CN107407154A - Frangible composite airfoil - Google Patents
Frangible composite airfoil Download PDFInfo
- Publication number
- CN107407154A CN107407154A CN201680005933.7A CN201680005933A CN107407154A CN 107407154 A CN107407154 A CN 107407154A CN 201680005933 A CN201680005933 A CN 201680005933A CN 107407154 A CN107407154 A CN 107407154A
- Authority
- CN
- China
- Prior art keywords
- energy dissipation
- dissipation component
- composite blading
- airfoil
- pouch
- 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.)
- Granted
Links
Classifications
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- 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
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- 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
- F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
- F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
- F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
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- 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
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- 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
-
- 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
Abstract
The present invention provides a kind of rotary machine (10) with least one frangible composite blading (40), and frangible composite blading (40) mitigates the unfavoured state related to the material release as caused by the impact damage to composite blading (40).Composite blading (40), which has, is used for dissipate energy, the function from crushing and predetermined release track.Also provide it is a kind of be used to manufacturing composite blading (40), by blade assembling into rotary machine (10) and operation from the method for crushing vane (40).
Description
The statement of research is subsidized on federal government
Nothing
The cross reference of priority information and related application
This application claims the priority of following U.S. Patent application：Darek Zatorski entitled " A method of
A kind of manufacturing a frangible blade (method for manufacturing frangible blade) " U.S. Patent Application Serials
No.14/596,841, entire contents are incorporated herein in by reference；Darek Zatorski entitled " A rotary
A kind of machine with a frangible composite blade (rotating machinery with frangible composite blading) " U.S.
State Patent Application Serial No.14/596,815, entire contents are incorporated herein in by reference；And Darek Zatorski
Entitled " A frangible airfoil (a kind of frangible airfoil) " U.S. Patent Application Serial No.14/596,804,
Entire contents are incorporated herein in by reference.
Technical field
The field of the invention is broadly directed to rotating machinery, and more particularly relates to the airfoil of rotating machinery.This
Embodiment is broadly directed to the airfoil of the blower module of the gas-turbine unit for aircraft installation.More specifically, work as front wing
Type part embodiment relates to, but are not limited to alleviate the compound wind of the unfavorable conditions related to the release of the material as caused by impact damage
Fan leaf or propeller.
Background technology
At least some known rotating machineries, such as gas-turbine unit, some of them are used for aircraft propulsion, including make
Downstream to guide the multiple rotating vanes or propeller of a part for the blower module of air.Although some single revolving wormgear spiral shells
Rotation paddle motor has been considered for higher cruising speed, but traditional single revolving wormgear propeller gas turbine engine pair
In the flight Mach number for reaching about 0.7 high efficiency is provided under low cruise speed.The higher of Mach 2 ship 0.7 to 0.9 is patrolled
Speed of a ship or plane degree is typically obtained using ducted fan gas-turbine unit to produce required relatively high thrust.Reversely revolved without exhausting
Rotating propeller gas-turbine unit, commonly known as without the ducted fan (registration mark of General Electric) or open
Formula rotor, it is developed to transmit the high thrust needed for high cruising speed with the efficiency higher than ducted fan.These blades
There is certain integrality for the exotic fragment sucked by engine with propeller, but the suction of exotic still is able to draw
The release of the destruction part of rotating vane or propeller is played, and therefore can improve these blades and propeller.
The content of the invention
In an aspect, embodiments of the invention are related to the airfoil with composite blading, composite blading have root,
Tip and the span between root and tip, together with leading edge and trailing edge, there is string, blade tool between leading edge and trailing edge
There is at least one energy dissipation component including pouch.
In another aspect, embodiments of the invention are related to the energy dissipation along the span chord extension of composite blading
Component and energy dissipation component has at least one cored wire.
In in other respects, embodiments of the invention are related to partly covered with releasing agent and jointly solid with composite blading
The energy dissipation component of change.
In in other respects, embodiments of the invention are related to the energy dissipation component for destroying initiator, destroy and trigger
Utensil has at least one cored wire for being attached to initiator.In addition, initiator can be pouch.Further, pouch can have
There is the plunger for meeting pouch, in this plunger with least one cored wire combination operation so that pouch expands, and then destroy or broken
Broken composite blading.
In a further aspect, embodiments of the invention are related to pouch, and the release part of composite blading is divided from composite blading
From when pouch activate.
In still other side, embodiments of the invention are related to the method for manufacturing frangible laminate, comprise the following steps：
Construction, which strengthens polymeric matrix, will strengthen polymeric matrix cuts into multiple thin layers, via stacking multiple thin layers and at least one
Energy dissipation component forms laminate and consolidation laminate.
In another aspect, embodiments of the invention relate to the use of the method for the reinforcement polymeric matrix including resin,
Wherein, the group that Choice of Resin is made up of following material：Polyether-ether-ketone, PEKK, polyphenylene sulfide, polyamide-imide, polyethers acyl
Imines, epoxy resin, polyester, phenolic aldehyde, vinyl esters, polyurethane, silicones, polyamide and polyamidoimide.Similarly, originally
The embodiment of invention is related to a kind of method, wherein, strengthening polymeric matrix includes stiffener, and wherein stiffener is selected from by following material
Expect the group of composition：Glass, graphite, aramid and organic fiber.In addition, embodiments of the invention are related to following methods, its
In, resin also includes toughening material, wherein, toughening material is selected from the group being made up of elastomer rubber and thermoplastic.
In in other respects, embodiments of the invention are related to the method that wherein thin layer is flaggy, are related to the shaping of its middle plate
For the method for final products, and it is related to the method that solidification is wherein performed in autoclave.
On the other hand, embodiments of the invention are related to the final products that wherein make laminate be configured to as composite blading
Method.In another aspect, embodiments of the invention relate to the use of the reinforcement polymeric matrix including resin and made as compound
The method of the final products shaping of blade, wherein, the group that Choice of Resin is made up of following material：Polyether-ether-ketone, PEKK, gather
Diphenyl sulfide, polyamide-imide, PEI, epoxy resin, polyester, phenolic aldehyde, vinyl esters, polyurethane, silicones, polyamide
And polyamidoimide.Similarly, embodiments of the invention relate to the use of reinforcement polymeric matrix and made as composite blading most
The method of finished product shaping, strengthening polymeric matrix includes stiffener, wherein, stiffener is selected from the group being made up of following material：
Glass, graphite, aramid and organic fiber.
On the other hand, embodiments of the invention are related to operation from crushing vane (operating a self-
Shredding blade) method, this method comprises the following steps：The release part of composite blading is discharged, composite blading includes
At least one energy dissipation component (energy dissipating member)；Via at least one energy dissipation component damage
Discharge part；Selectively keep the member-retaining portion of composite blading；And selectively via at least one energy dissipation component
Destroy member-retaining portion.
In another aspect, embodiments of the invention are related to method of the operation from crushing vane, wherein, energy dissipation structure
Part is attached to rotor.
On the other hand, embodiments of the invention are related to method of the operation from crushing vane, wherein, destroying step also includes
Destroy the composite blading structure around at least one energy dissipation component.
On the other hand, embodiments of the invention are related to method of the operation from crushing vane, in addition to via at least one
The track that energy dissipation component changes release part causes the step of release part is along row predefined paths.
