EP3088663A1 - Verfahren zum profilieren einer schaufel - Google Patents

Verfahren zum profilieren einer schaufel Download PDF

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Publication number
EP3088663A1
EP3088663A1 EP15165330.0A EP15165330A EP3088663A1 EP 3088663 A1 EP3088663 A1 EP 3088663A1 EP 15165330 A EP15165330 A EP 15165330A EP 3088663 A1 EP3088663 A1 EP 3088663A1
Authority
EP
European Patent Office
Prior art keywords
blade
skeleton line
length
skeleton
chord
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.)
Withdrawn
Application number
EP15165330.0A
Other languages
German (de)
English (en)
French (fr)
Inventor
Christian PEEREN
Stefan Schmitt
Ulrich Waltke
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP15165330.0A priority Critical patent/EP3088663A1/de
Priority to US15/567,141 priority patent/US10563511B2/en
Priority to CN201680025002.3A priority patent/CN107592896B/zh
Priority to PCT/EP2016/058559 priority patent/WO2016173875A1/de
Priority to EP16716884.8A priority patent/EP3274558B1/de
Priority to JP2017556642A priority patent/JP6524258B2/ja
Publication of EP3088663A1 publication Critical patent/EP3088663A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—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 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 longitudinal vibration of the blade with a node of vibration at the root 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). The material fatigue can lead to the formation of a crack and require a costly replacement of the blade.
  • the chatter is inhibited by reducing the load on the bucket.
  • this leads disadvantageously to a reduction in the efficiency of the axial flow machine.
  • conventional damping elements are provided, such as a shroud, which dampens the flutter of the blades.
  • this represents a structurally complex solution. Therefore, it would be desirable to design the blade such that it does not tend to flutter during operation of the axial flow machine.
  • 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 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 blade; Determining boundary conditions for a flow around the blade; Changing the skeleton line such that the boundary condition based flow causes the maximum of the isotropic Mach number difference between the pressure side and the suction side of the blade in a blade section extending from the blade trailing edge 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 are the same distance from the pressure side as from the suction side.
  • the blade chord designates the path in the profile section from the blade leading edge to the blade trailing edge.
  • the skeleton line is preferably formed of a first fourth degree polynomial describing the skeleton line from the leading edge of the blade to an extreme point and a second fourth degree polynomial describing the skeleton line from the extreme point to the trailing edge of the blade, the extreme point being that point of the skeleton line which has the maximum distance to the blade chord.
  • the distance refers to the length of a right angle from the blade chord extending to the skeleton line.
  • the first polynomial is formed by taking a leading edge skeleton angle, which is the angle between the leading edge tangent of the skeleton line and the blade chord, the length x S1 from the blade leading edge to the point of the blade chord having the maximum distance to the skeleton line, and the length S 1 which is the distance from the extreme point to the blade chord, the second polynomial being formed using a trailing edge skeleton angle which is the angle between the trailing edge tangent of the skeleton line and the blade chord, the length Sx S1 from the blade trailing edge to to the point of the blade chord having the maximum distance to the skeleton 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 x S1 + 0.5 * (Sx S1 ) from has the blade trailing edge, where S is the length of the blade chord. If a slope of zero is assumed for the extreme point, the first polynomial and the second polynomial are sufficiently determined
  • the skeleton line is changed such that S 1 is from 10.3% to 11.3% of the length S, x S1 is from 35.1% to 38.4% of the length S of the blade chord, S 2 from 64.8% to 67.9% of the length S is 1 , the back corner skeleton angle is from 15.192 ° to 19.020 °, and the front corner skeleton angle is from 37.663 ° to 39.256 °.
  • S 1 is from 10.3% to 11.3% of the length S
  • x S1 is from 35.1% to 38.4% of the length S of the blade chord
  • S 2 from 64.8% to 67.9% of the length S is 1
  • the back corner skeleton angle is from 15.192 ° to 19.020 °
  • the front corner skeleton angle is from 37.663 ° to 39.256 °.
  • the skeleton line is preferably changed such that S 1 is 10.8% of the length S, x S1 is 36.8% of the length S, S 2 is 66.3% of the length S 1 , the front corner skeleton angle is 17.106 ° and the posterior corner skeleton angle is 38.460 ° is. Based on these parameters is advantageously achieved that the blade has a particularly low tendency to flutter.
  • the geometric model has a varying thickness along the skeleton line that during is left the same as changing the skeleton line.
  • the skeleton line is changed to reduce the tendency of the blade to flutter, which is advantageously a simple process with only a few parameters to be changed.
  • the boundary conditions of the flow result from the nominal operating condition of the axial flow machine.
  • the isentropic Mach numbers are preferably determined experimentally and / or determined by calculation. It is preferred that the process be repeated for different profile cuts of the blade. This results in a design of the blade along its height.
  • the profile section is preferably located on a cylindrical surface or a conical surface, the axes of which coincide with the axis of the axial flow machine, on an S 1 flow surface or in a tangential plane of the axial flow machine.
