EP3205885A1 - Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel - Google Patents

Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel Download PDF

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Publication number
EP3205885A1
EP3205885A1 EP16155063.7A EP16155063A EP3205885A1 EP 3205885 A1 EP3205885 A1 EP 3205885A1 EP 16155063 A EP16155063 A EP 16155063A EP 3205885 A1 EP3205885 A1 EP 3205885A1
Authority
EP
European Patent Office
Prior art keywords
suction side
compressor
blade
profile
profile section
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Withdrawn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
EP16155063.7A
Other languages
German (de)
English (en)
French (fr)
Inventor
Christian Cornelius
Christoph Starke
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 EP16155063.7A priority Critical patent/EP3205885A1/de
Priority to US16/075,731 priority patent/US10837450B2/en
Priority to PCT/EP2017/050453 priority patent/WO2017137201A1/de
Priority to CN201780011074.7A priority patent/CN108603509B/zh
Priority to EP17700921.4A priority patent/EP3390833B1/de
Priority to KR1020187025646A priority patent/KR102206204B1/ko
Priority to JP2018541648A priority patent/JP6715941B2/ja
Publication of EP3205885A1 publication Critical patent/EP3205885A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D21/00—Pump involving supersonic speed of pumped fluids
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D19/00—Axial-flow pumps
    • 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
    • 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
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F05D2240/302—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor characteristics related to shock waves, transonic or supersonic flow
    • 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
    • F05D2240/305—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the pressure side of a rotor blade
    • 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
    • F05D2240/306—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the suction side of a rotor blade

