CN102770623A - Turbine or compressor blade - Google Patents
Turbine or compressor blade Download PDFInfo
- Publication number
- CN102770623A CN102770623A CN2010800521329A CN201080052132A CN102770623A CN 102770623 A CN102770623 A CN 102770623A CN 2010800521329 A CN2010800521329 A CN 2010800521329A CN 201080052132 A CN201080052132 A CN 201080052132A CN 102770623 A CN102770623 A CN 102770623A
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- China
- Prior art keywords
- blade
- load
- holder
- bearing member
- groove
- 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.)
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
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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
- 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
- F05D2230/00—Manufacture
- F05D2230/90—Coating; Surface treatment
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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
- F05D2260/00—Function
- F05D2260/30—Retaining components in desired mutual position
- F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
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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
Abstract
The invention relates to a blade for a turbine or a compressor, at least partially made of fiber-reinforced plastic, in particular carbon fiber reinforced plastic, being particularly durable under operating conditions. According to the invention, the blade (4) comprises a blade body (5) and a blade root (6). The blade body (5) is substantially made of a folded fabric web (7) made of fiber reinforced plastic, wherein a retaining loop (9) is formed in the area of the fold (8), and wherein a blade surface (11) is formed from the overlapping web ends (10). The blade root comprises a longitudinal beam (20) and at least two holders (25) for anchoring the blade (4) in a corresponding groove (3) of a rotor (2), said holders being preferably each fixedly connected to said beam at both ends. The blade body (5) is suspended on the beam (20) by means of the retaining loop (9).
Description
Technical field
The present invention relates to blade a kind of turbine or compressor.
Background technique
The blade of turbo machine comprises the blade that aerodynamics is crooked and comprises blade root on the other hand that this blade root is used for blade is anchored at the corresponding groove of rotor usually on the one hand.Equip vaned rotor and be called rotor assembly below.
Consider also now that carbon fiber-reinforced plastics (CFK) make the material of blade as new-type relatively being used to.Make the lower weight that for example advantageously causes blade by CFK.Yet disadvantageous is that CFK is unstable relatively for pressing load.This pressure stress is for example producing through the action of centrifugal force that is caused by rotation in groove inside in the zone blade root on the blade.
To this, for example by US 4,037, moving vane 990 known a kind of turbo machines, that process by fibrous composite.This moving vane is made up of a plurality of fibrous layers, and these layers constitute common ring on the end of its root side.At this, two in these rings are arranged for the formation blade root.For moving vane is fixed in the rotor disk, be provided with the bolt of fluting for a long time, the bolt element of this bolt extends through corresponding ring.Bolt head with can be tightened on this bolt end nut with vanes fixed be clamped in the axial groove of rotor.When turbo machine moved, because centrifugal action, fibrous layer was forced on the carrying side that keeps groove.Yet owing to, only can keep moving vane in this pressure stress that in these layers, occurs limitedly.In addition, by US 2,929,755 known a kind of moving vanes that are used for gas turbine, this moving vane has columniform, hard core in the root side, is provided with a plurality of by thread woven layer annularly around this core.Also constitute blade by these layers.Keep on core, being provided with sheet metal in the groove for moving vane is fixed on, these sheet metals abut on the side that keeps groove.Between two sheet metals, be provided with the packing material that is made of plastics, so that be filled in outmost layer and keep the free space between the channel profiles.
Summary of the invention
The objective of the invention is to, propose a kind ofly at least in part by fiber strengthened plastics, the blade that is used for turbine or compressor that especially CFK processes, this blade are especially durable, that is to say long service life.In addition, the objective of the invention is to, a kind of especially durable under operating conditions, rotor assembly of having basically the blade of being processed by fiber strengthened plastics is provided.
