EP3274558A1 - Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel - Google Patents
Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufelInfo
- Publication number
- EP3274558A1 EP3274558A1 EP16716884.8A EP16716884A EP3274558A1 EP 3274558 A1 EP3274558 A1 EP 3274558A1 EP 16716884 A EP16716884 A EP 16716884A EP 3274558 A1 EP3274558 A1 EP 3274558A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- blade
- length
- skeleton
- skeleton line
- turbine
- 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
- 238000000034 method Methods 0.000 title claims abstract description 26
- 238000013016 damping Methods 0.000 description 11
- 230000006835 compression Effects 0.000 description 6
- 238000007906 compression Methods 0.000 description 6
- 230000035939 shock Effects 0.000 description 5
- 101710137710 Thioesterase 1/protease 1/lysophospholipase L1 Proteins 0.000 description 2
- RLQJEEJISHYWON-UHFFFAOYSA-N flonicamid Chemical compound FC(F)(F)C1=CC=NC=C1C(=O)NCC#N RLQJEEJISHYWON-UHFFFAOYSA-N 0.000 description 2
- 230000002238 attenuated effect Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 210000003608 fece Anatomy 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000003550 marker Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000004936 stimulating effect Effects 0.000 description 1
- 210000002435 tendon Anatomy 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/16—Form or construction for counteracting blade vibration
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
Definitions
- the invention relates to a method for profiling a turbine blade for an axial flow machine.
- the trend in the design of blades for an axial flow machine is to increase the aspect ratio of the blades and make the blades thinner.
- the blades designed in this way tend to flutter during operation of the axial flow machine.
- the flutter is a self-excited vibration at the natural frequency of the blade. This vibration may be a longitu dinalschwingung the blade with a node at the foot of the blade. In this case, energy is transferred from the fluid flowing in the axial flow machine to the blade.
- the flutter can lead to a material fatigue of the blade at a repeated load change of the axial flow machine (English: high cycle fatigue). Mate rialermüdung can lead to the formation of a crack and make a costly replacement of the blade required
- the object of the invention is to provide a method for profiling a blade for an axial flow machine in which the blade has little tendency to flutter.
- the inventive method for profiling a turbine blade for an axial flow machine comprises the steps of: providing a geometric model of a blade profile having a skeleton line of a profile section of the turbine blade; Setting Randbedin ⁇ conditions for the turbine blade flowing around Strö ⁇ tion; Changing the skeleton line such that the reference to the boundary conditions, adjusting flow causes the maximum of the difference of the isentropic Mach number between the pressure side and the suction side of the turbine blade in a blade ⁇ section which extends starting from the Schaufelhin ⁇ terkante toward the blade leading edge and 65% of the length S of the blade chord is long.
- the skeleton line is that line of the profile section, whose points have the same distance from the pressure side as from the suction side ha ⁇ ben.
- the blade chord is the distance in the pro ⁇ filschnitt of the blade leading edge to the blade trailing edge ⁇ .
- the skeleton line is preferably formed by a first fourth order polynomial describing the skeleton line of the scene ⁇ felvorderkante to an extreme point, and a second fourth order polynomial describing the skeleton line of the extreme point to the blade trailing edge, wherein the extreme point that point is the skeleton line that has the maximum distance to the blade chord.
- the distance be ⁇ records the length of a perpendicular from the bucket Tendon extending to the skeleton line.
