation, its blade diameter has surpassed 3 meters, progressively increase along with design thrust, fan diameter further strengthens, hub ratio further reduces, and makes that the fan blade size is elongated, and this has also directly brought the increasing of blade centrifugal load; Three-dimensional blade profile design is also had higher requirement to blade strength, distortion etc.For big Bypass Ratio Turbofan Engine fan blade, the wide string blade of solid metal can not satisfy intensity and other designing requirements.
All advanced motors that adopt wide string fan blade for example among TRENT800, PW4000 and the GE90 etc., have all adopted the measure that reduces leaf weight abroad, as the hollow blade of hollow blade, belt carcass or composite material blade etc.(Chen Guangzhu, aeroengine structural design analysis, publishing house of BJ University of Aeronautics ﹠ Astronautics, 2006.7, Beijing).Recently the motor of developing for the B787 of Boeing type aircraft of future generation such as GEnx and sieve of GE company. the Trent 1000 of sieve company has adopted same composite material or hollow blade technology.
The fan blade of GE company adopts composite material and in conjunction with Ti metal leading edge technology, as shown in Figure 1.And sieve. the fan blade of sieve company has adopted the hollow belt of diffusion welding/superplastic forming (DB/SPF) to strengthen the titanium alloy technology of stringer, as shown in Figure 2.DB/SPF processing technology specific practice is, earlier the core stringer is coupled together at the diverse location place by diffusion connecting means and two panels inner face, then they are placed in the former under the high temperature, between two panels, fill earlier with high-pressure inert gas, two panels is outwards expanded under the superplasticity state, simultaneously stringer is elongated the ripple struction of forming as shown in Figure 2, because stringer welds together with panel, it has participated in load, thereby makes weight ratio sieve. the honeycomb interlayer hollow blade also light 15% that sieve is early stage.No matter be composite material blade or sieve of GE company. the DB/SPF processing technology of companies such as sieve, the application of all having succeeded is the crucial patented technology that this type of engine design is made.
The present invention relates to a kind of fan blade based on hollow structure metal/composite material framework.Hollow structure metal/composite material frame materials is made up of rigid backbone and inner hole, has excellent physical characteristics and favorable mechanical performance.It possesses the excellent physical mechanical property, and, specific strength little as density and specific stiffness are big, the energy-obsorbing and damping performance is good, have superior designability as a kind of engineering functional material.
It is little that the fan blade that the present invention relates to has density, specific strength, specific stiffness height, and vibration damping, damping capacity are superior, can improve the mechanical property of fan blade greatly, prolong the life-span of blade.Advanced at present process manufacturing technology such as high energy beam rapid shaping technique etc. provide possibility for the hollow structure metal/application of composite material frame materials in the turbofan engine fan blade.The direct rapid shaping technique of metal parts is to realize the bonding layer by layer of part from the cad model acquired information of setting up, and can directly produce theoretical density, high-strength functional metal parts.Wherein, laser high temperature sintering technology adopts laser pointwise illumination dusty material, makes the dusty material fusion realize the connection of material; The method that the laser melting coating rapid shaping adopts laser to apply is piled up material layer by layer, the final Three-dimensional Entity Components that forms with certain profile, and also the available metal filament replaces the metallic dust moulding.(the direct rapid shaping technique of metallic dust, developing electro-mechanic product and innovation, 2008 the 18th the 3rd phases of volume)
Summary of the invention
1, purpose: the object of the invention is exactly to combine with high energy beam rapid shaping or suitable process means and the design of thin sight engineering structure, for civilian big Bypass Ratio Turbofan Engine provides a kind of fan blade based on hollow structure metal/composite material framework.The present invention can reduce fan blade weight (loss of weight amplitude can up to 90%) significantly, and by to the microscopical structure design of fan blade metal frame to satisfy the specific intensity requirement of this type of fan.
