CN104981586A - Composite blade with uni-tape airfoil spars - Google Patents

Composite blade with uni-tape airfoil spars Download PDF

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Publication number
CN104981586A
CN104981586A CN201380054437.7A CN201380054437A CN104981586A CN 104981586 A CN104981586 A CN 104981586A CN 201380054437 A CN201380054437 A CN 201380054437A CN 104981586 A CN104981586 A CN 104981586A
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CN
China
Prior art keywords
spar
blade
airfoil
extension part
core
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN201380054437.7A
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Chinese (zh)
Inventor
N.J.克雷
I.F.普伦蒂斯
T.W.戴维斯
D-J.辛
P·D·沙
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General Electric Co
Original Assignee
General Electric Co
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Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of CN104981586A publication Critical patent/CN104981586A/en
Pending legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/16—Form or construction for counteracting blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6034—Orientation of fibres, weaving, ply angle
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Composite Materials (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

A gas turbine engine composite blade (10) includes an airfoil (12) having pressure and suction sides (41, 43) extending outwardly in a spanwise direction (S) from a blade root (20) along a span (S) to a blade tip (47). A core section (50) of the blade (10) including composite quasi-isotropic plies (52) extends spanwise outwardly through the blade (10). One or more spars (54, 56) including a stack (62) of uni-tape plies (63) having predominately a 0 degree fiber orientation with respect to the span (S) and extending spanwise outwardly through the root (20) and a portion (53) of the airfoil (12) towards the tip (47). Spars may include pressure and suction side spars (54, 56) sandwiching a chordwise extending portion (58) of the core section (50) in the airfoil (12) and which be located near or along the pressure and suction sides (41, 43) respectively. Chordwise extending portion (58) may be centered about a maximum thickness location (61) of the airfoil (12). Spars (54, 56) may have height (H), width (W), and thickness (T) that avoids flexural airfoil modes.