It yet still another aspect, embodiments of the invention are related to method of the operation from crushing vane, in addition to via at least one
The step of kinetic energy of energy dissipation component dissipation release part.
This general introduction provides the selection for being used for introducing the following design further illustrated in detail specifications in simplified form.
This general introduction is not intended to determine the key feature or essential characteristic of claimed theme, is also not intended to claimed for limiting
The scope of theme.All above-mentioned summary feature is understood to merely illustrative, and can be from this disclosure collection structure
With the more features and purpose of method.Feature, details, practicality and the more extensive of advantage of the present invention is represented in each of the present invention
There is provided, be shown in the drawings, and limited in following claims in the following printed instructions of individual embodiment.Therefore,
It is further read include entire disclosure in this, claims and accompanying drawing in the case of, it will be understood that this general introduction
Non-restrictive explanation.
Brief description of the drawings
By reference to the following explanation with reference to accompanying drawing, above-mentioned and other feature and advantage and the acquisition of these embodiments
Its mode will become apparent and embodiment will be better understood, wherein：
Fig. 1 is the side cross-sectional, view of ducted fan gas-turbine unit；
Fig. 2 is mounted in the perspective view without exhausting contraprop engine on aircraft；
Fig. 3 is the side view of contraprop engine；
Fig. 4, Fig. 5, Fig. 6 and Fig. 7 are corresponding sequential of the ducted fan engine in fan airfoil part part deenergized period
Front view；
Fig. 8 and Fig. 9 is the exemplary embodiment of the present invention and is the side view of the composite blading with energy dissipation component
Figure, blade are shown respectively in original state and released state；
Figure 10 is the alternate exemplary embodiment of the present invention and is with the energy dissipation structure for including destruction initiator
The side view of the composite blading of part；
Figure 11 is the perspective view of the destruction initiator of the exemplary embodiment of the invention in Figure 10.
Figure 12 and Figure 13 is being respectively at for the destruction initiator of exemplary embodiment and Figure 11 of the invention in Figure 10
The section Section View of " before accident " and " after accident " state.
Figure 14 is another alternative exemplary embodiment of the present invention and is with energy dissipation component and release areas
Composite blading side cross-sectional view；
Figure 15 is another alternative exemplary embodiment of the present invention and is the composite blading with energy dissipation component
Side view；
Figure 16, Figure 17, Figure 18 and Figure 19 be after impact accident propeller part deenergized period propeller phase
The sequential front view answered；And
Figure 20, Figure 21, Figure 22 and Figure 23 are that the of the invention of a part of deenergized period Figure 15 after impact accident is shown
The corresponding sequential front view of example property alternate embodiment.
Figure 24 is the flow chart for summarizing the subsequent treatment steps that the method according to the invention performs.
Embodiment
It should be understood that the application is not limited in description below to show in restriction or accompanying drawing by described embodiment
The construction of the part gone out and the details of arrangement.Described embodiment can be other embodiment and can be real in a variety of ways
Apply or perform.Each example provides by way of illustration, rather than the limitation to the disclosed embodiments.In fact, for ability
Field technique personnel to present example it is evident that can make without departing from the scope or spirit of the invention
Various modifications and variations.For example, the feature that the part as one embodiment shows or illustrated can be used for another implementation
Example is further to form further embodiment.Therefore, it is contemplated that covering falls into the model of appended claims and its equivalent
Enclose these interior improvement and modification.
Further, it is to be appreciated that wording used herein and term are for illustration purposes, and it is not construed as limiting
System." comprising ", "comprising" or the use of " having " and its modification herein refer to including hereafter listed project and its
Equivalent and other project.Unless make other limitation, otherwise term " connection ", " connection " and " installation " and its at this
Modification in text can be by broadly application and including connection directly or indirectly, connection and installation.In addition, term " connection " and
" connection " and its modification are not limited to physics or mechanical connection or connection.
As it is used herein, term " axial direction " or " axially " referring to size along the longitudinal axis of engine.
The term with " axial direction " or " axially " being used in combination is referred to " forward " along being moved towards the direction of engine intake, or portion
Part is relative closer to engine intake compared with another part.The term " rear portion " with " axial direction " or " axially " being used in combination
Refer to that edge is moved towards the direction of engine nozzle, or part is relative closer to engine spray compared with another part
Mouth.
As it is used herein, term " radial direction " or " radially " referring to the central longitudinal axis in engine with starting
The size extended between machine outer peripheral edge.No matter being single use or with term " radial direction " or " radially " being used in combination, term is " near
The use of end " or " proximally " refer to that edge is moved towards the direction of central longitudinal axis, or part is compared with another part
Relatively closer to central longitudinal axis.No matter being single use or with term " radial direction " or " radially " being used in combination, term is " remote
The use of end " or " distally " refer to that edge is moved towards the direction of engine outer peripheral edge, or part is compared with another part
Relatively closer to engine outer peripheral edge.
As used herein, term " transverse direction " or " laterally " refer to perpendicular to axial dimension and radial dimension two
The size of person.
Whole directions with reference to (for example, radially, axially, near-end, distal end, top, bottom, it is upward, downward, left and right, horizontal,
It is front portion, back, top, bottom, the above, following, vertical, horizontal, clockwise, counterclockwise) recognition purpose is only used for help to read
Person understands the present invention, rather than is construed as limiting, especially with regard to position, orientation or the use of the present invention.Connection is with reference to (for example, attached
Even, connection, connection and connection) it is broadly interpreted, and can be including between the intermediate member and element between element set
Relative motion, unless otherwise indicated.Therefore, connection is connected to each other directly and is in reference to being not necessarily inferred to two elements
In fixed relationship.Only for illustrating, the size, position, order and the relative size that reflect in accompanying drawing can change exemplary drawings.
For the fan blade of ducted fan gas-turbine unit and for single revolving wormgear propeller and without letter
The propeller of road contraprop gas-turbine unit is for the outer of the bird, fragment and other articles that are sucked by engine
Carrying out thing destruction has certain integrality.However, the suction of exotic may cause releasing for the part of rotating vane or propeller
Put, this may be damaged to other engine components or aircaft configuration.For single revolving wormgear propeller and without exhausting
In the case of the fan blade or open rotor of contraprop engine, if without other way to manages, for
The engine of these types, the shortage around the pipeline configuration of blade or propeller are blade or the rail of the release part of propeller
Mark provides the posterior leaflet for making the local collision adjacent and the possibility of other adjacent aircaft configurations.The leaf of prior art
Piece and propeller are without the size for reducing any release blade-section and the fragility of energy.It is, therefore, possible to provide resistance is outer
Come thing destroy however exhausting frangible when needed, without the single revolving wormgear propeller of exhausting and without exhausting counter-rotatable fans leaf
Piece and propeller.
