EP1965024A1 - Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks - Google Patents
Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks Download PDFInfo
- Publication number
- EP1965024A1 EP1965024A1 EP08102089A EP08102089A EP1965024A1 EP 1965024 A1 EP1965024 A1 EP 1965024A1 EP 08102089 A EP08102089 A EP 08102089A EP 08102089 A EP08102089 A EP 08102089A EP 1965024 A1 EP1965024 A1 EP 1965024A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- wheel
- bladed
- bladed wheel
- fixed
- wheels
- 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 description 25
- 230000005284 excitation Effects 0.000 claims abstract description 29
- 230000004044 response Effects 0.000 claims abstract description 22
- 230000001360 synchronised effect Effects 0.000 claims abstract description 10
- 238000012886 linear function Methods 0.000 claims abstract description 3
- 238000011144 upstream manufacturing Methods 0.000 claims description 10
- 230000010349 pulsation Effects 0.000 claims description 9
- 230000010363 phase shift Effects 0.000 claims description 8
- 230000002123 temporal effect Effects 0.000 claims description 7
- 238000004364 calculation method Methods 0.000 claims description 5
- 239000012530 fluid Substances 0.000 claims description 5
- 238000013016 damping Methods 0.000 claims description 3
- 230000002964 excitative effect Effects 0.000 claims description 3
- 230000008569 process Effects 0.000 claims description 3
- 230000009467 reduction Effects 0.000 claims description 3
- 238000013461 design Methods 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 210000003462 vein Anatomy 0.000 description 3
- 230000008878 coupling Effects 0.000 description 2
- 238000010168 coupling process Methods 0.000 description 2
- 238000005859 coupling reaction Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 2
- 238000005070 sampling Methods 0.000 description 2
- 238000004513 sizing Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 241000897276 Termes Species 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002068 genetic effect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 238000002922 simulated annealing Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
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
- F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/4932—Turbomachine making
- Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49327—Axial blower or fan
Definitions
- the present invention relates to the field of turbomachines and aims a method for reducing the vibrations on the blades of a bladed wheel subject to periodic excitation resulting from disturbances in the gas flow through the turbomachine, produced by a bladed wheel or an obstacle near said wheel, one being generally mobile and the other fixed.
- a turbomachine comprises one or more rotors formed of bladed wheels, that is to say of blades mounted on a mobile disc rotated about an axis, and one or more grids formed of fixed bladed wheels, that is to say not movable in rotation with respect to the axis above.
- the vanes of the fixed and moving wheels are traversed by a gaseous fluid in a general direction parallel to the axis.
- One of the main sources of excitation of the fixed or mobile vanes is wakes and pressure fluctuations generated by the obstacles adjacent to the vane.
- These various obstacles, namely the blades of the upstream and downstream stages or the casing arms induce disturbances in the flow of fluid through the blades.
- the scrolling of the vanes in these disturbances creates a synchronous harmonic excitation of the rotational speed of the rotor and generates an unsteady pressure field on the surface of the blade.
- the blades are particularly sensitive parts because they must meet in terms of dimensioning requirements of aerodynamic performance, aeroacoustics and mechanical resistance to rotation, temperature and aerodynamic load. All of these aspects mean that these structures are sufficiently charged statically and that, given the requirements of service life, the amplitudes of vibrations that they undergo must remain low.
- the aeroelastic coupling ie the coupling between the dynamics of the bladed wheels and the fluid flow, conditions the vibratory stability of the structure.
- the sizing process is iterative. Vibration sizing is done to avoid the presence critical resonances in the operating range of the machine.
- the assembly is validated at the end of the design cycle by a motor test on which the vibration amplitudes are measured. It sometimes appears high vibratory levels related to either resonances or vibratory instabilities. The development of the rotor concerned must then be redone which is particularly long and expensive.
- the object of the present invention is to control, already during the design or development phase of the machine, the levels of vibratory response of the bladed wheels in a turbomachine structure comprising at least one mobile bladed wheel and one fixed bladed wheel traversed by a gas flow.