Description

With the composite blading of one-way tape airfoil spar
Technical field
The present invention relates to gas turbine engine blade, and in particular to composite blading.
Background technique
Developed the composite blading for aero gas turbine engine, this composite blading is made up of the elongated filament being compounded in light-duty matrix.Blade is light-duty, has high strength.Term compound has been defined as comprising the material of the reinforcer of the such as fiber or particle and so on that are bearing in bonding or body material.Many composites are all used in aviation industry, and it comprises metal composite and non-metal compound.Composite for blade disclosed herein is made up of one-way tape material and epoxy resin-base.The discussion of this composite and other suitable material is found in " Engineered Materials Handbook (Engineering Materials Handbook) " (1987-1989 or the later versions) that U.S. material informatics meeting (ASM INTERNATIONAL) publishes.
Composite blading disclosed herein is made up of nonmetal type, and this nonmetal type is made up of the material of the fiber of the such as carbon fiber-containing comprised in the resin material being embedded in such as epoxides, PMR15, BMI, inorganic filler composite material (PEEU) etc. and so on, silica fibre, steel fiber, metal-oxide fiber or ceramic fiber and so on.Fiber is unidirectional array in band, and described band, with resin-dipping, forms part shape, and solidifies to be formed in it article that are that have the lightweight of lamination or synusia, firm, relative homogeneous via high pressure leaching process or extrusion moulding.
Develop composite fan blade for aero gas turbine engine to reduce weight and cost, particularly reduce weight and cost for the fan blade in big-block engine.Big-block engine compound wide width wing string fan blade provides significant weight and saves compared with having the big-block engine of standard wing chord fan blade.Problem is, all gas turbine engine blades are all in the face of resonance or flexure mode.Large-scale composite fan blade for the aero gas turbine engine with the high by-pass ratio of relative wide diameter fan just faces this problem.This is very actual for causing the frequency of blade experience first flexure airfoil pattern and the second flexure airfoil pattern (1F and 2F).
Very it is desirable that, provide light-duty and firm aero gas turbine engine fan blade, its avoid by or experience homophonic (assonance) and flexure mode and particularly first and second bend airfoil pattern (1F and 2F).
Summary of the invention
A kind of gas turbine engine composite fan blade (10) comprises airfoil (12), and this airfoil (12) has on direction (S), extend out to vane tip (47) in exhibition from the root of blade (20) of blade (10) along the span (S) on the pressure side (41) and suction side (43).The core (50) of blade (10) comprises quasi-isotropic compound synusia (52), and these synusia (52) are towards most advanced and sophisticated (47) along opening up to extending outwardly through the blade (10) comprising root (20) and airfoil (12).The one or more spars (54,56) comprising the stack (62) that the one-way tape synusia (63) that is preferably 0 degree by the fiber-wall-element model relative to the span (S) is formed are towards most advanced and sophisticated (47) along exhibition to extending outwardly through root (20) and through the part (53) of airfoil (12).
The tangential extension part (58) of core (50) can be placed in the middle about the maximum ga(u)ge position (61) of airfoil (12).Spar (54,56) can have to be opened up to height (H), tangential width (W) and avoids such as the first flexure airfoil pattern and second to bend the spar thickness (TS) of the flexure airfoil pattern of airfoil pattern and so on.One or more spar can be included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched core (50) in airfoil (12), and the tangential extension part (58) of core (50) can lay respectively on the pressure side the vicinity of (41) and suction side (43) or locate along on the pressure side (41) and suction side (43) respectively.
In an embodiment of blade (10), one or more spar comprises the tangential upstream pressure flank beam (74) separated and downstream pressure flank beam (76) and tangential suction side, upstream spar (78) of separating and suction side, downstream spar (80), the on the pressure side tangential extension part (58) of spar and suction side spar sandwiched core (50) in airfoil (12).
Accompanying drawing explanation
Illustrate in the following explanation carried out by reference to the accompanying drawings of the present invention aforementioned in and further feature, in accompanying drawing:
Fig. 1 is the perspective view of the aero gas turbine engine composite fan blade with unidirectional tape spar.