It is as discussed in more detail below according to the composite blading of the present invention.Such as used illustration, this section and following brief description
In, term " blade " is understood to include but is not limited to both fan blade and propeller, and term " composite " is understood
For include but is not limited to strengthen polymeric matrix composite material, including for thermosetting or thermoplastic matrix and including but it is unlimited
In the stiffener of the glass with any length, size or orientation, graphite, aramid or organic fiber, and further
Be understood to include but be not limited by injection moulding, resin transfer moulding, prepreg tape coating (manually or automatically), pultrusion into
Type or for manufacture strengthen polymeric matrix composite construction any other appropriate method manufacture.In addition, " composite "
It is understood to include but is not limited to and metal, the combination of more than one reinforcement polymeric matrix composite material or more than one gold
The mixing composite for the reinforcement polymeric matrix composite material that the combination of category combines.Term " co-curing " be understood that including
But it is not limited to solidify composite and is incorporated into simultaneously to the action of some other uncured materials, and by two or more
The action that multiple element is solidified togather, at least one in two or more elements can be fully cured, it is at least one can
With uncured.
Term " track " is understood to include but is not limited to the part institute after being released in the release part of composite blading
The path taken.The path for example can be described relative to the longitudinal centre line of rotary machine, such as relative to gas turbine
Engine centerline.
Composite blading can operate under high rotation speed and linear tip speed, and can include being selected from by for disappearing
Dissipate the device of energy, at least one of group of device composition from the device crushed and for predefining release track
Device.Composite blading can include one or more internal co-curing energy dissipation components, with exotic collision and
After part or all of blade for discharging blade, energy dissipation component can be realized selected from one of following function：Dissipation leaf
The kinetic energy for being released part of piece, the release part of crushing vane or blade and the track for discharging part for changing blade.
Energy dissipation component can be positioned at the inside of composite blading, or a part of of energy dissipation component can extend to compound leaf
The outside of piece and vane tip can be extended radially to from the base portion of blade or root, and can be along the shaft orientation string of blade
Distribution.In addition, some embodiments can include at least one bent portion in energy dissipation component.Energy dissipation component can be with
Including cored wire or selectable destruction initiator, to help crushing vane and dissipation kinetic energy in desired zone.
Term is understood to include " from crushing " but is not limited to being collided in blade with enough power to discharge for composite blading
To the ability destroyed purposely of composite blading itself after a part for composite blading, including destroy, tear, cut or expand week
The ability of the energy dissipation component for the composite blading structure enclosed, the composite blading structure of surrounding include for example strengthening polymeric matrix
Structure, strengthening polymeric matrix structure includes being thermosetting or thermoplastic matrix and stiffener, and it includes but is not limited to have
There are glass, graphite, aramid or the organic fiber of any length, size or orientation.May in the identical of composite blading or
Sequentially or simultaneously crushed at different thickness, depth, string or the span, crush the band that may cause composite blading structure
Or the release of fragment.
One exemplary non-limiting embodiments of composite blading utilize with cored wire (strand) and destroy initiator
The energy dissipation component of (damage initiator), cored wire and destruction initiator are collided to release in composite blading with enough power
Put part to pull by the structure of composite blading afterwards, so as to destroy composite blading structure.The other embodiment bag of composite blading
Include the release areas along the radial direction span of blade, release areas and energy dissipation component combination work with balance impact resistance and
Fragility.Other embodiment includes the energy dissipation component with cored wire, and cored wire has the relaxation or extra to interlock along chord of foil
Length, to be directed at or change the track of release part to prevent the collision with posterior leaflet or other structures.
With reference first to Fig. 1, the schematic side sectional of ducted fan gas-turbine unit 10 is illustrated as including along hair
The blower module 12 and engine core 14 that motivation axis 32 positions.Blower module 12 includes surrounding a series of fan airfoil parts 18
Blower-casting 16, fan airfoil part 18 extends from the radially distant end of rotor 20 and is attached to rotor 20.Engine core 14
Including high pressure compressor 22, combustion chamber 24 and high-pressure turbine 26.The driving fan airfoil 18 of low-pressure turbine 28.Selectively, subtract
Speed variator 34 can be connected between low-pressure turbine 28 and rotor 20 so that the rotary speed of blower module is reduced into low-pressure turbine
Below 28 rotary speed.Selectable deceleration device 34 can be the epicyclic gearbox of star or planetary structure, compound gear
Case or other geared systems for realizing the deceleration between low-pressure turbine 28 and rotor 20.
In operation, air is entered by the air intlet 30 of engine 10 and moved by least one compression stage,
It can be raised in this air pressure and be directed to combustion chamber 24.Compressed air is mixed and burnt with fuel, there is provided towards high pressure
Turbine 26 and low-pressure turbine 28 discharge the hot combustion gas of combustion chamber 24.At high-pressure turbine 26 and low-pressure turbine 28, from causing
The hot combustion gas extraction energy of turbine airfoil rotation, turbine airfoil then make high pressure compressed 22 and fan airfoil part respectively
18 axle rotates around engine axis 32.On embodiments described herein, fan airfoil part 18 represents composite blading 40
Position in blower module 12 and ducted fan engine 10.
Referring now to Figure 2, show on the wing 102 installed in aircraft 100 without exhausting contraprop engine
110 perspective view.In addition, in figure 3, the side view of contraprop engine 110 is illustrated as including engine axis
32nd, radome fairing 114 and blower module 116, blower module 116 have two level contraprop, the first order 118 and the second level
120.Each in level 118 and 120 has multiple propellers 122 and 124.Engine 110 operates and on the letter in Fig. 1
The discussion of road Duct-Burning Turbofan 10 is identical, and blower module 116 has not by shell structure encirclement without the He of ducted propeller 122
124.Although not shown in Fig. 2 or Fig. 3, turboprop has only single step helical oar 118, also without circular
Housing.On embodiments described herein, propeller 118 and 120 represents composite blading in contraprop engine
110 blower module 116 and with single step helical oar 118 turboprop in position.For the sake of clarity, exist
In total of three engine construction as described above, composite blading will be around corresponding engine axis 32 and rotate.
With reference to figure 1, the such as, but not limited to exotic for guiding and being inhaled into blower module 12 by import 30, bird
Class, it can result in the damage of fan airfoil part 18, blower-casting 16 and other downstream configurations in engine 10.Similarly,
For contraprop engine 110, as shown in figure 3, exotic can be located at blower module during power operation
In 116 path, cause to the destruction without ducted propeller 122 and 124.Destruction for fan airfoil part or propeller may
It is particularly troublesome, because these parts with the diameter of engine core 14 and may collide the example of fan airfoil part or propeller
Diameter and length are relatively large when size such as bird or the potential exotic of airport fragment is compared.This large scale allows fan
The part of airfoil or propeller discharges and causes secondary collision and cause subsequent destruction.This destruction may cause hair
The reduction of motivation performance and causing the loss of engine power in some cases.
Fig. 4, Fig. 5, Fig. 6 and Fig. 7 are described can be in the outer of fan airfoil part 18 and the release for causing fan airfoil part 18
The time phase image for the event come inside the blower module 12 that thing collision deploys afterwards.The main view of ducted fan engine 10
Figure uses the fan airfoil part 18 and blower-casting 16 of conventional stage.With reference now to Fig. 4, Fig. 5, Fig. 6 and Fig. 7, two are each illustrated
Ten fan airfoil parts 18 and blower-casting 16 and the sequential for showing the deenergized period engine 10 of part airfoil 18,20
Only it is the exemplary amounts of airfoil 18 and is not intended to limit the invention in any way.The wing in each in Fig. 4-7
One of type part 18 is denoted as letter r, is indicated as discharging airfoil or primitively then can may by exotic collision
Cause the airfoil 18 of the part release of airfoil 18.Be adjacent to discharged airfoil R another airfoil 18 by
Tee is identified as, is denoted as trailing aerofoil part.Trailing aerofoil part T is tracking or the airfoil 18 for lagging behind airfoil 18.
