EP1522679A2 - Aubes de guidage pour turbine - Google Patents

Aubes de guidage pour turbine Download PDF

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Publication number
EP1522679A2
EP1522679A2 EP04255388A EP04255388A EP1522679A2 EP 1522679 A2 EP1522679 A2 EP 1522679A2 EP 04255388 A EP04255388 A EP 04255388A EP 04255388 A EP04255388 A EP 04255388A EP 1522679 A2 EP1522679 A2 EP 1522679A2
Authority
EP
European Patent Office
Prior art keywords
vane
stagnation point
nozzle guide
air flow
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.)
Withdrawn
Application number
EP04255388A
Other languages
German (de)
English (en)
Other versions
EP1522679A3 (fr
Inventor
David Macmanus
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of EP1522679A2 publication Critical patent/EP1522679A2/fr
Publication of EP1522679A3 publication Critical patent/EP1522679A3/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Withdrawn legal-status Critical Current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
    • 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
    • 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
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling

Definitions

  • the present invention relates to turbine blades and more particularly but not exclusively to turbine blades used as nozzle guide vanes for a high pressure turbine stage of an engine.
  • nozzle guide vanes can be stationery when they are termed "stator blades'' or may be adjustable in terms of the degree of guiding of air flow presented to the high pressure turbine stage of the engine.
  • Some turbine nozzle guide vanes include film cooling flows which are designed to cool either the pressure or the suction side of the aerofoil surfaces of the guide vane.
  • Film cooling comprises releasing through a plurality of holes appropriately distributed upon the guide vane surface a flow of cooling air such that a "film" of such cooling air passes over the vane surface in order to cool that vane.
  • the path of the air flows depends upon a leading edge stagnation point upon the aerofoil surface. The location of the leading edge stagnation point splits the main stream flow.
  • FIG. 1 illustrates a typical nozzle guide vane and turbine blade cooling arrangement 1.
  • the nozzle vanes 2 are arranged whereby high pressure cooling air emitted from apertures flows over the aerofoil surfaces 3 in order to cool that vane 2.
  • Turbine blades 4 are also cooled by flows through such apertures.
  • a leading edge stagnation point spits the air flow presented to the vanes 2 in the direction of arrowhead A either side of the vane 2.
  • Prior Art 1 illustrates a plan cross-section of a conventional high pressure nozzle guide vane 12.
  • air flow in the direction of arrowhead AA is split about a stagnation point 10 or stagnation line in three dimensions.
  • the position of the stagnation point 10 is sufficiently well understood to enable the coolant apertures 11 described previously with regard to Fig. 1 to ensure appropriate film cooling of the vane 2.
  • the stagnation point is well understood as a high pressure nozzle guide vane is subject to relatively small variation in the inlet swirl angle of the flow AA.
  • High pressure nozzle guide vanes are generally insensitive to such variations in the inlet swirl angle.
  • the air flow AA is "lifted'' or guided by a pressure surface 13 to a desired direction.
  • inlet swirl around the annulus upon which the vanes are mounted will depend upon the ratio of combustion burners to nozzle guide vanes as well as burner settings at reduced power configurations. Variations in inlet angle to the nozzle guide vanes 12 will affect the leading edge stagnation point 10 and so the air flow from the apertures 11 in order to provide film cool about the vane.
  • Fig. Prior Art 1 illustrates a typical high pressure nozzle guide vane in schematic plan cross-section. It will be noted from Fig. 1 that the nozzle guide vanes 2 in the arrangement are set at an angle to the air flow A. If the number of aerofoils which create the nozzle guide vane arrangement is reduced and the chord CAX is fixed then a high lift design of nozzle guide vane is required.
  • FIG. Prior Art 2 a possible schematic plan cross-section of a high lift nozzle guide vane 22 is illustrated.
  • an air flow BB is again presented to the vane 22 such that the flow is diverted over the vane 22 as illustrated by the arrowheads.
  • Apertures 24 are again provided within the vane 22 from which high pressure cooling air emanates in order to provide film cooling of the aerofoil surfaces of the vane 22.
  • an aerofoil vane 22 as depicted in Fig. Prior Art 2 is susceptible to large displacements in leading edge stagnation point 20 position upon the vane 22 due to the relatively flat incident surface 21 upon which the air flow BB is presented.