About blade, this purpose realizes according to the invention through the features of claim 1.To this, blade also comprises having blade root microscler or that sell the load-bearing member of shape except the blade of aerodynamics bending, and this load-bearing member is made of metal in preferred embodiment.In addition, blade root comprises at least two holders, wherein, these be preferably plate shape holder (directly making progress at it at least) fixed-site be connected on the load-bearing member.Each holder is configured for blade is anchored in the groove corresponding capitate or fir shape of rotor, and can abut on the sidewall of groove.
Blade is processed by the range upon range of laminated fabric breadth of being processed by fiber strengthened plastics, especially CFK basically, and this laminated fabric breadth (basically between these holders) is directed round load-bearing member.At this, two interconnect away from the outstanding breadth level land of load-bearing member respectively, to be used to form blade face.The part around the load-bearing member guiding of blade constitutes and is used for blade is suspended at the retaining ring on the load-bearing member.At this, aspect manufacturing technology, preferably propose, at first make the laminated fabric of blade (being blade face and retaining ring) that be used to be shaped, and the blade that will so process subsequently is sleeved on the load-bearing member.To this as an alternative, obviously laminated fabric also can be installed round load-bearing member, connects blade above that to be used to constitute and be shaped.
Under the assembling situation of the routine of blade, blade that is to say the groove that places rotor by the retaining ring together with being arranged on load-bearing member wherein of blade, and the blade of blade stretches out from groove with respect to rotor radial basically by its blade root.
Because blade is suspended on the load-bearing member by retaining ring, so the centrifugal force that is caused by rotation that acts on the blade absorbs through load-bearing member basically.Do not take place or only in the direct power transmission that occurs on the relatively little circumference between blade and the rotor.Therefore, blade in other words its laminated fabric overwhelming majority be under the tensile stress.
Press load or shear load because compare opposing, fiber strengthened plastics can more times of ground opposing pulling loads, thus blade and especially the FX that is the blade root form of blade be especially durable and long service life with respect to operating conditions thus.
Advantageously, use fiber strengthened plastics, especially CFK to make the possibility that blade has realized being configured in the especially favourable blade in aerodynamics aspect.Thus, this helps to reduce the energy input, the CO of energy input advantageously causing the again reduction of this reduction
2Generate.Because the lower weight of fiber strengthened plastics, the blade of this blade also can be greater than the blade of metal blade under the situation of the blade root of identical size.This has also realized the lifting of mass flow.
Each holder of blade root interconnects through at least one lateral wall piece in order to stablize blade root, and wherein, lateral wall piece is arranged essentially parallel to the load-bearing member orientation.
At this preferably, be provided with two lateral wall pieces, these lateral wall pieces are installed in respectively on each two side margin in the holder, and corresponding holder stretches out above blade with these side margin.Corresponding to this place, two lateral wall pieces are preferably fully mutually opposed with respect to load-bearing member.At this, especially and for example the installation of lateral wall piece is realized in this place, makes these lateral wall pieces contact laminating fabric web not in holder stretches out above the zone of blade at least.Avoided the pressure stress of the non-expectation in the laminated fabric breadth thus reliably.In trapezoidal holder, the lateral wall piece preferred immobilization makes the line of force on lateral wall piece, realize fully on two trapezoidal waists.This has greatly reduced the distolateral load that keeps groove, and therefore makes the load in rotor disk significantly become big surface of contact and homogenization based on passing through lateral wall piece.Therefore, be arranged on two claws between the adjacent maintenance groove and diminish, it is possible keeping groove compact space-saving layout in rotor thus.
In the especially preferred mode of execution of the present invention, each in the holder stretched out above blade on both sides with respect to the longitudinal extension of blade in the zone of load-bearing member at least basically with meeting at right angles.In other words, in this structure, holder stretches out above the laminated fabric breadth towards both sides in the zone of blade that suspends, and makes not contact with the respective side (groove side) of groove in laminated fabric the zone at least there.Therefore, mainly only through holder and do not abut on the groove side, make that only holder is through compression chord at the situation lower blade of centrifugal force through laminated fabric.This has been avoided pressure stress in the laminated fabric zone of root side, that when the laminated fabric contact groove side of root side, occur owing to centrifugal action.