Specific airfoil 18 is identified as into release blade and posterior leaflet is exemplary and does not limit the invention in any way.
In Fig. 4, whole fan airfoil parts 18 are reset conditions, and it is not yet collided by exotic.In Figure 5, airfoil R has been discharged
Collided by exotic and may possibly be separated into two pieces now.Fig. 6 is turned to, release airfoil R free portion is likely to collide
Trailing aerofoil part T.Finally, in the figure 7, trailing aerofoil part T is separated into two due to the collision of release airfoil R free portion
Block, release airfoil R free portion is eliminated for clarity.
Due to the high rotation speed of the fan airfoil part 18 in engine 10, the size of the free portion of airfoil is discharged
It is any to reduce the kinetic energy for reducing that trailing aerofoil part T and the needs of blower-casting 16 are born.This reduction of required energy absorption causes
The reduction of the relative weight of blower-casting 16, because it, which allows to remove in housing 16, includes device and structure.Mitigate weight then
By allow increase engine 10 another region in weight and allow aircraft carry more multi fuel be used for longer voyage or
Improve robustness.Another the important beneficial effect brought by the size of reduction free portion is due to the release by inertial load
And the institute of rotor 20 caused by the degree of eccentricity caused by the change of the fan blade 18 on rotor 20 is carried in after discharge
The parallel reduction for the unbalanced load being subjected to.These beneficial effects can also consider open rotor engine 110 and spiral
Received an acclaim during any reduction of the size of the release part of oar 122 and 124.
As shown in exemplary embodiment of the invention in Fig. 8 and Fig. 9, the target can be by the way that one or more energy be disappeared
Component 80 is dissipated to be attached in composite blading 40 to realize.Fig. 8 is considered first, and the composite blading 40 in initial conditions is shown, its
With root 42, tip 44, leading edge 46 and trailing edge 48, the span 52 of blade 40 reaches tip 44 from the radially distant end of root 42,
Shaft orientation string 54 makes rear portion move to trailing edge 48 from leading edge 46.Internal flow path 50 can be radially remote along 54 opposing root of string 42
End ground limits in the span, and represent the span 52 will bear the minimum radial component of exotic collision accident.In the example
Property embodiment in, composite blading 40 has three energy dissipation components 80, and energy dissipation component 80 has the cored wire of various length
82, each energy dissipation component 80 selectively starts in root 42 and extended towards sophisticated 44 radially distant ends, then
Towards the radial direction of internal flow path 50 and proximally bend backward, form at least one selectable bent portion 86.Although should
Energy dissipation component 80 in embodiment starts at root 43, but component 80 can be in any position in composite blading 40
Start, for example, among tip, the span etc..Be attached to the both ends of each cored wire 82 can be with structure qualification as described above
At least one destruction initiator 84.In this embodiment, the setting of single energy dissipation component 80 is selected as including position
In one end radially below of internal flow path 50, internally flow path 50 extends through inside to the component radially above
Flow path 50, but it is not limited to this set and arrangement of component 80.Three energy dissipation components 80 are in the exemplary implementation
Shown in example, but any amount of component 80 can be used.
The non-limiting embodiments of energy dissipation component can include can with it is internally positioned, can be extended partially into it is outside with
And can be co-curing with composite blading cored wire.Cored wire material can include but is not limited to the registration mark of Toyobo companiesAny other of (poly- (to penylene -2,6- Benzo-dioxazoles)) fiber, high duty metal line or wire form is appropriate
High-strength material.The exemplary non-limiting embodiments of the cross sectional shape of cored wire can be circular, avette, polygon or irregular
, and its sectional dimension can be from about 0.005 inch to about 0.075 inch and from about 0.010 inch to big
In the range of about 0.030 inch.Other exemplary non-limiting embodiments of the area of section of cored wire can be from about 0.0001
Section face of the square inch to about 0.02 square inch and from about 0.001 square inch to about 0.002 square inch
In product scope.Other exemplary unrestricted wire forms can include braid, fabric, band or band forms.Cord segments can be with
Along consistent length or its sectional dimension, cross sectional shape, form and changes in material, including but not limited to size from length one
End increases to the other end.
The wheel in regional area of composite blading can be customized to by destroying the exemplary shape of initiator and material aspect
Exterior feature, and in addition material selection can be customized to it is co-curing, assembling or composite blading operate during not with composite blading
Learn reaction.Shaping, entity, hollow or wedge-shaped zigzag metal, ceramics can be included by destroying the non-limiting embodiments of initiator
Or composite construction, for the ease of the purpose of understanding, not to it show, and can also internally and can be with compound leaf
Piece is co-curing.This destruction initiator material can include but is not limited to steel, aluminium, titanium, cobalt, chromium and nickel metal alloy, or
Any other appropriate metal alloy.Other destroy initiator materials can include beryllium oxide, cerium oxide and
The oxide ceramic of zirconium oxide；Include the non-oxidized substance of carbide, boride, nitride and silicide；And with and without
The alone or in combination oxide and non-oxidized substance of grain stiffener or fiber reinforcement.Another of destruction initiator is unrestricted
Embodiment includes at least local hollow pouch for being at least partially filled with filler.The form of filler can include but unlimited
In fluid or semisolid.Fluid and semisolid material can include but is not limited to silicones, gel, caulking joint material or other can not
Compression or almost incompressible material, or these materials are suitable for the combination of composite manufacturing.Pouch can include and cored wire knot
Cooperation industry and can by when cored wire tenses be pressed into change the content of pouch make pouch expand plunger, thus draw
Send out the crushing in the region of pouch of composite blading.Selectively, filler can also be it is single or with it is as described above
Fluid and semi-solid filler combine small solid metal or ceramic member.Collided in composite blading with enough power to discharge
After a part for blade, another exemplary unrestricted model of crushing utilizes the energy dissipation structure with cored wire and pouch
Part, cored wire are pulled through the structure of composite blading, activate pouch and expand pouch, thus crush composite blading structure.
Energy dissipation component including cored wire and the non-restrictive example for destroying initiator can be at least partially covered with de-
Mould agent, film or coating are with by being easy to initial sliding of the component in composite blading or motion to help component dissipation energy.It is de-
Mould agent can include but is not limited to the registration mark of Henkel companiesEUROCOAT, DuPont registrar
Mark(polytetrafluoroethylene (PTFE)) or other appropriate releasing agents for manufacturing composite.
The including but not limited to any combinations of the composite blading member of energy dissipation component, cored wire and destruction initiator, bag
The all changes of the position of any element, material, manufacture, shape, size, cross section property and length characteristic are included, can be adapted to use
It is aligned in energy dissipation, crushing and track.The invention further relates to the method for manufacturing composite blading.Moreover, it relates to
Frangible or composite blading is assembled into rotary machine and for rotary machine.This method can utilize as described above compound
Any combinations of blade element.
Turning now to Fig. 9, Fig. 8 exemplary embodiment is illustrated at released state, similar to reference to respectively by outer
Come thing or discharge blade free portion collision after release blade R and posterior leaflet T when it is as above described in figures 4-7.