Fig. 2 is the cross sectional view through the 2-2 in Fig. 1 of composite fan blade.
Fig. 3 is the perspective skeleton diagram of the alternative aero gas turbine engine composite fan blade with unidirectional tape spar.
Fig. 4 is the perspective skeleton diagram of the unidirectional tape spar shown in Fig. 3.
Fig. 5 is the perspective skeleton diagram of the composite fan blade-P degree shown in Fig. 2,0 degree and+P degree synusia.
Fig. 6 is the perspective view of the alternative aero gas turbine engine composite fan blade with unidirectional tape spar.
Fig. 7 is the cross sectional view through the 7-7 in Fig. 6 of composite fan blade.
Embodiment
Shown in Fig. 1 and Fig. 2 is the composite fan blade 10 of the fan jet type gas turbogenerator (not shown) of high by-pass ratio for having composite airfoil 12.The lamination 30 that composite fan blade 10 free-living conchocelis is strengthened is formed, and the composite layer component 36 of the compound synusia 40 (shown in Fig. 5) that these lamination 30 free-living conchocelis are strengthened is formed.As used in this article, term " lamination " and " synusia " are synonyms.Airfoil 12 be included in that exhibition extends out to vane tip 47 on direction from fan blade root 20 along span S on the pressure side 41 and suction side 43.In the exemplary embodiment, root 20 comprise make fan blade 10 can be mounted to rotor disk, one Dovetail 28.
Herein exemplary on the pressure side 41 and suction side 43 be recessed with projection respectively.Airfoil 12 extends between tangential isolated leading edge LE and trailing edge TE along wing chord C.The thickness T of airfoil 12 is in chordwise direction C and exhibition change in the convex side being also referred to as blade or airfoil of blade 10 and on the pressure side extending between 41 and suction side 43 of concave side on the S of direction.Airfoil 12 can be arranged on wheel hub and in aggregates to form Integrally Bladed Rotor (IBR) or to be integrated with coiling in open type integral leaf dish (BLISK) constructs with wheel hub.
Synusia 40 is usually all by unidirectional fibre strand plies of material, be preferably made up of band, and as it is often referred to generation, this band is arranged according to the order of the span and usually for the formation of composite airfoil 12 as shown in Figure 1.Synusia 40 is in fact formed as the airfoil 12 of the blade 10 as shown in Fig. 1 and Fig. 3 and those synusia of root 20.
The lamination 30 that composite fan blade 10 free-living conchocelis is strengthened is formed, and the composite layer component 36 of the airfoil synusia 40 that these laminations 30 are strengthened by different strands is formed.Blade 10 utilizes strand to be oriented to 0 degree as shown in Figure 5, the lamination strengthened of the strand of+P degree and-P degree or synusia.Angle P is the predetermined angle measured from 0 degree of the roughly radial axis extended corresponding to airfoil, and is generally about 45 degree, and described axis can be center line or the heap superimposing thread of this airfoil.Example arrangement in U.S. Patent No. 4,022, more specifically pointed out by Stanley in 547 and illustrate.
With reference to Fig. 1-4, composite fan blade 10 comprises the core 50 be made up of quasi-isotropic compound synusia 52.In airfoil 12, the on the pressure side tangential extension part 58 of spar 54 and the sandwiched core of suction side spar 56 50, described tangential extension part 58 by respectively roughly on the pressure side 41 and suction side 43 near or respectively along on the pressure side 41 and the quasi-isotropic compound synusia 52 of suction side 43 form.The tangential extension part 58 of core 50 extends partially across airfoil 12 along tangential.The tangential extension part 58 of core 50 in airfoil 12 roughly along between two parties tangential.The exemplary embodiment of the tangential extension part 58 herein extends through airfoil 12 about 1/3 and about the centre of airfoil 12 roughly along between two parties tangential along tangential.The quasi-isotropic tangential extension part of compound synusia 58 of core 50 is preferably limited to the thicker cross-section region of airfoil 12, and it is around the maximum ga(u)ge T of airfoil 12 mAXposition 61 or the maximum ga(u)ge T about airfoil 12 mAXposition 61 placed in the middle (as shown in FIG. 2), being the most effective.For exemplary airfoil shown herein, T mAXposition 61 be about airfoil between leading edge LE and trailing edge TE along the central authorities 1/3rd of chordwise direction C.On the pressure side spar 54 and suction side spar 56 by the fiber-wall-element model relative to span S be 0 degree, the stack 62 of the one-way tape synusia 63 (see Fig. 5) that is preferably 0 degree forms.