2, technological scheme: a kind of fan blade based on hollow structure metal/composite material framework, blade profile as shown in Figure 3, its structure characteristic is: this blade interior matrix is the framing system of spatial spreading, it is made up of hollow structure metal/composite material framework, and porosity ratio directly translates into rib space arrangement mode and the rib diameter distributes; Blade surface is made of certain thickness material, can be designed to the form of UNICOM with holes and inner or closing surface, and concrete structure can be according to the demand of blade edge interlayer FLOW CONTROL; Framing system and blade surface are fixed with one.Blade profile can be continued to use the conventional design of prior art.What is more important is owing to structure superiority of the present invention, and blade profile might be used transnormal advanced pneumatic design.
Described framing system, its inner structure form can select for use a kind of in the typical space structural type or several to be combined to form,,, also can select atypical spatial structure pattern for use as diamond structure, tetrahedral unit framework, hexahedral element structure, cellular structure etc.; Or select for use typical space structural type and the mutual optimum organization of atypical spatial structure pattern to form framing system, or select for use other any spatial structure pattern Combinatorial Optimizations to form.Also can control the rigidity of blade and the deformable blade that causes by centrifugal force and aerodynamic force by its steric structure.This diamond structure as shown in Figure 7; This tetrahedral unit framework is shown in Fig. 3-6; This hexahedral element structure as shown in Figure 8; This cellular structure as shown in Figure 9.
Described hollow structure metal/composite material framework has superior designability as a kind of engineering functional material, is made up of framing system and inner hole that any spatial structure Combinatorial Optimization forms, has excellent physical characteristics and favorable mechanical performance.
Described rib space arrangement mode and rib diameter distribute, along the increase of blade radial along with radius, the rib diameter reduces gradually, the space is arranged sparse gradually, concrete distribution can distribute according to the centrifugal stress of blade and aerodynamic loading and design control, by control to rib space distribution and morpheme in the blade, improve the specific strength and the specific stiffness of blade, reach the designing requirement of satisfying blade strength.
The thickness of described blade surface is controlled by airload and process conditions, can carry out local thickness and adjust to improve the ability that the anti-foreign object of fan wounds.
The framing system and the blade surface of described blade are fixed with one, composite material framework blade adopts conventional composite material adhering method, the metal frame blade can be by the whole processing of rapid laser-shaping technique, perhaps similarly use the cladding rapid shaping technique of any kind of high energy beam and the various manufacturing process of other technology such as EDM (electric discharge machining), soldering, electrochemistry and foam metal, or any suitable manufacturing process.The metal frame blade uses the processing of high energy beam rapid shaping, concrete steps are as follows: (1) distributes according to blade loading and structural strength requires blade rib space arrangement mode and the distribution of rib diameter are designed, and blade surface thickness carried out three dimensional design, obtain the blade 3D solid and distribute; (2) select suitable metallic material; (3) according to the blade three-dimensional entity model, utilize high energy beam that material powder or filament are piled up layer by layer, directly produce theoretical density, high-strength functional metal parts.
Technique scheme also can be used on the blade, wheel disc of various turbomachines, as blade of wind turbine blade, water conservancy machinery etc.
3, advantage and effect: the advantage that the present invention compares with existing fan blade: direct rapid shaping, technology is simple, and structure morpheme designability is strong, can demonstrate fully material engineering at the superiority of using the designing material structure; The present invention simultaneously can carry out the design of strength stress distribution optimization; The mechanical damping optimal design; Blade morpheme distortion optimal design at aeroperformance; And the optimal design of other physico mechanical characteristics dissipates or the like as bump energy-absorbing, acoustic energy absorption; And has better casing containment with respect to common blade.
Blade technology provided by the invention is equally applicable to specific strength, specific stiffness, mechanical damping etc. are had the blade and the wheel disc of the various turbomachines of higher or specific (special) requirements, as wind turbine blade etc.