- the invention thus aims at the treatment of the vibrations produced by the disturbances generated for example by one of the wheels in the gas flow on the other bladed wheel. It is aimed in a particular case disturbances generated on the gas flow by the wake of a fixed bladed wheel or an obstacle such as crank arms; these disturbances produce vibrations on the mobile downstream wheel.
- the objective of the present invention is not limited to the control of vibration levels in a configuration where the bladed wheels are adjacent, it aims to control the vibratory responses on a bladed wheel for disturbances originating from upstream or downstream of the bladed wheel without being limited to adjacent wheels.
- the invention also relates to aerodynamic vein-type excitation excitations generated by one or more samplings in the gas vein or by a distortion of the engine inlet sleeve, when the engine is a turbojet engine, in the event of crosswind or flight in incidence. These distortions are included in the term obstacle, afterwards.
- Another object of the invention is the realization of a method that makes it possible to take the corrective measures that are required as early or as far upstream as possible in the process of designing and developing turbomachine bladed wheels.
- the initial configuration on the fixed wheel is modified, whether this is the exciter wheel or the wheel undergoing excitation.
- T y ⁇ * f ( ⁇ ) represents the generalized aerodynamic force for the eigenmode ⁇ .
- the treatment of vibration phenomena comprises within the scope of the invention the implementation of means for reducing the modulus
- a procedure to achieve this is to change the stacking axis of the studied blades in the direction tangential to the axis of rotation.
- the profile of the blade of a blade is geometrically defined from the profiles of each of the parallel sections made between the root of the blade and its top. The sections thus form a stack along a curve that is called the stacking axis.
- the profiles are determined aeromechanically.
- a turbomachine structure here a compressor, comprises at least one bladed wheel 3 movable about an axis of rotation adjacent to at least one fixed bladed wheel 2 or 4.
- the structure comprises a plurality of movable wheels separated by wheels fixed.
- the relative movement of one wheel relative to the other within an axial gas flow, represented by the arrow F is a source of disturbances.
- a first movable wheel 11 is influenced by a second fixed bladed wheel 12 while in its wake. This wake is the source of disturbances on the first moving wheel 11.
- a first movable bladed wheel 11 ' is considered in its position upstream with respect to a second fixed wheel 12' and which undergoes the excitatory forces generated by the second downstream wheel 12 '.
- the profile of a blade and its blade in particular is generally determined by a plurality of cuts made in the radial direction between the foot and the top.
- the figure 6 shows a fixed blade 30 of a stationary turbomachine stage with a foot 31 and its platform, a top 32 and its platform, and in between, a blade 33 swept by the gas flow.
- the blade 33 in position in the turbomachine is radially oriented relative to the axis of the latter.
- the blade is geometrically defined by the individual profile of a plurality of sections C 1 , C 2 , C 3 ,... C p (p being of the order of 20) by planes p1, p2, ... pp tangents to this radial direction.
- the profile of the blade swept by the gas flow is defined in the same way by cuts made in the tangent planes.
- the module of the forced response y ( ⁇ ) of the blades of a first bladed wheel is reduced by searching for an adequate distribution of the components of the pressures to minimize the modulus of the generalized aerodynamic force associated with each of the eigen modes ⁇ .
- the generalized aerodynamic force associated with an eigenmode is a multiplying factor that appears in each of the terms of the sum ⁇ .
- the first two steps are to define the specifications in terms of aerodynamic performance of the structure comprising the two bladed wheels, and then to calculate the initial configuration of the bladed wheels.
- This configuration includes the profiles of sections c 1 ,... C p and their stacking. It is generally carried out by aerodynamic iterations as is known to those skilled in the art.
- alpha is the smallest possible value given the manufacturing tolerances.
- Step 4 The procedure according to the invention is applied with the maximum vibratory level above as target.