Definitions

  • Losses in the flow of the working fluid in the transonic section arise, for example, in the compression shock and by separation of the boundary layer on the compressor blade in the region of the compression shock. The losses cause a reduction in the efficiency of the compressor.
  • the object of the invention is therefore to provide a compressor blade and a method for profiling the compressor blade, with which an increase in the efficiency of the compressor blade having a compressor can be achieved.
  • the compressor blade according to the invention for an axial compressor has a blade profile which has a transonic section and a profile section of the blade profile which extends in the transonic section and which has a concave suction side region on its suction side which is disposed at least partially upstream of a compression stroke exhibited by a flow established in the compressor at a nominal operating condition of the compressor whereby the surge is located downstream of a compression surge which would have a flow similar to a conventional compressor blade and the prior art Set nominal operating condition.
  • the inventive method for profiling a compressor blade for an axial design compressor, the compressor blade having a blade profile with a transonic section comprises the steps of providing a geometric model of the blade profile, the blade profile having a profile cut extending in the transonic section ; Determining boundary conditions for a flow around the blade that occurs at a nominal operating condition of the compressor; Changing the profile section such that the suction side has a concave suction side region located at least partially upstream of a compression stroke exhibited by a flow adjusting in the compressor at the boundary conditions whereby the surge is located downstream of a compression surge that would have flow; which would occur in the geometric model prior to changing the profile section and at the nominal operating condition.
  • the compressor with the compressor blade according to the invention and / or with the compressor blade profiled with the method according to the invention has a higher efficiency with at least the same operating range than a compressor with the conventional compressor blade.
  • the Mach numbers on the suction side of the compressor blade according to the invention prior to the compression shock are lower than on the suction side of the conventional compressor blade.
  • separations of the flow on the suction side of the invention Compressor blade less likely than the conventional compressor blade.
  • the compressor blade according to the invention can be performed with a shorter length of chord profile than is the case with the conventional compressor blade, without thereby sacrificing efficiency or a reduction of the working area.
  • the profile section of the conventional compressor blade is formed exclusively concave on the pressure side and / or is formed exclusively convex on the suction side.
  • the point of the concave suction side region with the minimum curvature when projecting perpendicularly onto the chord of the profile section on this prescribes a projection point which is from the leading edge of the profile section of 40% to 80% of the length of the chord.
  • the profile section preferably has on its pressure side a convex pressure side region, which is arranged in a region which is arranged opposite the concave suction side region.
  • the profile section on a cylindrical surface whose axis coincides with the axis of the compressor lie on a conical surface whose axis coincides with the axis of the compressor on an S 1 flow area of the compressor or in a tangential plane of the compressor.
  • the S 1 flow area extends in the circumferential direction and in the axial direction of the axial flow machine and describes a surface that follows an idealized flow.
  • the profile section is changed such that in the concave suction side area, the curve of the curvature multiplied by the length of the chord has a minimum value that is from -1.2 to -0.5.
  • the profile section is preferably modified such that the profile section has on its suction side a convex suction side region, which is arranged downstream of the concave suction side region. It is preferable that the profile section is changed such that in the convex suction side area, the curve of the curve has a maximum value larger than the maximum value of the curve of the curve in the corresponding area of the conventional compressor blade.
  • the profile section is preferably changed in such a way that in the convex suction side region the course of the curvature multiplied by the length of the chord has a maximum value which is from 2 to 4. It is preferred that the profile section is changed such that the point of the concave suction side region with the minimum curvature when projecting perpendicularly onto the chord of the profile section on this one projection point which is from 40% to 80% of the length of the chord from the leading edge of the profile section.
  • Each of these measures can further increase the efficiency of the compressor.
  • a compressor blade 1 for a compressor in axial construction on a blade profile has a radially inner subsonic section and a radially outer transonic section, wherein FIGS. 1 and 3 only the transonic section is shown.
  • the blade profile has a profile section 21 which extends in the transonic section.
  • the profile section 21 is located on a cylindrical surface whose axis coincides with the axis of the compressor, on a conical surface whose axis coincides with the axis of the compressor, on an S 1 flow area of the compressor or in a tangential plane of the compressor.
  • the profile section 21 has a front edge 2, a trailing edge 3, a pressure side 4 and a suction side 5.
  • a chord 22 is drawn, which extends as a straight line from the front edge 2 to the trailing edge 3.
  • a skeleton line 23 which extends from the front edge 2 to the trailing edge 3 and is always located in a direction perpendicular to the chord 22 midway between the pressure side 4 and the suction side 5.
  • FIG. 1 shows a two-dimensional flow distribution of a working medium flowing in the compressor in a region of the compressor.
  • a blade row 15 with the compressor blades 1, a blade row 15 downstream blade row 16 and a blade row 15 upstream blade row 17 are shown.
  • the profile section 21 has on its suction side 5 a concave suction side region 10, which is arranged at least partially upstream of a compression joint 18, which has an adjusting in the compressor at a nominal operating condition of the compressor flow.
  • the compression shock 18 is in FIG. 1 arranged in the areas of flow in which the Mach number decreases from higher than 1 to lower than 1.
  • FIG. 2 shows a comparison of the Mach number curves on the compressor blade 1 and the Machiereverstructure on the conventional compressor blade.
  • About the horizontal axis 19 is a point on the chord 22 of the profile section 21 and over the vertical axis 20, the Mach number is plotted.
  • Reference numeral 6 denotes the Mach number characteristic at the pressure side of the conventional compressor blade, with the reference numeral 7 Machiereverlauf on the suction side of the conventional compressor blade is designated by the reference numeral 8 is the Machiereverlauf on the pressure side 4 of the compressor blade 1 and the reference numeral 9 Machiereverlauf on the suction side 5 of the compressor blade 1 is designated.
  • FIG. 2 It can be seen that the Machiereverlauf 9 on the suction side 5 of the compressor blade 1 immediately upstream of the compression shock 18 lower supersonic Mach numbers than the Machiereverlauf 7 on the suction side of the conventional compressor blade immediately upstream of the compression shock. These lower supersonic Mach numbers are maintained over a longer extent along the chord 22 than in the conventional compressor blade. Due to the lower supersonic Mach numbers before the compression shock 18 losses are reduced. By keeping the supersonic Mach numbers over the longer extent, the total profile load correlated with the Mach number difference on the pressure side 4 and the suction side 5 is comparably high in the subsonic region downstream of the inspection shock 18 as in the conventional compressor blade. Moreover, it is off FIG.
  • the compression stroke 18 is arranged obliquely, which means that with increasing distance from the suction side 5, the compression shock 18 moves upstream. This also leads to a reduction of losses.
  • the FIG. 2 It can be seen that the profile load on the compressor blade 1 after the compression stroke 18 is significantly higher than in the conventional compressor blade. Due to the reduced losses and higher profile load in the subsonic region, a higher efficiency can be achieved with the compressor rotor blade 1 than with the conventional compressor rotor blade. Due to the higher efficiency, the compressor blade 1, as it is in FIG. 2 is shown to be shorter than the conventional compressor blade, thereby reducing losses can be reduced by friction of the working fluid to the compressor blade 1.
  • FIG. 4 shows a curvature 27 along the pressure side 4 and a curvature 28 along the suction side 5.
  • ⁇ s is the length of a circular arc and ⁇ is the difference angle between the tangents at the end points of the circular arc.
  • Concave suction side areas and convex pressure side areas are characterized by a negative sign of the curvature.
  • Convex suction side regions and concave pressure side regions are characterized by a positive sign of the curvature.
  • the profile section 21 has on its pressure side 4 a convex pressure side region 14, which is arranged in a region which is arranged opposite the concave suction side region 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16155063.7A 2016-02-10 2016-02-10 Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel Withdrawn EP3205885A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP16155063.7A EP3205885A1 (de) 2016-02-10 2016-02-10 Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel
US16/075,731 US10837450B2 (en) 2016-02-10 2017-01-11 Compressor rotor blade, compressor, and method for profiling the compressor rotor blade
PCT/EP2017/050453 WO2017137201A1 (de) 2016-02-10 2017-01-11 Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel
CN201780011074.7A CN108603509B (zh) 2016-02-10 2017-01-11 压气机转子动叶、压气机及用于对压气机转子动叶仿形的方法
EP17700921.4A EP3390833B1 (de) 2016-02-10 2017-01-11 Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel
KR1020187025646A KR102206204B1 (ko) 2016-02-10 2017-01-11 압축기 로터 블레이드, 압축기, 및 압축기 로터 블레이드를 프로파일링 하기 위한 방법
JP2018541648A JP6715941B2 (ja) 2016-02-10 2017-01-11 圧縮機動翼、圧縮機、および圧縮機動翼を輪郭形成するための方法