- the first polynomial is formed under pre ⁇ pull a leading edge skeleton angle, the angle Zvi ⁇ rule of the leading edge tangent to the skeleton line and
- Vane chord is the length x S i from the blade leading edge to the point of the blade chord having the maximum distance to the skeleton line and the length Si which is the distance from the extreme point to the blade chord , forming the second polynomial is edge-skeleton angle while referring to a rear, which is the angle between the Schukan ⁇ tentangente the skeleton line and the blade chord, length, Sx S i of the vane trailing edge to the point of the blade chord, which has the maximum distance from the mean camber line, and the length S 2 , which is the distance from the skeleton line to the point of the blade chord, which is the distance
- the skeleton line is changed such that Si is from 10.3% to 11.3% of the length S, x S i is from 35.1% to 38.4% of the length S of the blade chord, S2 of 64.8% to 67.9% of the length Si, the Schukan- is skeleton angle of 15.192 ° to 19.020 ° and the Vor ⁇ derkantenskelettwinkel of 37.663 ° to 39.256 °. An ⁇ hand of these parameters is advantageously ensured that the blade has only a slight tendency to flutter.
- the skeleton line is preferably changed so that Si
- the turbine blade has a transonic portion and the skeleton line in the transonic section is varied so that Si is from 7.6874% to 7.9% of the length S, x S i is from 35.4311% to 36.2% of the length S, S2 is from 63% to 65% of the length Si, the back corner skeleton angle is from 11.0 ° to 12.3 ° and the front corner skeleton angle is from 29.0 ° to 31.0 °.
- These parameters cause log is established in the operation of the axial flow rotary far downstream in the boundary conditions Adjustab ⁇ lender compression shock and sets having a low Machieregradienten. A flapping turbine blade causes disturbances in the flow.
- the turbine blade is freestanding. This means that no damping elements are provided, such as a shroud.
- the geometrical model of the skeleton line itself has a long ent ⁇ varying thickness, which is maintained the same during the change of the skeleton line.
- the boundary conditions of the flow result from the nominal operating condition of the axial flow machine.
- it is preferred that it is a statio ⁇ nary flow.
- the isentropic Mach numbers are preferably experimentally determined and / or calculated. It is preferred that the method be repeated for different profile sections of the turbine blade. This results in a design of the turbine blade along its height.
- the profile section preferably lies on a cylindrical surface or a conical surface ⁇ , whose axes coincide with the axis of the axial flow rotary machine, on a S i - flow area or in a tangential plane of the axial ⁇ turbomachine.
- the axial flow machine is preferably a gas turbine or a steam turbine.
- the method is preferably carried out for profile sections which lie in the radially outer half of the turbine blade, in particular the method is carried out only for the profile cuts which lie in the radially outer half of the turbine blade.
- the turbine blade according to the invention for a Axialströ ⁇ mung machine has a blade profile having a skeleton line of a profile section of the turbine blade, wherein the skeleton line is shaped so that on the basis of boundary conditions for the turbine blade flows around flow which adjusting flow the maximum of the difference of the isentropic Mach number between the pressure side and the suction side of the turbine blade in a Schaufelab ⁇ section causes, starting from the
- Vane trailing edge extends toward the blade leading edge and 65% of the length S of the blade chord is long.
- the skeleton line is formed by ei ⁇ nem first fourth order polynomial describing the skeleton line of the vane leading edge to an extreme point, and a second fourth order polynomial having the Skelettli ⁇ never from the extreme point to the blade trailing edge be - writes, wherein the extreme point is that point of the skeleton ⁇ line, which has the maximum distance to the blade chord, wherein the first polynomial is formed using a Vorderkantenskelettwinkels, the angle between the Front edge tangent of the skeleton line and the blade chord is, the length x S i from the blade leading edge to the point of the blade chord, which has the maximum distance to the skeleton ⁇ line, and the length S i, the distance from the extreme point to the Vane chord, wherein the second polynomial is formed using a
- the trailing edge tangent of the skeleton line and the blade chord is, the length Sx S i from the blade trailing edge to the point of the blade chord, which is the maximum distance to the blade
- Skeleton line, and the length S 2 which is the distance from the skeleton line to the point of the blade chord, which has the distance x S i + 0, 5 * (Sx S i) from the blade trailing edge, where S is the length of the blade chord is.