  • FIG. 1 shows a geometric model of a profile section of a blade for an axial flow machine.
  • the profile section is, for example, on a cylindrical surface or a conical surface whose axes coincide with the axis of the axial flow machine, on an S 1 flow surface or in a tangential plane of the axial flow machine.
  • the geometric model has 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 blade. It is still out FIG. 1 it can be seen that the blade has a blade leading edge 4 and a blade trailing edge 5.
  • the blade leading edge 4 and the blade trailing edge 5 define the skeleton line 3.
  • the distance between the blade leading edge 4 and the blade trailing edge 5 is the blade chord 13.
  • the geometric model is shown in FIG FIG. 1 drawn in a plot, the 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 FIG. 1 is selected 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 extreme point 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 Vorderkantentangente 7 includes the Schaufelsehne 13 a Vorderkantenskelettwinkel LESA.
  • a Schukantentangente 8 is shown, which is the tangent of the skeleton line 3 on the blade trailing edge 5.
  • the Deutschenkantentangente 8 includes with the blade chord 13 a Deutschenkantenskelettwinkel TESA.
  • the first polynomial 11 is formed by selecting the leading edge skeleton angle LESA, the length x S1 from the blade leading edge 4 to the point (x S1 , 0) on the blade chord 13 having the maximum distance to the skeleton line 13, and the length S 1 , which is the distance from the point (x S1 , 0) to the extreme point 30. Because the slope of the extreme point 30 is zero and the blade leading edge 4 lies in the origin of the coordinate system, the first polynomial 11 is sufficiently determined.
  • the second polynomial 12 is formed by selecting the hind corner skeleton angle TESA, the length Sx S1 from the blade trailing edge 5 to the point (x S1 , 0) on the blade chord 13, and the length S 2 representing the distance from the point (x S1 + 0.5 * (Sx S1 ), 0) 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 geometric model of the blade profile is provided as for FIG. 1 described. It provides boundary conditions for a flow around the blade.
  • the boundary conditions can result, for example, from the nominal operating condition of the axial flow machine.
  • the skeleton line 3 is changed such that the flow 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 blade 14, 15 in a blade section extending from the blade trailing edge 5 in the direction extends to the blade leading edge 4 and 65% of the length S of the blade chord is long.
  • FIG. 2 shows a blade 14, which is designed conventionally, and a blade 15, which is designed according to the invention.
  • the conventionally designed blade 14 has a blade leading edge 16 and a blade trailing edge 18 Changing the skeleton line 3 results in the blade 15 designed according to the invention.
  • the blade 15 designed according to the invention has a blade leading edge 17 and a blade trailing edge 19 FIG. 2 It can be seen that the blade 15 designed according to the invention has a more curved skeleton line 3 than the conventionally designed blade 14 after the skeleton line 3 has been changed.
  • the parameters describing the first polynomial 11 and second polynomial 12 can assume the following values, for example: Average lower limit Upper limit S 1 / S 0.108 0.113 0.103 X S1 / S 0.368 0.384 0.351 S 2 / S 1 0.663 0.679 0.648 TESA / ° 17.106 19.020 15.192 LESA / ° 38.460 39.256 37.663
  • FIG. 3 shows a plot over the abscissa 20, the length of the blade chord 13 and the ordinate 21, the isentropic Mach number is plotted.
  • FIG. 3 2 shows a Mach number course 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 on the pressure side and a Machiereverlauf 25 on the suction side of the inventively designed blade 15.
  • the Machiereverstructure 22 to 25 were determined by calculation , For this purpose, the Navier-Stokes equations for the stationary state of the given problem were solved.
  • the Machiereverstructure 22 to 25 show that for the conventionally designed blade, the difference of Machierevermati 25 and 23 in the front region of the blade 14 is greater than in the rear of the blade 14.
  • the difference of the Machiereverincome 24 and 22 for the invention profiled blade 15 in the rear region of the blade 15 is greater than in the front region of the blade 15.
  • the maximum of the difference of the inventively designed blade 15 is substantially at a length of the blade chord 13 of 0.5 * S.
  • FIG. 4 shows a plot in which the abscissa 25, the phase angle between two adjacent blades (English: Interblade Phase Angle) is plotted. About the ordinate 26 of FIG. 4 An aerodynamic damping value is plotted. Also plotted is a zero line 27 at which the aerodynamic damping value assumes the value zero. To determine whether the blade is damped or excited, the linearized Navier-Stokes equations are solved for each phase difference angle and the aerodynamic damping value is calculated.
  • FIG. 4 Figure 12 shows a damping value curve 28 for the conventional designed blade 14 and a damping value curve 29 for the blade 15 designed according to the invention.
  • the damping value curve 28 also assumes negative values, which means that the conventionally designed blade 14 has a self-excited flapping vibration during operation of the axial flow machine.
  • the attenuation value profile 29 has a positive value for all phase difference angles, which means that the blade 15 designed according to the invention has no self-excited flutter oscillation during operation of the axial-flow machine.
  • the blade is a vane or a blade.
  • the axial flow machine is preferably a gas turbine, a steam turbine or a compressor.

