EP2241722A1 - Conduit d'aube d'entrée et compresseur - Google Patents

Conduit d'aube d'entrée et compresseur Download PDF

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Publication number
EP2241722A1
EP2241722A1 EP09005326A EP09005326A EP2241722A1 EP 2241722 A1 EP2241722 A1 EP 2241722A1 EP 09005326 A EP09005326 A EP 09005326A EP 09005326 A EP09005326 A EP 09005326A EP 2241722 A1 EP2241722 A1 EP 2241722A1
Authority
EP
European Patent Office
Prior art keywords
camber
inlet guide
guide vane
flow
compressor
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Withdrawn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
EP09005326A
Other languages
German (de)
English (en)
Inventor
Michel Van Rooij
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 EP09005326A priority Critical patent/EP2241722A1/fr
Publication of EP2241722A1 publication Critical patent/EP2241722A1/fr
Withdrawn legal-status Critical Current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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/321—Application in turbines in gas turbines for a special turbine stage
    • F05D2220/3216—Application in turbines in gas turbines for a special turbine stage for a special compressor stage
    • 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
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/17—Purpose of the control system to control boundary layer

Definitions

  • the inlet guide vane 10 comprises a leading section 12 and a trailing section 14.
  • the inlet guide vane 10 comprises a small amount of bending and thus produces little flow turning at zero stagger angles, which is illustrated as a constant bending of the profile's surface 16.
  • the surface 16 extends from the leading section 12 to the trailing section 14. From the camber line 18, it may be noticed that the surface 16 provides a curvature which is small in amount. As a result, the flow incidence is large at high stagger angles leading to flow separation with high loses and breakdown of the flow angle separation.
  • FIG 2 is a partial sectional view of an exemplary axial compressor according to an embodiment herein.
  • the compressor 20 comprises a housing 22 to which inlet guide vanes 24 and a plurality of stator rows 26 are attached.
  • a hub 28 having attached therein a plurality of rotor rows 30 is attached to a shaft 32.
  • the shaft 32 and the hub 28 with the rotor rows 30 rotate about an axis of the shaft 32.
  • FIG 4 shows a graphical comparison of performances of an inlet guide vane of constant camber (hereinafter referred as "standard IGV") and an inlet guide vane according to the invention (hereinafter referred as "S-shaped IGV”).
  • the graphical comparison shown is total pressure loss in percentage versus stagger angle in degrees.
  • Plots are shown for a standard IGV and an S-shaped IGV. From the plot 42, it can be seen that the percentage of pressure loss increase for the standard IGV from a stagger angle of 15 degrees and reaches to 2 percent at the stagger angle of 30 degrees. From, the plot 44, it can be seen that the percentage of pressure loss for the S-shaped IGV remains constant till the stagger angle is 35 degrees and reaches to 0.8 percent at the stagger angle of 40 degrees. Therefore, the S-shaped IGV prevents pressure loss and also flow separation until higher stagger angles are reached.

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)
EP09005326A 2009-04-14 2009-04-14 Conduit d'aube d'entrée et compresseur Withdrawn EP2241722A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP09005326A EP2241722A1 (fr) 2009-04-14 2009-04-14 Conduit d'aube d'entrée et compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09005326A EP2241722A1 (fr) 2009-04-14 2009-04-14 Conduit d'aube d'entrée et compresseur

Publications (1)

Publication Number Publication Date
EP2241722A1 true EP2241722A1 (fr) 2010-10-20

Family

ID=41059630

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09005326A Withdrawn EP2241722A1 (fr) 2009-04-14 2009-04-14 Conduit d'aube d'entrée et compresseur

Country Status (1)

Country Link
EP (1) EP2241722A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013181396A (ja) * 2012-02-29 2013-09-12 Mitsubishi Heavy Ind Ltd 可変容量ターボチャージャ
WO2015019597A1 (fr) * 2013-08-06 2015-02-12 株式会社デンソー Ventilateur hélicoïdal et soufflerie/générateur de puissance utilisant ledit ventilateur
WO2016062531A1 (fr) * 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Profilage d'aubes directrices de dispositifs directeurs pour turbomachines, en particulier compresseurs
RU196070U1 (ru) * 2019-10-14 2020-02-14 Публичное акционерное общество "КАМАЗ" Система транспортирования текучей среды
EP4350122A1 (fr) * 2022-10-05 2024-04-10 RTX Corporation Stator de compresseur axial

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5472314A (en) * 1993-07-07 1995-12-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable camber turbomachine blade having resilient articulation
US20030129056A1 (en) * 2001-10-02 2003-07-10 Honda Giken Kogyo Kabushiki Kaisha Stator vane arrangement for rotating machinery
EP1340894A2 (fr) * 2002-02-28 2003-09-03 General Electric Company Aube de guidage variable pour la régulation du flux d'air entrant dans un turboréacteur
EP1674664A2 (fr) * 2004-12-21 2006-06-28 United Technologies Corporation Ailette du guidage de moteur de turbine et arrangement

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5472314A (en) * 1993-07-07 1995-12-05 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Variable camber turbomachine blade having resilient articulation
US20030129056A1 (en) * 2001-10-02 2003-07-10 Honda Giken Kogyo Kabushiki Kaisha Stator vane arrangement for rotating machinery
EP1340894A2 (fr) * 2002-02-28 2003-09-03 General Electric Company Aube de guidage variable pour la régulation du flux d'air entrant dans un turboréacteur
EP1674664A2 (fr) * 2004-12-21 2006-06-28 United Technologies Corporation Ailette du guidage de moteur de turbine et arrangement

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013181396A (ja) * 2012-02-29 2013-09-12 Mitsubishi Heavy Ind Ltd 可変容量ターボチャージャ
CN104136736A (zh) * 2012-02-29 2014-11-05 三菱重工业株式会社 可变容量涡轮增压器
US9926938B2 (en) 2012-02-29 2018-03-27 Mitsubishi Heavy Industries, Ltd. Variable geometry turbocharger
WO2015019597A1 (fr) * 2013-08-06 2015-02-12 株式会社デンソー Ventilateur hélicoïdal et soufflerie/générateur de puissance utilisant ledit ventilateur
WO2016062531A1 (fr) * 2014-10-21 2016-04-28 Siemens Aktiengesellschaft Profilage d'aubes directrices de dispositifs directeurs pour turbomachines, en particulier compresseurs
RU2674844C2 (ru) * 2014-10-21 2018-12-13 Сименс Акциенгезелльшафт Радиальный компрессор
US10634156B2 (en) 2014-10-21 2020-04-28 Siemens Aktiengesellschaft Centrifugal compressor
RU196070U1 (ru) * 2019-10-14 2020-02-14 Публичное акционерное общество "КАМАЗ" Система транспортирования текучей среды
EP4350122A1 (fr) * 2022-10-05 2024-04-10 RTX Corporation Stator de compresseur axial

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