- the modulus of the aeroelastic forced response is minimized for a given mode knowing that it can be extended to any mode.
- the method consists in determining the geometric offset ⁇ , illustrated on the figure 8 applied on the tangential stacking axis so as to minimize the vibratory response due to the disturbance, such as the wake.
- spline / poles or any discrete bases or chosen to project the stacking law are used for example.
- the optimization method can be any.
- gradient method so-called “simulated annealing” method
- genetic method ...
- the quantity to be minimized is the modulus
- Step 5 Perform a calculation of aeroelastic forced response y '( ⁇ ) on the modified blade to verify that the target in terms of maximum vibration level is reached. If this is not the case, a new profile definition is defined.
- Step 6 once the target has been reached, it is verified that the aerodynamic performances are preserved by modifying the stacking axis of the blade concerned.
- Step 7 the new definition of vane is retained; it meets the aerodynamic criteria in terms of performance and the mechanical criteria in terms of vibration levels.
- the figure 9 shows an example of aspect that takes the dawn 30 of the figure 6 after application of the method of the invention.
- the cuts c1, c2 ... cp are not aerodynamically modified. They have each undergone a tangential shift around the axis of the turbomachine.
- each point represents the value of the angle ⁇ for each of the cuts C 1 to C p over the entire height of the blade of the blade. It can be seen that this value remains relatively low, lower in this example than 1 degree with respect to the position corresponding to the initial configuration.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR0701408A FR2913074B1 (fr) | 2007-02-27 | 2007-02-27 | Methode de reduction des niveaux vibratoires d'une roue aubagee de turbomachine. |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1965024A1 true EP1965024A1 (de) | 2008-09-03 |
EP1965024B1 EP1965024B1 (de) | 2010-04-07 |
Family
ID=38562956
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP08102089A Active EP1965024B1 (de) | 2007-02-27 | 2008-02-27 | Verfahren zur Reduzierung der Schwingungsniveaus eines Schaufelrads eines Turbotriebwerks |
Country Status (7)
Country | Link |
---|---|
US (1) | US8286347B2 (de) |
EP (1) | EP1965024B1 (de) |
JP (1) | JP5685358B2 (de) |
CA (1) | CA2621839C (de) |
DE (1) | DE602008000918D1 (de) |
FR (1) | FR2913074B1 (de) |
RU (1) | RU2447293C2 (de) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2935350A1 (fr) * | 2008-08-27 | 2010-03-05 | Snecma | Methode de reduction des niveaux vibratoires d'une helice de turbomoteur. |
GB2462921B (en) * | 2008-08-27 | 2012-09-05 | Snecma | Method for reducing the vibration levels of a propfan of contrarotating bladed discs of a turbine engine |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20140072433A1 (en) * | 2012-09-10 | 2014-03-13 | General Electric Company | Method of clocking a turbine by reshaping the turbine's downstream airfoils |
US9435221B2 (en) | 2013-08-09 | 2016-09-06 | General Electric Company | Turbomachine airfoil positioning |
US10871170B2 (en) | 2018-11-27 | 2020-12-22 | Honeywell International Inc. | High performance wedge diffusers for compression systems |
US11333171B2 (en) | 2018-11-27 | 2022-05-17 | Honeywell International Inc. | High performance wedge diffusers for compression systems |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1995029331A2 (en) * | 1994-04-19 | 1995-11-02 | United Technologies Corporation | Stator vane arrangement for successive turbine stages |