As illustrated, when composite blading may collide, cored wire 82 can be tightened up or stretch.Apply to this strain of cored wire from release
Part extracts kinetic energy, composite blading 40 reduce that adjacent composite blading 40 or blower-casting 16 will be subjected to and need to bear rushes
Hit energy.With applying to the strain of cored wire 82, the release of composite blading 40 partly passes through the internal structure of composite blading 40
Co-curing cored wire 82 is pulled, reduces the kinetic energy of release part again while member-retaining portion and the release portion of crushing vane 40
Point.Selectable initiator 84 of destroying helps to discharge the crushing of part, and major part can be resolved into have it is lower
Two or more parts of single kinetic energy.
Figure 10 is another exemplary embodiment of composite blading 40, again with root 42, tip 44, leading edge 46 and after
Edge 48, the span 52 of blade 40 reach tip 44 from the radially distant end of root 42, and shaft orientation string 54 is from leading edge 46 backward to trailing edge
48.Again, internal flow path 50 can along string 54 being limited radially above in the span in root 42, and represent the span
52 will bear the minimum radial component of exotic collision accident.In this exemplary embodiment, composite blading 40 has five
Energy dissipation component 80.Each energy dissipation component 80 has at least one cored wire 82, and at least a portion of cored wire 82 is positioned at multiple
The outside of hing straps 40.The radial direction close end of cored wire 82 is attached to rotor 20, and then the length of cored wire 82 is radially distally advanced
Through root 42, to enter through internal flow path 50 in the span 52, can join in this cored wire 82 at its radially distant end portion
It is connected to and destroys initiator 84, in the exemplary embodiment for destroying initiator 84.Five energy dissipation components 80 are in the example
Shown in property embodiment, but any amount of component 80 can also be used.
Exemplary corruption initiator 84 as described in Figure 10 composite blading 40 figure 11 illustrates.This is exemplary broken
Bad initiator 84 has pouch 90, plunger 92, and can be at least partially filled with filler 94.The shape and chi of pouch 90
It is very little to may be adapted to there is any appropriate size, shape and structure to meet the office of the composite blading 40 in the region set by it
Contouring and size, shown construction is only for the purposes of illustration.Cored wire 82 can pass through pouch 90 and could be attached to post
Plug 92.At least a portion of energy dissipation component 80 can be demolded agent 96 and coat.In this exemplary embodiment, the He of pouch 90
At least a portion of the outside of cored wire 82 can cover the beginning to promote separation and crush with releasing agent 96.The periphery of plunger 92
It may be adapted to meet the pouch 90 in " before accident " position, not yet collided in this blade 40 with foreign object damage to energy dissipation structure
The degree that part 80 has been activated.
Figure 12 as Figure 10 sectional view depicts pouch 90, plunger 92 and the cored wire 82 of accident front position.Compound
In the accident that blade 40 can be collided by exotic, the energy being applied on composite blading 40 can cause a part for blade 40
Release.If the accident occurs, cored wire 82 and plunger 92 can be activated.When the release part of blade 40 is drawn in relative destruction
Send out the footpath of device 84 proximally and punished radially away from the position of the radial direction close end that could be attached to rotor 20 of related cored wire 82
From when, the activation can occur.Once being collided with the power that blade 40 can be caused to separate, then the release part of blade 40 can transport
Move radially away from rotor 20.However, the end that could be attached to rotor 20 of related cored wire 82 can not be with the blade part of release
Divide and move together, this may cause the relative fortune between the end for the cored wire 82 for being attached to rotor 20 and the release part of blade 40
Dynamic, the release part of blade 40 can include the radially distant end portion that could be attached to destruction initiator 84 of cored wire 82.This is relative
Motion can make it that be attached to the cored wire 82 for destroying initiator 84 is proximally pulled in " after accident " position by substantially radial, such as
Shown in Figure 10 sectional view 13.
When after plunger 92 is drawn into accident in position, plunger 92 can compress any filler 94 in pouch 90.
Because the periphery of plunger 92 can meet pouch 90, pouch can be filled with incompressible filler 94, be applied by plunger 92
Power on filler 94 is passed in pouch 90, thus expands pouch 90.When pouch 90 may be embodied in composite blading
When in 40, this expansion also expands composite blading 40.In addition, being aided in using the selectivity of releasing agent 96, separated region can be with
Formed in the composite blading for being adjacent to destruction initiator 84.Expansion and the separated region of composite blading 40 are it is possible thereby to crush simultaneously
And weaken blade 40.Crush the form of the leafing that can take composite construction, fracture fiber, fracture matrix etc..Which reduce load
The quantity of lotus load bearing complex structure and the intensity for thus reducing the composite for crushing opening position and surrounding.In the operation phase
Between, because composite blading is under high centrifugal load, this intensity reduces may be by being distributed in the smaller of blade 40 by load
Cause the further damage of composite blading 40 on section.This can ultimately result in the separation of the other part of blade 40 and release
Put.
This weakening or crushing of composite blading 40 can be by the energy dissipation structures being each activated in composite blading 40
Part 80 repeats.By axial location and radial position of the energy dissipation component 80 in composite blading 40 that interlock, powder can be produced
Broken sequence and combination.This can be by placing energy-absorbing member with the thickness of change in composite blading section and passing through
Change the size and dimension for destroying initiator 84 to adapt to the local geometric differences in shape of these thickness and opening position to realize.This
Outside, in energy dissipation component 80, one or more destruction initiator 84 can be used and can be along cored wire 82 in series
Distribution.In addition, in energy dissipation component 80, cored wire 82 can have between the destruction initiator 84 of series arrangement relaxation or
Extra length, when cored wire 82 is dragged passes through composite blading 40, flaccid part can crush composite blading 40, and can prolong
The activation for the destruction initiator 84 that can be arranged in series late.Five energy dissipation components 80 show in this exemplary embodiment,
But any amount of component 80 can be used.
Referring now to Figure 14, the side cross-sectional view of another exemplary embodiment of composite blading 40, again with root
42nd, tip 44, leading edge 46 and trailing edge 48, the span 52 of blade 40 reach tip 44, shaft orientation string 54 from the radially distant end of root 42
From leading edge 46 backward to trailing edge 48.Again, internal flow path 50 can along string 54 in root 42 radially above in the span
Middle restriction, and represent the span 52 will bear the minimum radial component of exotic collision accident.
In Figure 14 exemplary embodiment, the span 52 of composite blading 40 can radially be divided into three release areas,
Low span region 60, middle span region 62 and high span region domain 64.There can be one or more in each release areas
Cavity, it is identified as merely for exemplary purpose in size, shape, structure and positioning and is used for low span region 60 as shown in Example
60A, 60B, 60C, for the 62A and 62B of intermediate region 62, and 64A and 64B for high span region domain 64.These are empty
Chamber can lack filler or be optionally filled with resin, foam, pourable medium etc..Cavity 60C, 62B and 64B radial direction
Near-end rib includes one or more flanges 66 that the passage 68 of the cavity adjacent with being connected matches.Similarly, cavity 62A and 64A
Passage 68 including connecting adjacent cavity.Three energy dissipation components 80 can be located at the inside of composite blading 40 and with it is compound
Blade 40 is co-curing, and extends radially to tip 44 from root 42, through passage 68 and flange 66 and can be along string
54 not overlappingly axially distributions.Selectable initiator of destroying can couple at flange 66 and in the nested inner of flange 66
To cored wire.