- the skeleton line be such that S i is from 10.3% to 11.3% of the length S, x S i is from 35.1% to 38.4% of the length S, S 2 is from 64.8% to 67.9% of the length S i, the posterior skeletal angle of
- the turbine blade has a transonic section and the skeleton line in the transonic section is such that S i is from 7.6874% to 7.9% of the length S, x S i is from 35.4311% to 36 Is 2% of the length S, S 2 is from 63% to 65% of the length S i, the
- the axial flow rotary machine according to the invention includes a dung OF INVENTION ⁇ modern turbine blade, the turbine blade- ⁇ is detached and the axial flow rotary machine is from ⁇ particular a gas turbine or a steam turbine.
- FIG. 1 geometric model of a profile section
- FIG. 2 each show a profile section of a conventional turbine blade and a turbine blade designed in accordance with the invention
- FIG. 3 shows in each case a plot of an isentropic Mach number curve of a conventional turbine blade and a turbine blade designed according to the invention
- Figure 4 each have a damping performance based on a herkömmli ⁇ Chen and an inventively designed Turbi ⁇ nenlaufschaufel
- Figure 5 shows a thickness distribution of a profile section
- Figure 6 each have a damping performance based on a herkömmli ⁇ Chen and an alternative according to the invention being laid ⁇ turbine blade.
- Figure 1 shows a geometric model of a profile section of a turbine blade for an axial flow machine, which is for example a gas turbine or a steam turbine.
- the profile section is located for example on a cylinder der constitutional or a conical surface, whose axes coincide with the axis of the axial flow rotary machine, on a S i - flow area or in a tangential plane of the axial ⁇ turbomachine.
- the geometric model of a profile section of a turbine blade for an axial flow machine which is for example a gas turbine or a steam turbine.
- the profile section is located for example on a cylinder der constitutional or a conical surface, whose axes coincide with the axis of the axial flow rotary machine, on a S i - flow area or in a tangential plane of the axial ⁇ turbomachine.
- the geometric model of a profile section of a turbine blade for an axial flow machine which is for example a gas turbine or a steam turbine.
- Model a curved skeleton line 3 which is that line of the profile section whose points have the same distance from the pressure side as from the suction side of the turbine blade. Furthermore, it is apparent from Figure 1, that the turbine blade a blade leading edge 4 and a
- Bucket trailing edge 5 has.
- the blade leading edge 4 and the blade trailing edge 5 limiting the skeleton line 3.
- the Stre ⁇ bridge between the blade leading edge 4 and the Vane trailing edge 5 is the blade chord 13.
- the geometric ⁇ cal model is drawn in Figure 1 in a plot whose abscissa 1 coincides with the blade chord 13 and on the ordinate of the distance of the skeleton line 3 is applied by the blade chord 13.
- the distance refers to the length of a line extending at right angles from the blade chord 13 to the skeleton line.
- the coordinate system in Figure 1 is chosen such that the blade leading edge 4 coincides with the origin of the coordinate system.
- the blade trailing edge 5 lies in the point (S, 0), where S is the length of the blade chord 13.
- the skeleton line 3 is formed by a first polynomial 11 of the fourth degree and a second polynomial 12 of the fourth degree.
- the first polynomial 11 describes the skeleton line 3 from the blade leading edge 4 to an extreme point 30.
- the ext ⁇ remddling 30 is that point of the skeleton line 3, which has the maximum distance from the blade chord 13.
- the second polynomial 12 describes the skeleton line 3 from the extreme point 30 to the blade trailing edge 5.
- the pre ⁇ derkantentangente 7 includes the blade chord 13 is a front edges skeleton LESA angle a.
- FIG. 1 is the tangent of the skeleton line 3 on the blade trailing edge 5.
- the trailing edge tangent 8 includes with the blade chord 13 ei ⁇ nen Deutschenkantenskelettwinkel TESA.
- the first polynomial 11 is formed by selecting the leading edge skeleton angle LESA, the length x S i of the Schaufelvor ⁇ derkante 4 to the point (x S i, 0) on the blade chord 13, which has the maximum distance from the skeleton line 13, and the length S i, which is the distance from the point (x S i, 0) to the extreme point 30.
