EP2462320B1 - Aube - Google Patents

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Publication number
EP2462320B1
EP2462320B1 EP10754675.6A EP10754675A EP2462320B1 EP 2462320 B1 EP2462320 B1 EP 2462320B1 EP 10754675 A EP10754675 A EP 10754675A EP 2462320 B1 EP2462320 B1 EP 2462320B1
Authority
EP
European Patent Office
Prior art keywords
blade
thickening
profile
housing
area
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.)
Active
Application number
EP10754675.6A
Other languages
German (de)
English (en)
Other versions
EP2462320A2 (fr
Inventor
Sergio Elorza Gomez
Rudolf Selmeier
Wilfried SCHÜTTE
Peter EIBELSHÄUSER
Harald Passrucker
Manfred Dupslaff
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines 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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Publication of EP2462320A2 publication Critical patent/EP2462320A2/fr
Application granted granted Critical
Publication of EP2462320B1 publication Critical patent/EP2462320B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • 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
    • 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
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • F04D29/544—Blade shapes
    • 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid 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
    • F04D29/66—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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/71—Shape curved
    • F05D2250/711—Shape curved convex
    • 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
    • F05D2250/71—Shape curved
    • F05D2250/713—Shape curved inflexed

Definitions

  • the present invention relates to an airfoil of a turbomachine, in particular an adjustable guide vane of a gas turbine, with at least one thickening on a pressure side of the airfoil profile, wherein the thickening is arranged in a radially outer, housing-side region of the airfoil.
  • Such blades for turbomachines are from the DE 28 41 616 , of the DE 10 2004 026 386 and the EP 0 789 447 B1 known.
  • the disclosed thickenings of the blades serve in particular to minimize the so-called secondary flow losses.
  • the thickening of the airfoil is in each case formed in the housing and / or scar-side suction and pressure region of the airfoil.
  • the known thickenings of the blade profile in the housing-side area are also necessary to counteract the high static stresses that frequently occur on the housing side of adjustable guide vanes of compressors.
  • the known circumferential, ie formed on the suction and pressure side thickenings have aerodynamic disadvantages. From the EP 1591624 is another compressor blade with a thickening known.
  • An inventive blade of a turbomachine in particular an adjustable guide vane of a gas turbine, comprising at least one thickening on a pressure side of the airfoil profile, wherein the thickening is disposed in a radially outer, housing-side portion of the airfoil and the thickening of a leading edge and a trailing edge of the airfoil each spaced is trained.
  • a complete thickening of the radially outer, housing-side regions of the airfoils is dispensed with.
  • thin, aerodynamic favorable airfoil profiles can be designed, which still have the required strength due to the locally pronounced thickening.
  • the thickening is designed as a convex contour within the overall concave contour of the pressure side of the airfoil profile.
  • the convex contour or the at least partially convex configuration of the thickening has proved to be advantageous in terms of flow mechanics.
  • the thickening in the housing-side end region of the airfoil can have their greatest profile thickness. In this case, the profile thickness of the thickening, starting from the largest profile thickness continuously decrease to a normal profile thickness of the airfoil profile without thickening.
  • the thickening extends maximally to a height of the housing and pressure-side region of the blade, which corresponds to 25% of the blade blade height. It has been found that such a dimensioning of the thickening the necessary strength ensures the blade in the housing-side area.
  • predominant regions of the airfoil may have a relatively thin, aerodynamically optimized airfoil profile.
  • the distance between the leading edge of the blade and the thickening in the housing-side end region of the blade is at least 15% of a chord length of the blade in this end region.
  • the convex contour of the thickening at the ends of the thickening can each extend tangentially to the concave contour of the pressure side of the airfoil profile.
  • the thickening may be formed at least partially bead or hump.
  • An inventive blade is on the housing side connected to a rotatably mounted in a housing of the turbomachine turntable.
  • the leading edge of the blade can be arranged completely within the diameter of the turntable.