Release areas cavity is combined and worked with energy dissipation component and destruction initiator, seeks balance blade along blade
The radial direction span impact resistance and fragility.When exotic utilizes the high span of enough energy in cavity 64A region
When colliding composite blading 40 at region 64 to separate whole high 64 part of span region domain of composite blading 40, through cavity 64B's
The energy dissipation component 80 of flange 66 and passage 68 will be tightened up, as shown in Figure 9, reduce the kinetic energy of release part.It is nested in
Destruction initiator inside flange 66 will also be drawn across flange 66 and passage 68 and will release part be ground into one with
On fragment or part, each has lower independent kinetic energy.However, for present exemplary, other two can not be tensed
Individual energy dissipation component 80 because its can radially closer to release (whole high span region domain 64) part of composite blading 40,
And the integrality of low span region 60 and middle span region 63 to collision is not therefore reduced.With multiple energy dissipation component knots
The radial distribution of the release areas cavity of conjunction provides the fragility in the region radially away from collision area, but remains close to and touch
Hit the impact resistance in the region in region.Three energy dissipation components 80 are shown in this exemplary embodiment, but can be used
Any amount of component 80.Similarly, three span regions and seven cavitys are shown, but can use any number of region,
Cavity, flange and passage.
Turning now to Figure 15, the side view of another exemplary embodiment of composite blading 40, it may have root 42, tip
44th, leading edge 46 and trailing edge 48, the span 52 of blade 40 reach tip 44 from the radially distant end of root 42, elapsed from leading edge 46 to rear
The shaft orientation string 54 of edge 48.Again, internal flow path 50 can along string 54 being limited radially above in the span in root 42,
And represent the span 52 will bear the minimum radial component of exotic collision accident.Composite blading 40 has single energy dissipation
Component 80, overlappingly not extend radially to tip 44 from root 42 from leading edge 46 to the alternative form of trailing edge 48.For energy
The other exemplary alternative form of dissipation component 80 can start at rotor 20 or root of blade 42, along the span 52 radially
Distally extend, with spirality path through string 54 to vane tip 44, and change in the depth through the thickness of blade 40.
Other exemplary alternative form for energy dissipation component 80 can brokenly be interlocked along the string of the span and blade 40,
And it can be formed at least when energy dissipation component 80 can extend to tip 44 from root 42 or the radially distant end of rotor 20
One selectable bent portion 86.The example energy dissipation component 80 can be located at the inside of composite blading 40 and with it is compound
Blade 40 is co-curing.The embodiment of energy dissipation component 80 can be described in exemplary embodiment as above in fig. 8
Cored wire.In this prior in embodiment, compared with it will extend directly to the short length at tip 44 from root 42, alternative form can be with
Relaxation or extra length are provided to component 80.When foreign object damage collides composite blading 40, the portion being released of blade 40
Divide partially radially and proximally will pull component 80 from release, reduce the kinetic energy of release part.In addition, as described below, energy
The setting of amount dissipation component 80 and the track for discharging part that can staggeredly change composite blading 40.Single energy dissipation component 80
Show in this exemplary embodiment, but any amount of component 80 can be used.
Aircraft 100 in reference picture 2, there is the contraprop gas turbine being arranged on aircraft 100 to start for it
Machine 110, also referred to as open rotor, if a part for propeller discharges from blower module 116, there may be the portion of propeller
The possibility of airframe may be collided by dividing.As described above, setting and interlock general of the energy dissipation component in composite blading 40
Adjust the track of the release part of composite blading 40.The improvement is probably favourable, because it may want to guiding release part
Include away from adjacent composite blading 40 or potentially the aircaft configuration of airframe.
Figure 16 to 19 and Figure 20 to 23 depicts track improvement.Accompanying drawing using reference vanes sequential (Figure 16-19) and
The separated sequential (Figure 20-23) of the exemplary embodiment of composite blading 40 of the description with modification track.As detailed in Fig. 4-7
One of the sequential stated, the airfoil in each in Figure 16-19 is indicated using letter r, identifies as discharging airfoil, separately
One is indicated using tee, identifies as trailing aerofoil part.Sequential from description just with exotic collide after the release wing
Figure 16 of type part and trailing aerofoil part in initial conditions starts.Then, in fig. 17, discharging a part of of airfoil can court
Posteriorly airfoil moves, and the radial direction close end of part rotates towards trailing aerofoil part not yet influences trailing aerofoil part.Then exist
In Figure 18, although any other part of release airfoil can collide rear portion airfoil, the footpath of part is discharged proximally
Portion can collide rear portion airfoil, distort the shape of trailing aerofoil part.Finally, in Figure 19, the release part of airfoil is discharged
Continue to collide and trailing aerofoil part is further distorted.Kinetic energy and the rear portion wing depending on the release part of release airfoil
Contact position on type part, this distortion may cause the destruction of trailing aerofoil part.
By contrast, as depicted in figs. 20-23, the exemplary embodiment of the composite blading 40 from Figure 15, which is in, has again
It is denoted as R release blade and is similarly denoted as in the T position of adjacent rear blade, repeats the sequential.Sequential is again
Since the release blade after description is just collided with exotic and in Figure 20 of the posterior leaflet of initial conditions.However,
In Figure 20, the release part for discharging blade is restricted to the member-retaining portion of release blade by energy dissipation component 80.Then, exist
In Figure 21, when the radial direction close end of part is limited to member-retaining portion by energy dissipation component 80, the release portion of blade is discharged
Divide and moved towards posterior leaflet.In figure 21, energy dissipation component 80 as described above has the pine provided in composite blading 40
The alternative form of relaxation or extra length.When the kinetic energy for discharging part makes the part be moved from member-retaining portion radially distant end, energy
Flaccid part in amount dissipation component 80 can be pulled through along the preferred orientations of the track of the release part relative to alignment
Part is discharged, while reduces the kinetic energy of release part.When radially distant end motion is continued in release part, in energy dissipation component 80
Flaccid part can utilize with member-retaining portion keep be directed at release part reduction, as shown in figure 22.Finally, as shown in figure 23,
When the flaccid part in energy dissipation component 80 is consumed, component 80 can be destroyed, and release part is continued on alignment path, is subtracted
It is small release part kinetic energy and avoid posterior leaflet.The principle of uniformity can be used for release part being limited to preferential alignment master
To be the release part at rear portion, away from aircraft 100 and neighbouring aircaft configuration.
The above-mentioned example embodiment of composite blading 40 can be used in rotary machine, including but not limited to exhausting wind
Fan, open rotor, turbo-propeller gas-turbine unit and bank base gas turbine, the count range of blade 40 are included but not
It is limited to from about 2 to about 24, from about 8 to about 16, in addition from about 10 to about 14.These examples of composite blading 40
Property embodiment the span 52 can include but is not limited to about 20 inches to about 90 inches, from about 40 inches to about 70
Inch and from about 50 inches to about 70 inches in the range of.The string 54 of these exemplary embodiments of composite blading 40 can
With include but is not limited to about 5 inches to about 40 inches, from about 10 inches to about 30 inches and from about 12 English
In the range of very little to about 24 inches.