Suitable is, each in the holder also stretched out above blade on the side of radially inner (the deviating from blade face) usually of blade, makes the laminated fabric breadth also contactlessly be suspended in the bottom land of rotor.
In another embodiment of the present invention; Blade root comprises that two especially are installed in the distolateral holder of load-bearing member; And at least one the 3rd holder, wherein, the 3rd holder load-bearing member vertically on be installed in two distolateral holders each and turn up the soil at interval and be positioned on the load-bearing member.Preferably, these additional holders that are provided with distribute on the length of load-bearing member equably.In this embodiment, blade is processed by a plurality of laminated fabric breadths aptly, and these laminated fabric breadths are suspended on the load-bearing member between two holders respectively, and thus the holder of central authorities be positioned at load-bearing member vertically on.In principle, the selection of blade center of gravity ground is depended in two fixed positions of holder on microscler load-bearing member, yet makes that the non-distolateral fixed position that is arranged in the load-bearing member end regions of holder also can be significant.
Preferably, each in the holder is provided with the penetrating part that the cross section with load-bearing member is complementary, and load-bearing member correspondingly accurately passes this penetrating part basically ordinatedly and inserts.Optional is load-bearing member and holder welding.
What suit is that lateral wall piece difference shape engages perhaps preferably to peg graft the material joint and perhaps is connected with holder with welding.
Preferably, the cross section of load-bearing member is shaped to round or leg-of-mutton basically.Under triangular shaped situation, preferred isosceles triangle especially has the isosceles triangle of rounded edge, and wherein, the seamed edge that is enclosed by two purses is especially approximately towards the blade face of blade.
Preferably, load-bearing member is provided with sliding layer in its surface, especially is provided with the layer of being processed by teflon.Thus, when in case of necessity, inner most laminated fabric breadth can slide with respect to load-bearing member.
In favourable mode of execution of the present invention, laminated fabric is the uniaxially structure basically, and wherein, laminated fabric has primary fibre direction, and this primary fibre direction is directed along the centrifugal force direction that is caused by operation basically.Thus, blade is especially stable for the pulling force that is produced.Additionally or as an alternative, laminated fabric three-dimensional through fiber in the zone of blade root or in the zone of load-bearing member interweaves and strengthens.
Suitable is that blade is provided with the corrosion protection layer at least in its surface in the zone of its blade face, the corrosion protection layer of especially perhaps being processed by the metallic thin film that is coated with hard material by particle composites.This layer also advantageously improved the repellence of blade for water intrusion.
About rotor assembly, the characteristic through claim 12 realizes above-mentioned purpose according to the present invention.So, rotor assembly comprises rotor, in this rotor, introduce at least one groove and aforementioned according to blade of the present invention at least one.Blade by its blade root fixed-site place groove.
Because the low relatively weight of the blade of being processed by fiber strengthened plastics basically, each that is arranged in the groove in the rotor advantageously constitutes relatively littlely.In addition, whole rotor assembly is advantageously light especially.Obvious is that if in the turbo machine of running load, should substitute the blade of being processed by metal or stainless steel fully according to blade of the present invention, blade root also can cross greatly with respect to blade and constitute so.
Preferably, groove is coordinated with holder each other, makes holder be supported on respectively on the side of groove.Holder fills up the groove cross section basically in suitable mode of execution.
Preferably, not only the cross section of holder but also groove is trapezoidally basically and constructs (" swallow tail shaped slot ").Other shape of cross sections, for example " fir shape " or semicircle also are possible for holder and groove cross-sectional profiles.
In suitable configuration of the present invention, the holder of blade is constructed identical from one anotherly, and wherein, groove has unified width and shape on its length.