  • the trailing edge of the airfoil protrudes beyond the turntable, and the thickening ends outside the diameter of the turntable. As a result, it is possible to specifically reduce stresses on the edge of the turntable.
  • a turbomachine according to the invention in particular gas turbine, with a stator and / or rotor blading comprises a plurality of blades according to the embodiments of the invention described above.
  • a compressor according to the invention of a turbomachine in particular a high-pressure compressor of a gas turbine, comprises a stator blading with a multiplicity of airfoils according to one of the embodiments described above.
  • FIG. 1 shows a schematic representation of an airfoil 10 without thickening according to the prior art.
  • the airfoil 10 has a conventional airfoil contour 16, wherein the airfoil contour 16 on the pressure side D of the airfoil 10 as a whole is concave and on the suction side S of the airfoil 10 is formed as a whole convex.
  • the chord length Se of the airfoil 10 is usually defined as a linear distance between the leading edge 12 and the trailing edge 14 of the respective profile section.
  • FIG. 2 shows a schematic representation of an airfoil 10, which does not belong to the subject invention.
  • the airfoil 10 is an airfoil of a turbomachine, in particular an adjustable guide vane of a gas turbine. It can be seen that the airfoil 10 has a thickening 18 on a pressure side D of the airfoil profile P, wherein the thickening 18 is arranged in a radially outer, housing-side region of the airfoil 10. In this illustration, the housing is not shown.
  • the airfoil profile P is formed and defined by an airfoil contour 16. It is clear that the thickening 18 as a convex contour 20 within the total concave contour of the pressure side D of the airfoil profile P is trained.
  • the extent E of the thickening 18 is selected such that the thickening 18 is formed in a spaced manner in total from the front edge 12 and the trailing edge 14 of the airfoil 10.
  • the distance between the front edge 12 and the thickening 18 in the housing-side end region of the blade 10 shown is approximately 15% of the chord length Se of the blade 10 in this end region. This distance is marked with Se 15 .
  • the thickening 18 in the housing-side end portion of the blade 10 has its greatest profile thickness d max. Starting from this largest profile thickness d max , the profile thickness d decreases in the direction of the housing-side end region of the airfoil 10 opposite end region - usually a hub region of a turbomachine - continuously up to a normal profile thickness d norm of the airfoil profile P without thickening 18 out. Furthermore, it is clear that the convex contour 20 of the thickening 18 at the ends of the thickening 18 runs tangentially to the concave contour of the pressure side D of the airfoil profile P. It can be seen that the thickening 18 is at least partially hump-shaped.
  • FIG. 3 shows a schematic representation of a arranged on a turntable 22 airfoil 10 without thickening according to the prior art.
  • the blade 10 is arranged on the turntable 22, that its front edge 12 protrudes on the turntable 22 and the rear edge 14 over the diameter of the turntable 22.
  • FIG. 4 shows a schematic representation of a arranged on a turntable 22 airfoil 10 according to a second Ausurugsform of the invention.
  • the turntable 22 serves to adjust the airfoil 10 and is rotatably mounted within a housing of the turbomachine.
  • the blade 10 is arranged on the turntable 22 in the illustrated embodiment such that its front edge 12 of the blade 10 on the turntable 22 and the rear edge 14 projects beyond the diameter of the turntable 22.
  • the thickening 18 is spaced from the leading edge 12 and the trailing edge 14 of the airfoil 10. In the illustrated housing-side end region of the airfoil 10, the thickening 18 their largest profile thickness d max .
  • the profile thickness d of the thickening 18 in turn decreases, starting from the largest profile thickness d max, continuously up to a normal profile thickness d norm of the airfoil profile P. Furthermore, it is clear that the thickening 18 extends maximally to a height from the housing and pressure-side region of the blade 10, which corresponds to 25% of the blade blade height Sh. From this representation of the airfoil profile P as well as in FIG. 2 As shown, it is clear that the greatest profile thickness d max of the thickening 18 protrudes beyond the imaginary line of the chord length Se. In this case, the in FIG. 4 shown thickening 18 relative to the in FIG. 2 shown thickening 18 a greater extent E on the pressure side D of the airfoil 10 on. Furthermore, it is clear that the thickening 18 ends outside the diameter of the turntable 22.
  • the exemplary embodiment shown is part of a stator blading of a compressor of a turbomachine, in particular of a high-pressure compressor of a gas turbine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Control Of Turbines (AREA)