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP16155063.7A EP3205885A1 (de) 2016-02-10 2016-02-10 Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel

Publications (1)

Publication Number Publication Date
EP3205885A1 true EP3205885A1 (de) 2017-08-16

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Family Applications (2)

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EP16155063.7A Withdrawn EP3205885A1 (de) 2016-02-10 2016-02-10 Verdichterlaufschaufel und verfahren zum profilieren der verdichterlaufschaufel
EP17700921.4A Active EP3390833B1 (de) 2016-02-10 2017-01-11 Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel

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EP17700921.4A Active EP3390833B1 (de) 2016-02-10 2017-01-11 Verdichterlaufschaufel, verdichter und verfahren zum profilieren der verdichterlaufschaufel

Country Status (6)

Country Link
US (1) US10837450B2 (zh)
EP (2) EP3205885A1 (zh)
JP (1) JP6715941B2 (zh)
KR (1) KR102206204B1 (zh)
CN (1) CN108603509B (zh)
WO (1) WO2017137201A1 (zh)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111156195B (zh) * 2020-01-07 2023-11-17 哈尔滨工程大学 一种压气机叶片前缘结构

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934259A (en) * 1956-06-18 1960-04-26 United Aircraft Corp Compressor blading
FR2551145A1 (fr) * 1980-07-30 1985-03-01 Onera (Off Nat Aerospatiale) Etage de compresseur supersonique a aubes et procede de determination
JPH08121390A (ja) * 1994-10-25 1996-05-14 Ishikawajima Harima Heavy Ind Co Ltd 高速流体用の圧縮機翼形

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6116856A (en) * 1998-09-18 2000-09-12 Patterson Technique, Inc. Bi-directional fan having asymmetric, reversible blades
US7195456B2 (en) * 2004-12-21 2007-03-27 United Technologies Corporation Turbine engine guide vane and arrays thereof
JP5371578B2 (ja) 2009-06-26 2013-12-18 三菱重工業株式会社 タービンロータ
EP2299124A1 (de) * 2009-09-04 2011-03-23 Siemens Aktiengesellschaft Verdichterlaufschaufel für einen Axialverdichter
FR2953571B1 (fr) * 2009-12-07 2018-07-13 Valeo Systemes Thermiques Helice de ventilateur, en particulier pour vehicule automobile
JP5502695B2 (ja) * 2010-10-14 2014-05-28 株式会社日立製作所 軸流圧縮機
EP2669475B1 (fr) * 2012-06-01 2018-08-01 Safran Aero Boosters SA Aube à profile en S de compresseur de turbomachine axiale, compresseur et turbomachine associée
DE102013209966A1 (de) * 2013-05-28 2014-12-04 Honda Motor Co., Ltd. Profilgeometrie eines Flügels für einen Axialkompressor
EP3088663A1 (de) * 2015-04-28 2016-11-02 Siemens Aktiengesellschaft Verfahren zum profilieren einer schaufel

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2934259A (en) * 1956-06-18 1960-04-26 United Aircraft Corp Compressor blading
FR2551145A1 (fr) * 1980-07-30 1985-03-01 Onera (Off Nat Aerospatiale) Etage de compresseur supersonique a aubes et procede de determination
JPH08121390A (ja) * 1994-10-25 1996-05-14 Ishikawajima Harima Heavy Ind Co Ltd 高速流体用の圧縮機翼形

Also Published As

Publication number Publication date
KR20180110054A (ko) 2018-10-08
KR102206204B1 (ko) 2021-01-22
WO2017137201A1 (de) 2017-08-17
JP6715941B2 (ja) 2020-07-01
US10837450B2 (en) 2020-11-17
EP3390833B1 (de) 2019-09-04
CN108603509B (zh) 2020-04-03
US20190048880A1 (en) 2019-02-14
CN108603509A (zh) 2018-09-28
JP2019504962A (ja) 2019-02-21
EP3390833A1 (de) 2018-10-24

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