WO1998036966A1 (en) * | 1997-02-21 | 1998-08-27 | California Institute Of Technology | Rotors with mistuned blades |
FR2824597A1 (fr) * | 2001-05-11 | 2002-11-15 | Snecma Moteurs | Reduction de vibrations dans une structure comprenant un rotor et des sources de perturbation fixes |
EP1528223A2 (de) * | 2003-10-29 | 2005-05-04 | ROLLS-ROYCE plc | Entwurf vibrationsbelasteter Turbomaschinenschaufeln |
EP1589191A1 (de) * | 2004-04-20 | 2005-10-26 | Snecma | Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
RU2076307C1 (ru) * | 1994-06-30 | 1997-03-27 | Анатолий Алексеевич Хориков | Способ диагностики автоколебаний рабочего колеса осевой турбомашины |
JPH11247605A (ja) * | 1997-12-26 | 1999-09-14 | United Technol Corp <Utc> | タ―ボマシ―ンコンポ―ネントの振動緩衝方法及び装置 |
FR2811635B1 (fr) * | 2000-07-13 | 2003-01-03 | Eurocopter France | Aeronef a voilure tournante a commande de pas electrique |
US7191161B1 (en) * | 2003-07-31 | 2007-03-13 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method for constructing composite response surfaces by combining neural networks with polynominal interpolation or estimation techniques |
EP1658966A1 (de) * | 2004-11-17 | 2006-05-24 | General Electric Company | Dämpfmaterial, Dämpfungseinrichtung, und Verfahren zum Entwurf einer Dämpfungseinrichtung |
-
2007
- 2007-02-27 FR FR0701408A patent/FR2913074B1/fr not_active Expired - Fee Related
-
2008
- 2008-02-22 US US12/035,966 patent/US8286347B2/en active Active
- 2008-02-26 JP JP2008044025A patent/JP5685358B2/ja active Active
- 2008-02-26 CA CA2621839A patent/CA2621839C/fr active Active
- 2008-02-26 RU RU2008107300/06A patent/RU2447293C2/ru active
- 2008-02-27 DE DE602008000918T patent/DE602008000918D1/de active Active
- 2008-02-27 EP EP08102089A patent/EP1965024B1/de active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO1995029331A2 (en) * | 1994-04-19 | 1995-11-02 | United Technologies Corporation | Stator vane arrangement for successive turbine stages |
WO1998036966A1 (en) * | 1997-02-21 | 1998-08-27 | California Institute Of Technology | Rotors with mistuned blades |
FR2824597A1 (fr) * | 2001-05-11 | 2002-11-15 | Snecma Moteurs | Reduction de vibrations dans une structure comprenant un rotor et des sources de perturbation fixes |
EP1528223A2 (de) * | 2003-10-29 | 2005-05-04 | ROLLS-ROYCE plc | Entwurf vibrationsbelasteter Turbomaschinenschaufeln |
EP1589191A1 (de) * | 2004-04-20 | 2005-10-26 | Snecma | Verfahren zum Einstellen gezielter unterschiedlicher Eigenfrequenzen eines beschaufelten Rotors einer Turbomachine sowie Rotor |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2935350A1 (fr) * | 2008-08-27 | 2010-03-05 | Snecma | Methode de reduction des niveaux vibratoires d'une helice de turbomoteur. |
GB2462921B (en) * | 2008-08-27 | 2012-09-05 | Snecma | Method for reducing the vibration levels of a propfan of contrarotating bladed discs of a turbine engine |
US8398372B2 (en) | 2008-08-27 | 2013-03-19 | Snecma | Method for reducing the vibration levels of a propeller of a turbine engine |
Also Published As
Publication number | Publication date |
---|---|
FR2913074A1 (fr) | 2008-08-29 |
JP2008208835A (ja) | 2008-09-11 |
US20080206058A1 (en) | 2008-08-28 |
CA2621839C (fr) | 2014-10-21 |
US8286347B2 (en) | 2012-10-16 |
CA2621839A1 (fr) | 2008-08-27 |
JP5685358B2 (ja) | 2015-03-18 |
RU2008107300A (ru) | 2009-09-10 |
RU2447293C2 (ru) | 2012-04-10 |
EP1965024B1 (de) | 2010-04-07 |
FR2913074B1 (fr) | 2009-05-22 |
DE602008000918D1 (de) | 2010-05-20 |
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