With reference to Fig. 3 and Fig. 4, on the pressure side spar 54 and suction side spar 56 (and they be made up of it one-way tape synusia) extend through fan blade root 20 along exhibition to S and through a part 53 to the spar tip 57 of airfoil 12.On the pressure side spar 54 and suction side spar 56 have the exhibition that measures from fan blade root 20 to spar tip 57 to height H, and it is less than the span S of airfoil.In the embodiment of the composite fan blade 10 in this article, on the pressure side spar 54 and suction side spar 56 (and they be made up of it one-way tape synusia) extend through the root 20 comprising Dovetail 28 always.
What quasi-isotropic synusia core 50 roughly comprised band has different fiber-wall-element model+P, 0 and the alternately synusia of-P.On the pressure side spar 54 and suction side spar 56 comprise the one-way tape synusia that fiber-wall-element model is mainly 0 degree.Exemplary blade synusia laminates is disclosed in the U.S. Patent No. 5 of " composite blading of anti-foreign object damage and the manufacture (Foreign Object DamageResistant Composite Blade and Manufacture) " by name of authorizing Evans, 375, in 978, this U. S. Patent is promulgated on December 27th, 1994 and is transferred the same assignee of this patent and be combined in herein in the mode of reference.Be disclosed in 5,375, the synusia laminates in 978 refer to there is multiple synusia shape, fiber-wall-element model is 0 degree ,+45 degree, 0 degree, the quasi-isotropic laminates sequence of the standard of-45 synusia of spending.
The stack 62 of spar comprises the one-way tape synusia that fiber-wall-element model is mainly 0 degree.Several synusia can have another fiber-wall-element model.Example is a kind of stack, and this stack has 8 synusia, respectively has 4 fiber-wall-element model to be the synusia of 0 degree in the both sides of two synusia that fiber-wall-element model is respectively+30 degree and-30 degree.This synusia laminates can represent or instruction by 0,0,0,0 ,+30 ,-30,0,0,0,0.
With reference to Fig. 1, Fig. 2 and Fig. 3, spar has exhibition to height H, tangential width W and spar thickness TS, and this spar thickness TS is designed to increase when not increasing the weight of blade the radial direction of airfoil 12 or exhibition to rigidity.Spar is also designed to or is customized to or is adjusted to the flexure airfoil pattern avoiding such as first flexure airfoil pattern 1F and second flexure airfoil pattern 2F and so on.Open up and be designed or be customized to height H and spar thickness TS the flexure airfoil pattern adjusting or avoid such as first flexure airfoil pattern 1F and second flexure airfoil pattern 2F and so on.The one-way tape synusia spar that fiber-wall-element model is mainly 0 degree account for harder blade, and without the need to increasing thickness and weight can not be increased, can not penalty being caused.The exemplary embodiment of the composite blading is herein a kind of fan blade, but also the composite blading of the spar having quasi-isotropic synusia core and be made up of the stack 62 of 0 degree of one-way tape synusia 63 can be used for other gas turbine engine blade of such as compressor blade and so on.
The exemplary embodiment of composite blading 10 herein comprises the one or more outer cover sheet 66 be made up of quasi-isotropic compound synusia around core 50 and on the pressure side spar 54 and suction side spar 56.Leading edge metal skirt 68 is combined in around leading edge LE.This guard shield is commonly referred to as metal coating.
With reference to Fig. 6 and Fig. 7, the alternative spar design for composite fan blade 10 comprises the core 50 that is made up of quasi-isotropic compound synusia and two groups on the pressure side spar and suction side spar.These two groups comprise tangential isolated upstream pressure flank beam 74 and downstream pressure flank beam 76 and suction side, tangential isolated upstream spar 78 and suction side, downstream spar 80, the on the pressure side tangential extension part 58 of spar and suction side spar sandwiched core 50 respectively, described tangential extension part 58 roughly on the pressure side 41 and suction side 43 near or respectively along on the pressure side 41 and suction side 43 be made up of quasi-isotropic compound synusia.
Describe the present invention by way of illustration.It will be understood that the term used is intended to have the character of descriptive words and non-limiting word.Preferred and the content of exemplary embodiment of the present invention is considered to be herein although described; but by instruction herein; other change of the present invention should be clear to those skilled in the art; and therefore, be intended to protect in the following claims all this changes dropped in true spirit of the present invention and scope.
Therefore, that be intended to be protected by U. S. Patent special permit is the present invention as limited in the following claims and distinguishing.