- the first polynomial 11 is sufficiently determined.
- the second polynomial 12 is formed by selecting the hind-corner skeleton angle TESA, the length S-Xsi from the blade trailing edge 5 to the point (x S i, 0) on the blade chord 13, and the length S 2 representing the distance from the point (x S i + 0, 5 * (Sx S i), 0) up to skeleton line 3. Because the slope of the extreme point 30 is zero and the blade trailing edge 5 lies in the point (S, 0), the second polynomial 12 is sufficiently determined.
- the geometrical model of the blade profile is provided, as described for FIG. It provides boundary conditions for a flow around the blade.
- the Randbedin ⁇ conditions can, for example, from the Nenn nowadayssbedin- account the axial flow result.
- the skeleton line 3 is changed in such a way that the flow which adjusts itself based on the boundary conditions causes the maximum of the difference of the isentropic Mach number 22 to 25 between the pressure side and the suction side of the turbine blade 14, 15 in a blade section which starts from the
- Blade trailing edge 5 extends in the direction of the blade leading edge 4 and 65% of the length S of the blade chord is long.
- FIG 2 shows a turbine blade 14, which is designed herkömm ⁇ Lich, and a blade 15, which is designed in accordance of invention.
- the conventionally designed blade 14 has a blade leading edge 16 and a blade trailing edge 18. After changing the skeleton line 3 results in the inventively designed blade 15.
- the inventively designed blade 15 has a blade leading edge 17 and a blade trailing edge 19. From Figure 2 it can be seen that the According to the invention designed turbine blade 15 after changing the skeleton line 3 has a more curved skeleton line 3 than the conventionally designed blade 14 has.
- the first polynomial 11 and second Polynomial 12 descriptive parameters for example, assume the following values:
- FIG. 3 shows a plot over whose abscissa 20 the length of the blade chord 13 and above its ordinate 21 the isentropic Mach number is plotted.
- Figure 3 shows a Machiereverlauf 22 on the pressure side and a Machiereverlauf 24 on the suction side of the conventionally designed blade 14. Also shown is a Machiereverlauf 23 at the
- the Machiereverstructure 22 to 25 show that for the conven ⁇ Lich designed turbine blade, the difference of the Mach ⁇ number curves 25 and 23 in the front of the blade 14 is greater than in the rear of the turbine blade 14.
- the difference in the Machiereverêt 24 and 22 for according to the invention profiled blade 15 in the rear ⁇ ren region of the turbine blade 15 is greater than in the prede ⁇ ren region of the turbine blade 15.
- the maximum of the dif- ference of the invention designed according to the turbine blade 15 is located at substantially a length of the blade chord 13 0.5 * S.
- Figure 4 shows a graph in which on the abscissa 25, the phase angle between two adjacent turbine ⁇ shovel (English: Inter blade phase angle) is applied. About the ordinate 26 of Figure 4 is an aerodynamic Damping value applied. Also plotted is a zero line 27 at which the aerodynamic damping value assumes the value zero. To determine is whether the turbine show ⁇ fel attenuated or excited, for each angle Phasendif- ferenz the linearized Navier-Stokes equations ge ⁇ dissolves and calculates the aerodynamic damping value.
- Figure 4 shows a damping value curve 28 for the conventional set of ⁇ turbine blade 14 and a Dämpfungswertver ⁇ marker 29 RDI for the inventively designed Turbinenlaufschau- 15.
- the attenuation value profile 28 assumes negative values, which means that the conventionally designed turbine ⁇ blade 14 in the Operation of the axial flow machine has a self-excited flutter vibration.
- the attenuation value profile 29, however, has a positive value for all phase difference angles, which means that the present invention
- Blade 15 in the operation of the axial flow machine has no self-excited flutter vibration.