  • Variations in the inlet swirl angle of this flow BB will create movement of the stagnation point 20 up and down upon this surface 21. Variations in the leading edge stagnation point 20 render it more likely that the film cooling provided through high pressure cooling air flows from the apertures 24 will not follow the intended path upon the surface 21 or a suction surface 23 and so result in potentially unacceptably high operating temperatures or thermal cycling. Unsteady losses may also be increased due to the stagnation point movements leading to a loss of efficiency.
  • a guide vane for an engine comprising a surface towards which an air flow is directed in use, the surface being curved with a leading edge bulge ridge to limit the proportion of surface in a flat presentation aspect to the air flow in use and so limit in use possible stagnation point positions for that flow upon the aerofoil.
  • the bulge ridge is located substantially centrally upon the surface of the vane.
  • the bulge ridge is positioned off-centre.
  • the curves either side of the bulge ridge are differently shaped.
  • one curve is substantially flat whilst the other slope is curved.
  • one slope upon the surface develops into an early suction side for the vane due to its shape and/or position relative to the bulge ridge.
  • nozzle guide vane assembly for a turbine engine incorporating a plurality of vanes as described above.
  • an engine incorporating a nozzle guide vane assembly or nozzle guide vane as described above.
  • FIG. 2 schematically illustrating a plan cross-section of a vane in accordance with the present invention.
  • Fig. 3 which illustrates a vane 31 in accordance with the present invention.
  • the vane 31 incorporates a pressure side 32 and a suction side 33 with an air flow C presented to the aerofoil.
  • the aerofoil incorporates apertures 34 through which cooling air is released from supply channels 35.
  • the air flow C impinges or strikes upon the aerofoil such that there is a stagnation point 30 where the air flow C is substantially perpendicularly presented to the aerofoil. Air flows either side of the stagnation point 30 pass about and over the pressure side 32 and around a leading edge 36 onto the suction side 33.
  • the part of aerofoil which within the pressure surface 32 is formed also incorporates a bulge ridge 37 from which extend slopes 32a, 32b.
  • the bulge ridge 37 provides a limited top surface which may be perpendicular to the presented air flow C.
  • the slopes 32a, 32b either side of the bulge ridge 37 are curved as presented to the air flow C and so the air flow C is generally deflected.
  • the bulge ridge 37 and a limited margin either side of that ridge 37 constitute the potential range of positions for the stagnation point 30.
  • the position of the stagnation point 30 is well defined and stable such that there is a predictability which allows appropriate positioning of the apertures 34 in order to achieve film cooling as require.
  • a deviation in the air flow C in accordance with the primary function of a nozzle guide vane is still achieved principally by the lower slope 32b and more fundamentally by the suction side 33 which is substantially the same as the suction sides 14, 23 of previous vanes described with regard to Fig. Prior Art 1 and Fig. Prior Art 2.
  • the vane 31 described in Fig. 2 has an increased cross-sectional area in coolant air supply channels 35 which allows an improved cooling air pressure to be presented through the apertures 34 for film cooling efficiency. Furthermore, the increased boxed shape of the vane 31 will improve mechanical strength and stiffness of the vane 31.
  • Fig. 1 illustrating a typical nozzle guide vane and turbine blade cooling arrangement 1 for a turbine engine.
  • the vanes 2 are mounted such that they are angularly presented to the air flow A.
  • This axial chord spacing CAX will typically be fixed as described previously such that if it is desired to reduce the number of vanes and aerofoils in a nozzle guide vane arrangement it is necessary for each vane to create more lift in the presented air flow A. As indicated previously, it is when attempting to achieve this greater lift that particular difficulties occur with regard to stagnation point predictability and stability.
  • the bulge ridge 37 is defined as a forward part of the pressure surface 32 such that dotted line 38 constitutes the notional front edge of the nozzle guide vane surface presented to the air flow.
  • the expected inlet flow angle will be towards that nominal front edge (broken line 38) and the slopes 32a, 32b will each be angularly curved in presentation to the flow.
  • the actual presentation of the air flow C may swirl but nevertheless in accordance with the present invention the stagnation point 30 will remain substantially about the top of the bulge ridge 37.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)
EP04255388A 2003-10-11 2004-09-04 Aubes de guidage pour turbine Withdrawn EP1522679A3 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GBGB0323909.2A GB0323909D0 (en) 2003-10-11 2003-10-11 Turbine blades
GB0323909 2003-10-11