In the preferred implementation of rotor assembly, this rotor assembly comprise a plurality of difference directed vertically basically, on circumference equally distributed groove, wherein, blade is especially correspondingly inserted in each groove and location there.To this as an alternative, in the rotor turbine rotor assembly or the compressor drum assembly, introduce circumferential groove, wherein, a plurality of blades are contained in this groove with arranging each other, and are fixed on the there.
Description of drawings
At length explain two embodiments of the present invention according to accompanying drawing below.Accompanying drawing illustrates:
Fig. 1 illustrates first mode of execution of the turbine rotor assembly with turbine blade with cross section, and this turbine blade comprises blade and blade root;
Fig. 2 illustrates the blade root according to first mode of execution with the exploded view of signal; And
Fig. 3 illustrates the blade root according to second mode of execution with the diagrammatic sketch according to Fig. 2.
Corresponding components is provided with identical reference character with parameter all the time in institute's drawings attached each other.
Embodiment
Fig. 1 illustrates turbine rotor assembly 1 with the sectional view of signal slightly.Turbine rotor assembly 1 comprises the rotor of being processed by stainless steel 2, and a plurality of axial grooves 3 are incorporated in this rotor with the mode that is evenly distributed on the circumference.The sectional view of rotor 2 in the zone of single axial groove 3 only is shown in Fig. 1.In first mode of execution shown here, each axial groove 3 constitutes so-called swallow tail shaped slot basically.
In axial groove 3, accommodate turbine blade 4.This turbine blade 4 comprises blade 5 (only partly illustrating) here, and blade root 6, and this blade root is used for turbine blade is anchored at axial groove 3.
Blade 5 is processed by a plurality of stacked breadths of mainly being processed by unidirectional CFK laminated fabric 7.At this, breadth 7 preferably approximately builds up in central folding, makes to form retaining ring 9 in the zone of the kink 8 that when folding, produces.On the one side (top in the drawings) away from this retaining ring 9, these 10 level lands, breadth end are stacked each other, and wherein, they are " joint " under the situation of the blade face that is shaped to blade 5 11.Blade face 11 approximately stretches out from the axial groove 3 of rotor 2 diametrically.
The main fiber direction of CFK laminated fabric makes each graphite fiber 12 of CFK laminated fabric be arranged essentially parallel to the longitudinal section of blade 5 (basically also respectively under the situation that forms ring) orientation approximately along breadth 7 orientations.
Blade 5 covers with the corrosion protection layer on the surface 13 in its (under manufacturing state shown here) outside.To this alternatively, corrosion protection layer 14 only is arranged in the zone of blade face 11.
Each holder 25 has circular penetrating part 26 at about its face center, and metal-cored 20 accurately are inserted in this penetrating part basically ordinatedly, and wherein, these holders 25 approximately stretch out above metal-cored with respect to metal-cored 20 with meeting at right angles.
On two waists 27 of each holder 25, the recess 28 of each edge side is introduced in the said waist.These recesses 28 are used for fixing 30, two holders 25 of two lateral wall pieces and under assembling condition, on these waists 27, are connected with these lateral wall pieces respectively.
Each lateral wall piece 30 is made up of rectangle, microscler steel plate basically.Each lateral wall piece 30 has ridge 32 on side 31, this ridge extends on the whole length of corresponding lateral wall piece 30 respectively.At this, ridge 32 respectively with recess 28 moulding complementally, make that lateral wall piece 30 can be by ridge 32 fixed position in recess 28.
In addition, each lateral wall piece 30 has the edge 33 of the longitudinal side of bending a little.At this, each lateral wall piece 30 is sized to, and makes the straight part of side 31 have width b, and this width is approximately corresponding to the long L of the waist of holder 25.Under assembling condition, lateral wall piece 30 is respectively on both sides installation, two waists 27 of preferred weld at two holders 25.By approximately being provided with trapezoidal long limit 35 with edge 33 opposed side margin 34, wherein, the edge 33 of bending stretches out above waist 27 on trapezoidal minor face 36 respectively lateral wall piece 30 with flushing respectively.