Description of drawings
Fig. 1: the schematic cross-section of solid composite material fan blade;
Fig. 2: hollow belt is strengthened the schematic cross-section of the metal fan blade of stringer;
Fig. 3: the schematic cross-section of fan blade of the present invention;
Fig. 4: fan blade framing system schematic representation of the present invention;
Fig. 5: the framing system distribution schematic diagram of fan blade surface of the present invention;
Fig. 6: the framing system distribution schematic diagram in the fan blade leaf of the present invention on certain section;
Fig. 7: diamond crystal structures schematic representation of the present invention;
Fig. 8: hexahedral element structural representation of the present invention;
Fig. 9: cellular structure schematic representation of the present invention.
Sequence number is described as follows among the figure:
1 framing system; 2 blade surfaces.
Embodiment
A kind of fan blade of the present invention based on hollow structure metal/composite material framework, the framing system 1 that this blade interior matrix is a spatial spreading, it is made up of hollow structure metal/composite material framework, and porosity ratio directly translates into rib space arrangement mode and the rib diameter distributes; Blade surface 2 is made of certain thickness metallic material, and it is designed to the form of UNICOM with holes and inner and closing surface, and framing system 1 is fixed with one with blade surface 2; It can be used for modern civilian big duct when in the fan level of super large Bypass Ratio Turbofan Engine, and its specific embodiment is as follows.
Embodiment 1:
Wide string shown in the left figure of Fig. 4 does not have the convex shoulder fan blade, and blade profile has satisfied motor totally to the performance requirement of fan part through pneumatic design.Utilize tetrahedron element that blade is carried out spatial spreading, the node line of tetrahedron element is the rib of fan blade, cell node is exactly the tie point of rib, and the interconnective framing system 1 of whole blade is shown in the right figure of Fig. 4, and Fig. 5 is framing system 1 distribution schematic diagram of fan blade surface 2.Fan blade makes up by this hollow structure metal/composite material framework, and than the solid metal blade, quality is much smaller.
Fan blade is subjected to the effect of centrifugal load when work, centrifugal force along with radius reduce increase gradually, so the rib diameter is along with radius reduces and must increase, to weaken the tensile stress that centrifugal force produces in the cross section, the concrete distribution design that can carry out rib diameter etc. according to the regularity of distribution of centrifugal load, thereby change the porosity ratio of fan blade, the tensile stress that blade is subjected to minimizes.
Fan blade is under the acting in conjunction of centrifugal load and aerodynamic loading, can bend and torsional deflection, Fig. 6 is 1 distribution schematic diagram of the framing system on certain section in the fan blade leaf, can arrange flexural rigidity and the torsional stiffness that changes blade by the rib space on the blade profile, for example just can significantly change the torsional stiffness of blade to the angle that changes the rib that links to each other along chord of blade.
After space distribution structure that designs the fan blade rib and diameter distribution, can process blade by rapid laser-shaping technique, perhaps similarly use the cladding rapid shaping technique of any kind of high energy beam.
As seen, the invention provides that a kind of porosity ratio is adjustable with load, bending and the controlled fan blade of torsional stiffness based on hollow structure metal/composite material framework.
Embodiment 2:
As a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1, framing system 1 is wherein formed by diamond crystal structures as shown in Figure 7.
Embodiment 3:
As a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1, framing system 1 is wherein formed by hexahedral element structure as shown in Figure 8.
Embodiment 4:
As a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1, framing system 1 is wherein formed by cellular structure as shown in Figure 9.
Embodiment 5:
As a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1, framing system 1 is wherein formed by the Combinatorial Optimization that comprises any spatial structure of framing system form among the example 1-4.
Embodiment 6:
As a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1-5, the framing system 1 of described blade and blade surface 2 can be processed by various manufacturing process or any suitable manufacturing process of other technologies such as EDM, soldering, electrochemistry and foam metal.
Embodiment 7:
As the technological scheme of a kind of fan blade based on hollow structure metal/composite material framework among the embodiment 1-6, be used for the blade and the wheel disc of various turbomachines, as wind turbine blade etc.