Figure 24 shows an Example non-limiting procedures 500 for manufacturing frangible laminate, and a non-restrictive example is frangible
Laminate can be composite blading 40.The process 500 can include being constructed by resin and reinforcement material 502 strengthening polymeric matrix
Substantially unidirectional pre--dipping (pre-preg) process.Reinforcement material can take fiber, rove, pad, braiding rove, braiding yarn,
The form of braid or stitch bonded fabrics.Resin is as liquid offer at room temperature or can be heated to liquid.Then, armature
Material is impregnated using resin to form reinforcement polymeric matrix.Can be by injection, dip-coating, bonding or similarly on reinforcement material
The dipping being also referred to as sized is realized with one or more layers or dimensioning step resin deposition.Non-limiting example is conduct
Utilize the carbon fiber of the unidirectional reinforcement material of epoxy resin dipping.Other exemplary unrestricted resins include polyether-ether-ketone
(PEEK), PEKK (PEKK), polyphenylene sulfide (PPS), polyamide-imide (PAI) and PEI (PEI), Yi Jiju
Ester, phenolic aldehyde, vinyl esters, polyurethane, silicones, polyamide, polyamidoimide etc..Some in these resins can pass through
With reference to the dispersed elastomeric body of for example, elastomer rubber or thermoplastic for being dispersed in resin etc. and by toughening.
In Example non-limiting procedures 500, lamination process (lay-up process) can be then performed.Placement process
Multiple thin layers 504 are cut into including polymeric matrix will be strengthened.As used in this specification, term thin layer refers to
The part of complete flaggy, flaggy section and flaggy in shape and band.Then thin layer and at least one heap of energy dissipation component 80
Fold to produce laminate 506.One or more energy dissipation components 80 can be arranged on the opening position of change in laminate, and can
Positioned at the inside of laminate or to be positioned partially at the outside of laminate, such as the exemplary embodiment institute of composite blading in Fig. 10
Show.The process can also include ultrasonic assistant sewing process, wherein, reinforcing fibre is inserted through multiple flaggies, overall
The upper quality for improving laminate.Lamination process is additionally may included in stack thin layer and energy dissipation component 80 before and period make it is thin
Layer shaping.When compared with cutting flaggy using manual dexterity and labour and constructing and make traditional lamination process that thin layer shapes
When, machine placement process can save labour cost.
Finally, the process can utilize consolidation process so that laminate shapes and solidified so as to produce composite blading 508.Consolidation
Process using consolidation force so that laminate and its thin layer are pressed into required shape, and can be lamination process a part and can
To perform on the spot.One non-restrictive example is autoclave process, its laminate is placed in high-pressure installation so that laminate shaping and
Solidification.Appropriate autoclave temp is included from about 400 ℉ to about 840 ℉, preferably from about 600 ℉ to about 760 ℉
Temperature.
This specification discloses the present invention, including preferred embodiment using example, and also enables those skilled in the art
Implement the present invention, including manufacture and using any device or system and the method for performing any use.The present invention's obtains
The scope of patent is defined by the claims, and may include other examples that those skilled in the art expect.If these its
His example has and does not have the structural detail of difference with the word wording of claim, or these other examples include and power
Profit require equivalent structural elements of the word wording without substantive difference, then these other examples be intended to fall under the scope of claim
It is interior.The aspect of illustrated each embodiment and can be by this area for each other known equivalents in terms of these
Those of ordinary skill is combined and matched, and additional embodiment and technology are built with the principle according to the application.
Claims (30)
1. a kind of airfoil, including：
Composite blading (40), the composite blading (40) have root (42), sophisticated (44) and positioned at the span between the two
(52), leading edge (46), trailing edge (48) and positioned at string (54) between the two, and include at least the one of at least one pouch (90)
Individual energy dissipation component (80).
2. airfoil according to claim 1, it is characterised in that at least one energy dissipation component (80) is along institute
State the span (52) extension and be distributed along the string (54), at least one energy dissipation component (80) includes at least one
Cored wire (82).
3. airfoil according to claim 1, it is characterised in that at least one energy dissipation component (80) at least portion
Divide ground covered with releasing agent (96).
4. airfoil according to claim 1, it is characterised in that at least one energy dissipation component (80) with it is described
Composite blading (40) is co-curing at least in part.
5. airfoil according to claim 1, it is characterised in that at least one energy dissipation component (80) also includes
At least one destruction initiator (84), wherein, at least one cored wire (82) is attached at least one destruction initiator
(84)。
6. airfoil according to claim 5, it is characterised in that at least one destruction initiator (84) includes described
At least one pouch (90).
7. airfoil according to claim 6, it is characterised in that at least one destruction initiator (84) includes being suitable to
Meet at least one plunger (92) of at least one pouch (90).
8. airfoil according to claim 7, it is characterised in that at least one plunger (92) be attached to it is described at least
One cored wire (82), at least one pouch (90) are at least partially filled with filler (94).
9. airfoil according to claim 8, it is characterised in that at least one plunger (92) with it is described at least one
Cored wire (82) is with reference to operation so that the pouch (90) expansion, thus crushes the composite blading (40).
10. airfoil according to claim 1, it is characterised in that when release part and the institute of the composite blading (40)
The pouch (90) is activated when stating composite blading (40) separation.
11. a kind of method (500) for manufacturing frangible laminate, the described method comprises the following steps：
Construction strengthens polymeric matrix (502),
The reinforcement polymeric matrix is cut into multiple thin layers (504),
Laminate (506) is formed via the multiple thin layer of stacking and at least one energy dissipation component, and consolidates the laminate
(508)。
12. according to the method for claim 11, it is characterised in that the reinforcement polymeric matrix includes resin, wherein, institute
State resin and be selected from the group being made up of following material：Polyether-ether-ketone, PEKK, polyphenylene sulfide, polyamide-imide, polyetherimide
Amine, epoxy resin, polyester, phenolic aldehyde, vinyl esters, polyurethane, silicones, polyamide and polyamidoimide.
13. according to the method for claim 11, it is characterised in that the reinforcement polymeric matrix includes stiffener, wherein,
The stiffener is selected from the group being made up of following material：Glass, graphite, aramid and organic fiber.
14. according to the method for claim 11, it is characterised in that the multiple thin layer includes multiple flaggies.
15. according to the method for claim 11, in addition to the laminate is set to be configured to final products.
16. according to the method for claim 11, it is characterised in that consolidate the laminate and be additionally included in autoclave and consolidate institute
State laminate.
17. according to the method for claim 11, it is characterised in that the laminate includes blade (18).
18. according to the method for claim 12, it is characterised in that the resin also includes toughening material, wherein, it is described tough
Change material and be selected from the group being made up of elastomer rubber and thermoplastic.
19. according to the method for claim 17, it is characterised in that the reinforcement polymeric matrix includes resin, wherein, institute
State resin and be selected from the group being made up of following material：Polyether-ether-ketone, PEKK, polyphenylene sulfide, polyamide-imide, polyetherimide
Amine, epoxy resin, polyester, phenolic aldehyde, vinyl esters, polyurethane, silicones, polyamide and polyamidoimide.