Can see that by Fig. 1 the edge 33 that exceeds is used under assembling condition, on tangential direction, keeping blade 5 basically.
In addition; Can see by Fig. 1; The size of the mean breadth B (Fig. 2) of each in the holder 25 even as big as make holder metal-cored 20 or the zone of retaining ring 9 in be substantially perpendicular to blade face 14 ground and stretch out in both sides above blade 5, promptly especially also surpass laminated fabric breadth 7 respectively.
Thus, especially radially metal-cored 20 or the height of retaining ring 9 on, do not exist in the contact between lateral wall piece 30 and the CFK laminated fabric breadth 7.Thus, even do not produce under (radially in rotor effect) the centrifugal force F effect that in this zone, when turbine rotor assembly 1 operation, produces the disadvantageous pressure of CFK laminated fabric is not loaded yet.
Therefore when operation, blade 5 is directed along centrifugal force F, and blade 5 is similar to and only is under the pulling load thus, and the CFK laminated fabric is especially also because the said pulling load of the special opposing of favourable main fiber direction.
In the mode of execution shown here, two lateral wall pieces 30 weld with rotor 2 in axial groove 3.
Shown in Fig. 3 according to the blade root 6 of second mode of execution of turbine rotor assembly 1 or turbine blade 4.This second mode of execution is basically corresponding to first mode of execution.Different therewith ground, blade root 6 here have in order more advantageously to eliminate load the 3rd holder 25, the three holders metal-cored 20 vertically on approximately be arranged on central authorities.This central holder 25 is similar to distolateral holder 5 ground structure, and wherein, metal-cored 20 pass penetrating part 26 inserts.
Blade 5 is made up of breadth 7 divided into two parts at this.In the zone of retaining ring 9, breadth 7 respectively metal-cored 20 vertically on be arranged between these holders 25, wherein, said breadth also is used for the holder 25 of axial restraint central authorities except the blade 5 that is used to suspend.
Also can consider to have four perhaps mode of executions of more holders 25.
Claims (15)
1. the blade (4) that is used for turbine or compressor comprises blade (5) and blade root (6),
-wherein; Said blade (5) is processed by folding laminated fabric breadth (7) basically, and said laminated fabric breadth is processed by fiber strengthened plastics, wherein; In the zone of kink (8), constitute retaining ring (9); And wherein, by mutually stacked breadth end (10) shaping blade face (11)
-wherein; Said blade root (6) comprises microscler load-bearing member (20); And at least two respectively with said load-bearing member fixed-site ground holder (25) that be connected, that be used for said blade (4) is anchored at the corresponding groove (3) of turbine rotor assembly (1), and
-wherein, said blade (5) is suspended on the said load-bearing member (20) by said retaining ring (9),
It is characterized in that each is used for stable said holder (25) and interconnects through at least one lateral wall piece (30), and wherein, said lateral wall piece is arranged essentially parallel to said load-bearing member (20) orientation.
2. blade according to claim 1 (4), wherein, each in the said holder (25) in the zone of said load-bearing member (20) at least substantial lateral stretch out in both sides in the longitudinal extension ground of said blade (5) and surpass said blade.
3. blade according to claim 1 and 2 (4); Have the 3rd holder (25) that at least one is used for being anchored at corresponding groove (3), said the 3rd holder is turned up the soil at interval in vertical each that goes up and especially be installed in distolateral two holders (25) of said load-bearing member (20) and is positioned on the said load-bearing member (20).
4. according to the described blade of one of claim 1 to 3 (4), wherein, said lateral wall piece (30) shape engages or material is connected with said holder (25) with engaging.
5. according to one of aforesaid right requirement described blade (4), said blade has two lateral wall pieces (30), and said two lateral wall pieces are installed in respectively on the side margin (27) that stretches out two zones that surpass said blade (5) of said holder (25).
6. according to the described blade of one of claim 1 to 5 (4), wherein, the cross section of said load-bearing member (20) is configured as circular or triangle basically.