- the maximum of the difference of the isentropic Mach number is in the inventive blade portion, can for example, take the following values in a transonic section of a turbine blade in an alternative turbine ⁇ shovel alternatively, the first polynomial 11 and second poly ⁇ nom 12 descriptive parameters :
- Figure 5 shows a thickness distribution of the alternative turbine blade.
- the thickness distribution is plotted in FIG. 5 in a plot whose abscissa 1 coincides with the blade chord 13 and over whose ordinate the thickness of the alternative turbine blade is plotted.
- the polynomial is formed by selecting the leading edge curvature radius R LE , the length x D i from the blade leading edge 4 to the point (x D i, 0) on the blade chord 13 where the maximum turbine blade air thickness Dl is the thickness d2 which is the thickness of the alternative turbine blade at the point (x D i + 0, 5 * (Sx D i), 0), and
- Blade further has at the blade trailing edge 5 on a blade trailing edge 5 tapered portion, which starts from a thickness d 3 and drops to zero.
- the thickness d3 can be in a range of 96% to 99.9% of S.
- the aforementioned quantities can assume the following values:
- Figure 6 shows a damping value curve 31 for a herkömm ⁇ Liche designed turbine blade and a damping ⁇ value curve 32 for the alternative according to the invention designed turbine blade.
- the damping value profile 32 takes in lesser extent negative values as the attenuation value ⁇ extending 31, causing the alternative turbine blade is less liable to flutter than the conventional turbine bucket ⁇ .
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Description
Claims
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP15165330.0A EP3088663A1 (de) | 2015-04-28 | 2015-04-28 | Verfahren zum profilieren einer schaufel |
PCT/EP2016/058559 WO2016173875A1 (de) | 2015-04-28 | 2016-04-18 | Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel |
Publications (2)
Publication Number | Publication Date |
---|---|
EP3274558A1 true EP3274558A1 (de) | 2018-01-31 |
EP3274558B1 EP3274558B1 (de) | 2021-03-17 |
Family
ID=53039740
Family Applications (2)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15165330.0A Withdrawn EP3088663A1 (de) | 2015-04-28 | 2015-04-28 | Verfahren zum profilieren einer schaufel |
EP16716884.8A Active EP3274558B1 (de) | 2015-04-28 | 2016-04-18 | Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP15165330.0A Withdrawn EP3088663A1 (de) | 2015-04-28 | 2015-04-28 | Verfahren zum profilieren einer schaufel |
Country Status (5)
Country | Link |
---|---|
US (1) | US10563511B2 (de) |
EP (2) | EP3088663A1 (de) |
JP (1) | JP6524258B2 (de) |
CN (1) | CN107592896B (de) |
WO (1) | WO2016173875A1 (de) |
Families Citing this family (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3081751B1 (de) | 2015-04-14 | 2020-10-21 | Ansaldo Energia Switzerland AG | Gekühlte turbinenschaufel und verfahren zur herstellung dieser schaufel |
EP3205885A1 (de) * | 2016-02-10 | 2017-08-16 | Siemens Aktiengesellschaft | Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel |
EP3239460A1 (de) * | 2016-04-27 | 2017-11-01 | Siemens Aktiengesellschaft | Verfahren zum profilieren von schaufeln einer axialströmungsmaschine |
US10563512B2 (en) * | 2017-10-25 | 2020-02-18 | United Technologies Corporation | Gas turbine engine airfoil |