Claims (26)

1. a gas turbine engine composite blading (10), comprising:
Airfoil (12), described airfoil (12) has on direction (S), extend out to vane tip (47) in exhibition from the root of blade (20) of described blade (10) along the span (S) on the pressure side (41) and suction side (43)
The core (50) of described blade (10), described core (50) comprises quasi-isotropic compound synusia (52), described synusia (52) is towards described tip (47) along opening up to extending outwardly through the described blade (10) comprising described root (20) and described airfoil (12)
One or more spar (54,56), described one or more spar (54,56) comprises the stack (62) that the one-way tape synusia (63) that is mainly 0 degree by the fiber-wall-element model relative to the described span (S) is formed, and
Described one or more spar (54,56) is towards described tip (47) along exhibition to extending outwardly through described root (20) and through the part (53) of described airfoil (12).
2. blade according to claim 1 (10), it is characterized in that, described blade (10) also comprises described one or more spar, and described one or more spar is included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched described core (50) in described airfoil (12).
3. blade according to claim 2 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
4. blade according to claim 1 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), and the described tangential extension part (58) of described core (50) is placed in the middle about the maximum ga(u)ge position (61) of described airfoil (12).
5. blade according to claim 4 (10), it is characterized in that, described blade (10) also comprises described one or more spar, and described one or more spar is included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched described core (50) in described airfoil (12).
6. blade according to claim 5 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
7. blade according to claim 1 (10), it is characterized in that, described blade (10) also comprises described spar (54,56), and described spar (54,56) has exhibition to height (H), tangential width (W) and the spar thickness (TS) avoiding bending airfoil pattern.
8. blade according to claim 7 (10), is characterized in that, described blade (10) also comprises described flexure airfoil pattern, and described flexure airfoil pattern comprises the first flexure airfoil pattern and the second flexure airfoil pattern.
9. blade according to claim 8 (10), it is characterized in that, described blade (10) also comprises described one or more spar, and described one or more spar is included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched described core (50) in described airfoil (12).
10. blade according to claim 9 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
11. blades according to claim 8 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), and the described tangential extension part (58) of described core (50) is placed in the middle about the maximum ga(u)ge position (61) of described airfoil (12).
12. blades according to claim 11 (10), it is characterized in that, described blade (10) also comprises described one or more spar, and described one or more spar is included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched described core (50) in described airfoil (12).
13. blades according to claim 12 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
14. blades according to claim 1 (10), it is characterized in that, described blade (10) also comprises described one or more spar, described one or more spar comprises tangential isolated upstream pressure flank beam (74) and downstream pressure flank beam (76) and suction side spar, tangential isolated upstream (78) and suction side, downstream spar (80), in described airfoil (12), the tangential extension part (58) of described on the pressure side spar and the sandwiched described core (50) of described suction side spar.
15. blades according to claim 14 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
16. blades according to claim 15 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), and the described tangential extension part (58) of described core (50) is placed in the middle about the maximum ga(u)ge position (61) of described airfoil (12).
17. blades according to claim 16 (10), it is characterized in that, described blade (10) also comprises and has exhibition to height (H), tangential width (W) with avoid the described upstream pressure flank beam (74) of the spar thickness (TS) bending airfoil pattern and described downstream pressure flank beam (76) and tangential suction side spar, isolated described upstream (78) and suction side, described downstream spar (80).
18. blades according to claim 17 (10), it is characterized in that, described blade (10) also comprises described flexure airfoil pattern, and described flexure airfoil pattern comprises the first flexure airfoil pattern and the second flexure airfoil pattern.
19. blades according to claim 17 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
20. blades according to claim 19 (10), it is characterized in that, described blade (10) also comprises described flexure airfoil pattern, and described flexure airfoil pattern comprises the first flexure airfoil pattern and the second flexure airfoil pattern.
21. blades according to claim 1 (10), is characterized in that, described blade (10) also comprises:
Described root (20) comprises the Dovetail (28) of one,
Around one or more outer cover sheets (66) of described core (50), and
Be combined in described leading edge (LE) leading edge metal skirt (68) around.
22. blades according to claim 21 (10), it is characterized in that, described blade (10) also comprises described spar (54,56), and described spar (54,56) has exhibition to height (H), tangential width (W) and the spar thickness (TS) avoiding bending airfoil pattern.
23. blades according to claim 22 (10), it is characterized in that, described blade (10) also comprises described flexure airfoil pattern, and described flexure airfoil pattern comprises the first flexure airfoil pattern and the second flexure airfoil pattern.
24. blades according to claim 23 (10), it is characterized in that, described blade (10) also comprises described one or more spar, and described one or more spar is included on the pressure side spar (54) and the suction side spar (56) of the tangential extension part (58) of sandwiched described core (50) in described airfoil (12).
25. blades according to claim 24 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), and the described tangential extension part (58) of described core (50) is placed in the middle about the maximum ga(u)ge position (61) of described airfoil (12).
26. blades according to claim 25 (10), it is characterized in that, described blade (10) also comprises the described tangential extension part (58) of described core (50), described in the described tangential extension part (58) of described core (50) lays respectively on the pressure side (41) and described suction side (43) vicinity or respectively along described on the pressure side (41) and described suction side (43) location.
CN201380054437.7A 2012-10-23 2013-09-24 Composite blade with uni-tape airfoil spars Pending CN104981586A (en)

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US13/658,209 US20140112796A1 (en) 2012-10-23 2012-10-23 Composite blade with uni-tape airfoil spars
US13/658209 2012-10-23
PCT/US2013/061294 WO2014065968A1 (en) 2012-10-23 2013-09-24 Composite blade with uni-tape airfoil spars

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WO2014065968A1 (en) 2014-05-01
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US20140112796A1 (en) 2014-04-24
BR112015009060A2 (en) 2017-07-04
JP6179961B2 (en) 2017-08-16
EP2917496A1 (en) 2015-09-16

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