7. according to the described blade of one of claim 1 to 6 (4), wherein, said load-bearing member (20) is made of metal.
8. according to the described blade of one of claim 1 to 7 (4), wherein, said load-bearing member (20) is provided with sliding layer (22) on its surface (21).
9. according to the described blade of one of claim 1 to 8 (4), wherein, said laminated fabric (7) is the uniaxially structure basically, and wherein, the primary fibre direction of said laminated fabric is farthest directed along the centrifugal force direction that is caused by operation.
10. according to the described blade of one of claim 1 to 9 (4), wherein, said blade (5) is provided with corrosion protection layer (14) at least in part on its surface (13).
11. according to the described blade of one of claim 1 to 10 (4), wherein, said fiber strengthened constructed in plastic material is carbon fiber-reinforced plastics (CFK).
12. rotor assembly (1); Has rotor (2) and at least one is according to the described blade of one of claim 1 to 11 (4); In said rotor, introduce at least one groove (3), wherein, the blade root (6) of said blade (4) is inserted in the said groove (3); And wherein, said blade root is positioned in the said groove (3) with said rotor (2) with being connected.
13. rotor assembly according to claim 12 (1), wherein, said holder (25) and/or said lateral wall piece (30) are supported on the side of said groove (3).
14. according to claim 12 or 13 described rotor assembly (1), wherein, said holder (25) fills up the groove cross section basically.
15. according to the described rotor assembly of one of claim 12 to 14 (1), wherein, not only said groove (3) but also said holder (25) are configured to trapezoidal basically.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP09014381A EP2322763A1 (en) | 2009-11-17 | 2009-11-17 | Turbine or compressor blade |
| EP09014381.9 | 2009-11-17 | ||
| PCT/EP2010/067581 WO2011061192A1 (en) | 2009-11-17 | 2010-11-16 | Turbine or compressor blade |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102770623A true CN102770623A (en) | 2012-11-07 |
| CN102770623B CN102770623B (en) | 2015-01-07 |
Family
ID=42062015
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201080052132.9A Active CN102770623B (en) | 2009-11-17 | 2010-11-16 | Turbine or compressor blade and rotor component |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US20120230829A1 (en) |
| EP (2) | EP2322763A1 (en) |
| JP (1) | JP2013510994A (en) |
| CN (1) | CN102770623B (en) |
| ES (1) | ES2530053T3 (en) |
| PL (1) | PL2501901T3 (en) |
| RU (1) | RU2517005C2 (en) |
| WO (1) | WO2011061192A1 (en) |
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| CN105874209A (en) * | 2013-11-30 | 2016-08-17 | 厄利孔莱博尔德真空有限责任公司 | Rotor disc and rotor for a vacuum pump |
| CN106812554A (en) * | 2015-11-10 | 2017-06-09 | 通用电气公司 | Turbo blade attachment means |
| CN110621849A (en) * | 2017-05-31 | 2019-12-27 | 三菱重工业株式会社 | Composite blade and method for manufacturing composite blade |
| CN112109341A (en) * | 2019-06-19 | 2020-12-22 | 三菱重工业株式会社 | Composite blade and method for forming composite blade |
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| US20110206522A1 (en) * | 2010-02-24 | 2011-08-25 | Ioannis Alvanos | Rotating airfoil fabrication utilizing cmc |
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| JP6121740B2 (en) * | 2013-02-13 | 2017-04-26 | 株式会社Ihi | Fan blade manufacturing method and manufacturing apparatus |
| EP2957775B1 (en) * | 2013-02-13 | 2017-10-04 | IHI Corporation | Method and device for manufacturing a turbofan blade |