Publications (2)

Publication Number Publication Date
EP1522679A2 true EP1522679A2 (fr) 2005-04-13
EP1522679A3 EP1522679A3 (fr) 2012-08-01

Family

ID=29433777

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04255388A Withdrawn EP1522679A3 (fr) 2003-10-11 2004-09-04 Aubes de guidage pour turbine

Country Status (3)

Country Link
US (1) US20050079060A1 (fr)
EP (1) EP1522679A3 (fr)
GB (1) GB0323909D0 (fr)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2974840A1 (fr) * 2011-05-06 2012-11-09 Snecma Distributeur de turbine dans une turbomachine
CN102089499B (zh) * 2008-12-24 2014-06-18 三菱重工业株式会社 一级定子叶片的冷却结构及燃气轮机
EP2846000A3 (fr) * 2013-09-09 2015-04-29 Rolls-Royce Deutschland Ltd & Co KG Roue statorique d'une turbine à gaz
US9395085B2 (en) 2009-12-07 2016-07-19 Mitsubishi Hitachi Power Systems, Ltd. Communicating structure between adjacent combustors and turbine portion and gas turbine
EP3124743A1 (fr) 2015-07-28 2017-02-01 Rolls-Royce Deutschland Ltd & Co KG Aube de distributeur et procédé de fabrication d'une aube de distributeur
EP3569817A1 (fr) * 2018-05-14 2019-11-20 ArianeGroup GmbH Agencement d'aubes directrices à utiliser dans une turbine

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7323791B2 (en) * 2006-03-27 2008-01-29 Jonsson Stanley C Louvered horizontal wind turbine
US20100098542A1 (en) * 2008-10-20 2010-04-22 Jonsson Stanley C Wind Turbine Having Two Sets of Air Panels to Capture Wind Moving in Perpendicular Direction
DE102009036406A1 (de) * 2009-08-06 2011-02-10 Mtu Aero Engines Gmbh Schaufelblatt
WO2011116231A2 (fr) * 2010-03-19 2011-09-22 Sp Tech Pale d'hélice
US20130156602A1 (en) † 2011-12-16 2013-06-20 United Technologies Corporation Film cooled turbine component
US9021816B2 (en) * 2012-07-02 2015-05-05 United Technologies Corporation Gas turbine engine turbine vane platform core
EP2964932B1 (fr) 2013-03-04 2020-11-04 United Technologies Corporation Aube et moteur à turbine à gaz associé
GB201405572D0 (en) * 2014-03-28 2014-05-14 Rolls Royce Plc Actuation system investigation apparatus
EP3124749B1 (fr) * 2015-07-28 2018-12-19 Ansaldo Energia Switzerland AG Dispositif d'aube de turbine de premièr ètage
US20170159442A1 (en) * 2015-12-02 2017-06-08 United Technologies Corporation Coated and uncoated surface-modified airfoils for a gas turbine engine component and methods for controlling the direction of incident energy reflection from an airfoil
US11286787B2 (en) * 2016-09-15 2022-03-29 Raytheon Technologies Corporation Gas turbine engine airfoil with showerhead cooling holes near leading edge
JP6934350B2 (ja) * 2017-08-03 2021-09-15 三菱パワー株式会社 ガスタービン
US11840939B1 (en) * 2022-06-08 2023-12-12 General Electric Company Gas turbine engine with an airfoil