20. according to the method for claim 17, it is characterised in that the reinforcement polymeric matrix includes stiffener, wherein,
The stiffener is selected from the group being made up of following material：Glass, graphite, aramid and organic fiber.
21. operating the method from crushing vane, the described method comprises the following steps：
The release part of composite blading (40) is discharged, the composite blading (40) includes at least one energy dissipation component (80)；
The release part is destroyed via at least one energy dissipation component (80)；
Optionally keep the member-retaining portion of the composite blading (40)；And
Optionally the member-retaining portion is destroyed via at least one energy dissipation component (80).
22. according to the method for claim 21, it is characterised in that at least one energy dissipation component (80) also includes
At least one cored wire (82).
23. according to the method for claim 21, it is characterised in that at least one energy dissipation component (80) also includes
At least one destruction initiator (84).
24. according to the method for claim 21, it is characterised in that at least one energy dissipation component (80) at least portion
Divide ground covered with releasing agent (96) and co-curing with the composite blading (40) at least in part.
25. according to the method for claim 23, it is characterised in that at least one destruction initiator (84) is included at least
One pouch (90).
26. according to the method for claim 25, it is characterised in that at least one energy dissipation component (80) also includes
At least one cored wire (82)；And at least one destruction initiator (80) includes being adapted to conform at least one pouch
(90) at least one plunger (92), wherein, at least one plunger (92) is attached at least one cored wire (82), institute
State at least one pouch (90) and be at least partially filled with filler (94).
27. according to the method for claim 21, it is characterised in that at least one energy dissipation component (80) extremely
Few one is attached to rotor (20).
28. the method according to claim 11, it is characterised in that the destruction step also includes destroying described at least
The composite blading structure of one energy dissipation component (80).
29. according to the method for claim 21, in addition to via at least one energy dissipation component (80) change institute
The track for stating release part causes the step of release part is along row predefined paths.
30. according to the method for claim 21, in addition to via at least one energy dissipation component (80) dissipation institute
The step of stating the kinetic energy of release part.
Applications Claiming Priority (7)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/596,804 US9828862B2 (en) | 2015-01-14 | 2015-01-14 | Frangible airfoil |
| US14/596804 | 2015-01-14 | ||
| US14/596,841 US9878501B2 (en) | 2015-01-14 | 2015-01-14 | Method of manufacturing a frangible blade |
| US14/596,815 US9243512B1 (en) | 2015-01-14 | 2015-01-14 | Rotary machine with a frangible composite blade |
| US14/596841 | 2015-01-14 | ||
| US14/596815 | 2015-01-14 | ||
| PCT/US2016/013419 WO2016115352A1 (en) | 2015-01-14 | 2016-01-14 | A frangible composite airfoil |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107407154A true CN107407154A (en) | 2017-11-28 |
| CN107407154B CN107407154B (en) | 2019-12-24 |
Family
ID=55272690
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201680005933.7A Active CN107407154B (en) | 2015-01-14 | 2016-01-14 | Fragile composite airfoil |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP3245387A1 (en) |
| JP (1) | JP2018508684A (en) |
| CN (1) | CN107407154B (en) |
| CA (1) | CA2972805A1 (en) |
| WO (1) | WO2016115352A1 (en) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110131210A (en) * | 2018-02-08 | 2019-08-16 | 通用电气公司 | Turbogenerator with composite blading |
| CN111059080A (en) * | 2018-10-16 | 2020-04-24 | 通用电气公司 | Fragile gas turbine engine airfoil including retention feature |
| CN111140539A (en) * | 2018-11-01 | 2020-05-12 | 通用电气公司 | Fragile gas turbine engine airfoil |
| CN111350693A (en) * | 2018-12-20 | 2020-06-30 | 通用电气公司 | Pretensioning and retaining structure for composite fan blade |
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|---|---|---|---|---|
| US3551070A (en) * | 1968-05-08 | 1970-12-29 | Dov Z Glucksman | Axial fan |
| GB2249592A (en) * | 1990-07-20 | 1992-05-13 | Gen Electric | Composite airfoil blade. |
| US6290895B1 (en) * | 1997-10-14 | 2001-09-18 | General Electric Company | Selectively flexible caul and method of use |
| US20070041842A1 (en) * | 2005-08-04 | 2007-02-22 | Thompson Ewan F | Aerofoil |
| EP2159379A2 (en) * | 2008-08-27 | 2010-03-03 | Rolls-Royce plc | Blade arrangement |
| US20110217160A1 (en) * | 2010-03-04 | 2011-09-08 | Rolls-Royce Plc | Component comprising a resin matrix |
| EP2365186A2 (en) * | 2010-03-04 | 2011-09-14 | Rolls-Royce plc | Improvements relating to layered composite components |
-
2016
- 2016-01-14 CA CA2972805A patent/CA2972805A1/en not_active Abandoned
- 2016-01-14 WO PCT/US2016/013419 patent/WO2016115352A1/en active Application Filing
- 2016-01-14 JP JP2017535663A patent/JP2018508684A/en active Pending
- 2016-01-14 EP EP16702283.9A patent/EP3245387A1/en not_active Withdrawn
- 2016-01-14 CN CN201680005933.7A patent/CN107407154B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3551070A (en) * | 1968-05-08 | 1970-12-29 | Dov Z Glucksman | Axial fan |
| GB2249592A (en) * | 1990-07-20 | 1992-05-13 | Gen Electric | Composite airfoil blade. |
| US6290895B1 (en) * | 1997-10-14 | 2001-09-18 | General Electric Company | Selectively flexible caul and method of use |
| US20070041842A1 (en) * | 2005-08-04 | 2007-02-22 | Thompson Ewan F | Aerofoil |
| EP2159379A2 (en) * | 2008-08-27 | 2010-03-03 | Rolls-Royce plc | Blade arrangement |
| US20110217160A1 (en) * | 2010-03-04 | 2011-09-08 | Rolls-Royce Plc | Component comprising a resin matrix |
| EP2365186A2 (en) * | 2010-03-04 | 2011-09-14 | Rolls-Royce plc | Improvements relating to layered composite components |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110131210A (en) * | 2018-02-08 | 2019-08-16 | 通用电气公司 | Turbogenerator with composite blading |
| CN111059080A (en) * | 2018-10-16 | 2020-04-24 | 通用电气公司 | Fragile gas turbine engine airfoil including retention feature |
| CN111059080B (en) * | 2018-10-16 | 2021-01-05 | 通用电气公司 | Fragile gas turbine engine airfoil including retention feature |
| CN111140539A (en) * | 2018-11-01 | 2020-05-12 | 通用电气公司 | Fragile gas turbine engine airfoil |
| CN111350693A (en) * | 2018-12-20 | 2020-06-30 | 通用电气公司 | Pretensioning and retaining structure for composite fan blade |
| CN111350693B (en) * | 2018-12-20 | 2021-10-22 | 通用电气公司 | Pretensioning and retaining structure for composite fan blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2972805A1 (en) | 2016-07-21 |
| WO2016115352A1 (en) | 2016-07-21 |
| EP3245387A1 (en) | 2017-11-22 |
| JP2018508684A (en) | 2018-03-29 |
| CN107407154B (en) | 2019-12-24 |
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