| US9938930B2 (en) * | 2015-05-11 | 2018-04-10 | United Technologies Corporation | Composite wear pad for exhaust nozzle |
| US10443409B2 (en) * | 2016-10-28 | 2019-10-15 | Rolls-Royce North American Technologies Inc. | Turbine blade with ceramic matrix composite material construction |
| US10577939B2 (en) * | 2016-11-01 | 2020-03-03 | Rolls-Royce Corporation | Turbine blade with three-dimensional CMC construction elements |
| GB201803802D0 (en) | 2018-03-09 | 2018-04-25 | Rolls Royce Plc | Composite fan blade and manufacturing method thereof |
| GB201808939D0 (en) * | 2018-05-31 | 2018-07-18 | Rolls Royce Plc | Composite fan blade root |
| CN110454233A (en) * | 2019-08-08 | 2019-11-15 | 中国长江动力集团有限公司 | A kind of steam turbine is cultivated one's moral character the movable vane piece group of blade and its composition |
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| DE3826378A1 (en) * | 1988-08-03 | 1990-02-08 | Mtu Muenchen Gmbh | FIBER TECHNICAL PROPELLER BLADES |
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| GB0815475D0 (en) * | 2008-08-27 | 2008-10-01 | Rolls Royce Plc | A blade |
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2009
- 2009-11-17 EP EP09014381A patent/EP2322763A1/en not_active Withdrawn
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- 2010-11-16 US US13/510,295 patent/US20120230829A1/en not_active Abandoned
- 2010-11-16 WO PCT/EP2010/067581 patent/WO2011061192A1/en active Application Filing
- 2010-11-16 EP EP10782578.8A patent/EP2501901B1/en active Active
- 2010-11-16 CN CN201080052132.9A patent/CN102770623B/en active Active
- 2010-11-16 ES ES10782578.8T patent/ES2530053T3/en active Active
- 2010-11-16 RU RU2012124907/06A patent/RU2517005C2/en not_active IP Right Cessation
- 2010-11-16 PL PL10782578T patent/PL2501901T3/en unknown
- 2010-11-16 JP JP2012539305A patent/JP2013510994A/en active Pending
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| US4037990A (en) * | 1976-06-01 | 1977-07-26 | General Electric Company | Composite turbomachinery rotor |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105874209A (en) * | 2013-11-30 | 2016-08-17 | 厄利孔莱博尔德真空有限责任公司 | Rotor disc and rotor for a vacuum pump |
| CN106812554A (en) * | 2015-11-10 | 2017-06-09 | 通用电气公司 | Turbo blade attachment means |
| US10227880B2 (en) | 2015-11-10 | 2019-03-12 | General Electric Company | Turbine blade attachment mechanism |
| CN110621849A (en) * | 2017-05-31 | 2019-12-27 | 三菱重工业株式会社 | Composite blade and method for manufacturing composite blade |
| CN110621849B (en) * | 2017-05-31 | 2021-09-07 | 三菱重工业株式会社 | Composite blade and method for manufacturing composite blade |
| CN112109341A (en) * | 2019-06-19 | 2020-12-22 | 三菱重工业株式会社 | Composite blade and method for forming composite blade |
| CN112109341B (en) * | 2019-06-19 | 2022-06-21 | 三菱重工业株式会社 | Composite blade and method for forming composite blade |
Also Published As
| Publication number | Publication date |
|---|---|
| US20120230829A1 (en) | 2012-09-13 |
| EP2501901A1 (en) | 2012-09-26 |
| EP2322763A1 (en) | 2011-05-18 |
| EP2501901B1 (en) | 2014-12-31 |
| WO2011061192A1 (en) | 2011-05-26 |
| JP2013510994A (en) | 2013-03-28 |
| ES2530053T3 (en) | 2015-02-26 |
| RU2012124907A (en) | 2013-12-27 |
| PL2501901T3 (en) | 2015-05-29 |
| RU2517005C2 (en) | 2014-05-27 |
| CN102770623B (en) | 2015-01-07 |
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Effective date of registration: 20220908 Address after: Munich, Germany Patentee after: Siemens energy Global Ltd. Address before: Munich, Germany Patentee before: SIEMENS AG |