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  • 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)
EP15165330.0A 2015-04-28 2015-04-28 Verfahren zum profilieren einer schaufel Withdrawn EP3088663A1 (de)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP15165330.0A EP3088663A1 (de) 2015-04-28 2015-04-28 Verfahren zum profilieren einer schaufel
US15/567,141 US10563511B2 (en) 2015-04-28 2016-04-18 Method for profiling a turbine rotor blade
CN201680025002.3A CN107592896B (zh) 2015-04-28 2016-04-18 用于对涡轮转子叶片进行造型的方法
PCT/EP2016/058559 WO2016173875A1 (de) 2015-04-28 2016-04-18 Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel
EP16716884.8A EP3274558B1 (de) 2015-04-28 2016-04-18 Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel
JP2017556642A JP6524258B2 (ja) 2015-04-28 2016-04-18 タービンロータ翼の断面形状を決定するための方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP15165330.0A EP3088663A1 (de) 2015-04-28 2015-04-28 Verfahren zum profilieren einer schaufel

Publications (1)

Publication Number Publication Date
EP3088663A1 true EP3088663A1 (de) 2016-11-02

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 After (1)

Application Number Title Priority Date Filing Date
EP16716884.8A Active EP3274558B1 (de) 2015-04-28 2016-04-18 Verfahren zum profilieren einer turbinenlaufschaufel und entsprechende turbinenschaufel

Country Status (5)

Country Link
US (1) US10563511B2 (ja)
EP (2) EP3088663A1 (ja)
JP (1) JP6524258B2 (ja)
CN (1) CN107592896B (ja)
WO (1) WO2016173875A1 (ja)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190048880A1 (en) * 2016-02-10 2019-02-14 Siemens Aktiengesellschaft Compressor rotor blade, compressor, and method for profiling the compressor rotor blade

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EP3081751B1 (en) * 2015-04-14 2020-10-21 Ansaldo Energia Switzerland AG Cooled airfoil and method for manufacturing said airfoil
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

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EP2299124A1 (de) * 2009-09-04 2011-03-23 Siemens Aktiengesellschaft Verdichterlaufschaufel für einen Axialverdichter
EP2360377A2 (en) * 2010-02-24 2011-08-24 Rolls-Royce plc A compressor aerofoil
WO2013178914A1 (fr) * 2012-05-31 2013-12-05 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied

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Publication number Priority date Publication date Assignee Title
DE102005025213A1 (de) * 2005-06-01 2006-12-07 Honda Motor Co., Ltd. Schaufel einer Axialströmungsmaschine
EP2299124A1 (de) * 2009-09-04 2011-03-23 Siemens Aktiengesellschaft Verdichterlaufschaufel für einen Axialverdichter
EP2360377A2 (en) * 2010-02-24 2011-08-24 Rolls-Royce plc A compressor aerofoil
WO2013178914A1 (fr) * 2012-05-31 2013-12-05 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20190048880A1 (en) * 2016-02-10 2019-02-14 Siemens Aktiengesellschaft Compressor rotor blade, compressor, and method for profiling the compressor rotor blade
US10837450B2 (en) * 2016-02-10 2020-11-17 Siemens Aktiengesellschaft Compressor rotor blade, compressor, and method for profiling the compressor rotor blade

Also Published As

Publication number Publication date
US10563511B2 (en) 2020-02-18
CN107592896B (zh) 2019-11-29
EP3274558A1 (de) 2018-01-31
JP6524258B2 (ja) 2019-06-05
CN107592896A (zh) 2018-01-16
US20180100399A1 (en) 2018-04-12
EP3274558B1 (de) 2021-03-17
JP2018519452A (ja) 2018-07-19
WO2016173875A1 (de) 2016-11-03

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