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013877A2 (fr) * 1998-12-21 2000-06-28 United Technologies Corporation Aube de turbine creuse
EP1273758A2 (fr) * 2001-07-05 2003-01-08 General Electric Company Méthode de refroidissement par pellicule d'une aube d'une turbomachine

Family Cites Families (5)

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US3000401A (en) * 1960-01-29 1961-09-19 Friedrich O Ringleb Boundary layer flow control device
US4123196A (en) * 1976-11-01 1978-10-31 General Electric Company Supersonic compressor with off-design performance improvement
US5151014A (en) * 1989-06-30 1992-09-29 Airflow Research And Manufacturing Corporation Lightweight airfoil
FR2728618B1 (fr) * 1994-12-27 1997-03-14 Europ Propulsion Distributeur supersonique d'etage d'entree de turbomachine
US6358012B1 (en) * 2000-05-01 2002-03-19 United Technologies Corporation High efficiency turbomachinery blade

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1013877A2 (fr) * 1998-12-21 2000-06-28 United Technologies Corporation Aube de turbine creuse
EP1273758A2 (fr) * 2001-07-05 2003-01-08 General Electric Company Méthode de refroidissement par pellicule d'une aube d'une turbomachine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102089499B (zh) * 2008-12-24 2014-06-18 三菱重工业株式会社 一级定子叶片的冷却结构及燃气轮机
US9091170B2 (en) 2008-12-24 2015-07-28 Mitsubishi Hitachi Power Systems, Ltd. One-stage stator vane cooling structure and gas turbine
US9395085B2 (en) 2009-12-07 2016-07-19 Mitsubishi Hitachi Power Systems, Ltd. Communicating structure between adjacent combustors and turbine portion and gas turbine
CN103518037A (zh) * 2011-05-06 2014-01-15 斯奈克玛 涡轮发动机中的涡轮喷管
WO2012153049A1 (fr) * 2011-05-06 2012-11-15 Snecma Distributeur de turbine dans une turbomachine
FR2974840A1 (fr) * 2011-05-06 2012-11-09 Snecma Distributeur de turbine dans une turbomachine
CN103518037B (zh) * 2011-05-06 2016-08-03 斯奈克玛 一种用于涡轮发动机涡轮的扇形喷管和涡轮发动机
US9599020B2 (en) 2011-05-06 2017-03-21 Snecma Turbine nozzle guide vane assembly in a turbomachine
EP2846000A3 (fr) * 2013-09-09 2015-04-29 Rolls-Royce Deutschland Ltd & Co KG Roue statorique d'une turbine à gaz
US9896950B2 (en) 2013-09-09 2018-02-20 Rolls-Royce Deutschland Ltd & Co Kg Turbine guide wheel
EP3124743A1 (fr) 2015-07-28 2017-02-01 Rolls-Royce Deutschland Ltd & Co KG Aube de distributeur et procédé de fabrication d'une aube de distributeur
US10415409B2 (en) 2015-07-28 2019-09-17 Rolls-Royce Deutschland Ltd & Co Kg Nozzle guide vane and method for forming such nozzle guide vane
EP3569817A1 (fr) * 2018-05-14 2019-11-20 ArianeGroup GmbH Agencement d'aubes directrices à utiliser dans une turbine
US11536146B2 (en) 2018-05-14 2022-12-27 Arianegroup Gmbh Guide vane arrangement for use in a turbine

Also Published As

Publication number Publication date
US20050079060A1 (en) 2005-04-14
GB0323909D0 (en) 2003-11-12
EP1522679A3 (fr) 2012-08-01

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