GB201719539D0 (en) * | 2017-11-24 | 2018-01-10 | Rolls Royce Plc | Gas Turbine Engine |
FR3089553B1 (fr) * | 2018-12-11 | 2021-01-22 | Safran Aircraft Engines | Aube de turbomachine a loi de fleche a forte marge au flottement |
CN110990994B (zh) * | 2019-10-23 | 2023-10-31 | 东北大学 | 一种基于Matlab和UG的涡轮叶片参数化造型方法 |
US20210381385A1 (en) * | 2020-06-03 | 2021-12-09 | Honeywell International Inc. | Characteristic distribution for rotor blade of booster rotor |
DE102021123281A1 (de) | 2021-09-08 | 2023-03-09 | MTU Aero Engines AG | Schaufelblatt für einen Verdichter einer Strömungsmaschine |
JP2023114509A (ja) * | 2022-02-07 | 2023-08-18 | 本田技研工業株式会社 | ターボ機器及びターボ機器の設計方法 |
Family Cites Families (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4919593A (en) | 1988-08-30 | 1990-04-24 | Westinghouse Electric Corp. | Retrofitted rotor blades for steam turbines and method of making the same |
US5203676A (en) | 1992-03-05 | 1993-04-20 | Westinghouse Electric Corp. | Ruggedized tapered twisted integral shroud blade |
US6129528A (en) * | 1998-07-20 | 2000-10-10 | Nmb Usa Inc. | Axial flow fan having a compact circuit board and impeller blade arrangement |
DE102005025213B4 (de) * | 2005-06-01 | 2014-05-15 | Honda Motor Co., Ltd. | Schaufel einer Axialströmungsmaschine |
DE102006026968A1 (de) * | 2006-06-09 | 2008-01-24 | Rolls-Royce Deutschland Ltd & Co Kg | Strömungsarbeitsmaschine mit Rotoren hoher spezifischer Energieabgabe |
GB0821429D0 (en) * | 2008-11-24 | 2008-12-31 | Rolls Royce Plc | A method for optimising the shape of an aerofoil |
JP4923073B2 (ja) | 2009-02-25 | 2012-04-25 | 株式会社日立製作所 | 遷音速翼 |
EP2299124A1 (de) * | 2009-09-04 | 2011-03-23 | Siemens Aktiengesellschaft | Verdichterlaufschaufel für einen Axialverdichter |
GB201003084D0 (en) * | 2010-02-24 | 2010-04-14 | Rolls Royce Plc | An aerofoil |
WO2012019650A1 (en) * | 2010-08-12 | 2012-02-16 | Nuovo Pignone S.P.A. | Radial diffuser vane for centrifugal compressors |
US9309769B2 (en) * | 2010-12-28 | 2016-04-12 | Rolls-Royce Corporation | Gas turbine engine airfoil shaped component |
GB201103222D0 (en) * | 2011-02-24 | 2011-04-13 | Imp Innovations Ltd | A turbine wheel,a turbine and a use thereof |
FR2991373B1 (fr) * | 2012-05-31 | 2014-06-20 | Snecma | Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied |
GB201309280D0 (en) * | 2013-05-23 | 2013-07-10 | Rolls Royce Plc | Aerofoil Recambering |
US10443390B2 (en) * | 2014-08-27 | 2019-10-15 | Pratt & Whitney Canada Corp. | Rotary airfoil |
-
2015
- 2015-04-28 EP EP15165330.0A patent/EP3088663A1/de not_active Withdrawn
-
2016
- 2016-04-18 WO PCT/EP2016/058559 patent/WO2016173875A1/de active Application Filing
- 2016-04-18 CN CN201680025002.3A patent/CN107592896B/zh active Active
- 2016-04-18 JP JP2017556642A patent/JP6524258B2/ja active Active
- 2016-04-18 EP EP16716884.8A patent/EP3274558B1/de active Active
- 2016-04-18 US US15/567,141 patent/US10563511B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US20180100399A1 (en) | 2018-04-12 |
EP3088663A1 (de) | 2016-11-02 |
JP2018519452A (ja) | 2018-07-19 |
US10563511B2 (en) | 2020-02-18 |
WO2016173875A1 (de) | 2016-11-03 |
CN107592896B (zh) | 2019-11-29 |
EP3274558B1 (de) | 2021-03-17 |
JP6524258B2 (ja) | 2019-06-05 |
CN107592896A (zh) | 2018-01-16 |
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