Obviously, for the person of ordinary skill of the art, also may make other mode of execution with reference to embodiment mentioned above.All embodiments above are exemplary rather than circumscribed.All modifications within the essence of claim technological scheme of the present invention all belong to its scope required for protection.
Claims (10)
1. fan blade based on hollow structure metal/composite material framework, it is characterized in that: this blade interior matrix is the framing system of spatial spreading, blade is made up of hollow structure metal/composite material framework, and porosity ratio directly translates into rib space arrangement mode and the rib diameter distributes; Blade surface is designed to the form of UNICOM with holes and inner or closing surface, and framing system and blade surface are fixed with one;
Described framing system is controlled the rigidity of blade and the deformable blade that is caused by centrifugal force and aerodynamic force by its space arrangement mode;
Described hollow structure metal/composite material framework, it is made up of framing system and inner hole that space arrangement mode optimization forms;
Described rib space arrangement mode and rib diameter distribute, along the increase of blade radial along with radius, the rib diameter reduces gradually, the space is arranged intensive gradually, porosity ratio increases gradually, specifically distributes according to the centrifugal stress of blade and aerodynamic loading and designs control, by the control to rib space distribution and morpheme in the blade, improve the specific strength and the specific stiffness of blade, reach the designing requirement of satisfying blade strength;
The thickness of described blade surface is controlled by airload and process conditions, carries out local thickness and adjusts to improve the ability that the anti-foreign object of fan wounds;
The framing system and the blade surface of described blade are fixed with one, composite material framework blade adopts conventional composite material adhering method, the metal frame blade pass is crossed the whole processing of rapid laser-shaping technique, perhaps uses the cladding rapid shaping technique processes of high energy beam to form.
2. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1 is characterized in that: the metal frame blade uses the rapid shaping technique processes of high energy beam, and concrete steps are as follows:
Step 1: require blade rib space arrangement mode and the distribution of rib diameter are designed according to blade loading distribution and structural strength, and blade surface thickness is carried out three dimensional design, obtain the blade 3D solid and distribute;
Step 2: select suitable metallic material;
Step 3: according to the blade three-dimensional entity model, utilize high energy beam that material powder, filament are piled up layer by layer, directly produce theoretical density, high-strength functional metal parts.
3. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1, it is characterized in that: this framing system is a diamond structure.
4. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1, it is characterized in that: this framing system is a tetrahedral unit framework.
5. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1, it is characterized in that: this framing system is the hexahedral element structure.
6. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1, it is characterized in that: this framing system is a cellular structure.
7. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1 is characterized in that: this framing system is the two or more pattern combination in diamond structure, tetrahedral unit framework, hexahedral element structure and the cellular structure.
8. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1 is characterized in that: this framing system is atypical spatial structure pattern.
9. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1 is characterized in that: this framing system is that the mutual optimum organization of typical space structural type and atypical spatial structure pattern forms.
10. a kind of fan blade based on hollow structure metal/composite material framework according to claim 1 is characterized in that: the form of this framing system and combination are used on the blade, wheel disc of turbomachine.
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| CN2009100922747A CN101649844B (en) | 2009-09-09 | 2009-09-09 | Fan blade based on hollow metal/composite material structure |
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| CN2009100922747A CN101649844B (en) | 2009-09-09 | 2009-09-09 | Fan blade based on hollow metal/composite material structure |
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| CN101649844B true CN101649844B (en) | 2011-10-19 |
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| EP2843193A1 (en) * | 2013-08-28 | 2015-03-04 | Techspace Aero S.A. | Composite blade made by additive manufacturing |
| EP2843192A1 (en) * | 2013-08-28 | 2015-03-04 | Techspace Aero S.A. | Composite blade made by additive manufacturing ahd associated manufacturing process |
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| US9816381B2 (en) | 2013-08-28 | 2017-11-14 | Safran Aero Boosters Sa | Composite blade made by additive manufacturing |
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