Claims (9)

  1. Pale d'aube d'une machine d'écoulement, en particulier aube directrice réglable d'une turbine à gaz, avec au moins une surépaisseur (18) sur un côté refoulement (D) du profil de pale d'aube (P), la surépaisseur (18) étant disposée dans une zone de la pale d'aube (10) située à l'extérieur radialement côté carter, la surépaisseur (18) étant constituée à distance d'une arête avant (12) et d'une arête arrière (14) de la pale d'aube (10), caractérisée en ce que la pale d'aube (10) est, côté carter, raccordée à un plateau tournant (22) supporté de façon rotative dans un carter, dans laquelle l'arête arrière (14) dépasse au-dessus du plateau tournant (22), et la surépaisseur (18) se termine à l'extérieur du diamètre du plateau tournant (22).
  2. Pale d'aube selon la revendication 1, caractérisée en ce que la surépaisseur (18) est constituée en tant que contour convexe (20) à l'intérieur du contour globalement concave du côté refoulement (D) du profil de pale d'aube (P).
  3. Pale d'aube selon la revendication 1 ou 2, caractérisée en ce que la surépaisseur (18) présente sa plus grande épaisseur de profil (dmax) dans la zone d'extrémité, côté carter, de la pale d'aube (10).
  4. Pale d'aube selon la revendication 3, caractérisée en ce qu'une épaisseur de profil (d) de la surépaisseur (18) diminue de façon continue en partant de la plus grande épaisseur de profil (dmax) jusqu'à une épaisseur de profil normale (dnorm) du profil de pale d'aube (P) sans surépaisseur (18).
  5. Pale d'aube selon l'une des revendications précédentes, caractérisée en ce que la surépaisseur (18) s'étend au maximum jusqu'à une hauteur de la zone côté carter et refoulement de la pale d'aube (10) qui correspond à 25 % de la hauteur de pale d'aube (Sh).
  6. Pale d'aube selon l'une des revendications précédentes, caractérisée en ce que la distance entre l'arête avant (12) de la pale d'aube (10) et la surépaisseur (18) dans la zone d'extrémité, côté carter, de la pale d'aube (10) correspond au moins à 15 % d'une longueur de corde (Se) de la pale d'aube (10) dans cette zone d'extrémité.
  7. Paie d'aube selon l'une des revendications précédentes, caractérisée en ce que le contour convexe (20) de la surépaisseur (18) aux extrémités de la surépaisseur (18) est respectivement tangentiel au contour concave du côté refoulement (D) du profil de pale d'aube (P).
  8. Pale d'aube selon l'une des revendications précédentes, caractérisée en ce que la surépaisseur (18) est constituée au moins partiellement en forme de bourrelet ou de protubérance.
  9. Pale d'aube selon la revendication 1, caractérisée en ce que l'arête avant (12) de la pale d'aube (10) dépasse au-dessus du plateau tournant (22).
EP10754675.6A 2009-08-06 2010-08-05 Aube Active EP2462320B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102009036406A DE102009036406A1 (de) 2009-08-06 2009-08-06 Schaufelblatt
PCT/DE2010/000920 WO2011015193A2 (fr) 2009-08-06 2010-08-05 Aube

Publications (2)

Publication Number Publication Date
EP2462320A2 EP2462320A2 (fr) 2012-06-13
EP2462320B1 true EP2462320B1 (fr) 2016-10-12

Family

ID=43430143

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10754675.6A Active EP2462320B1 (fr) 2009-08-06 2010-08-05 Aube

Country Status (5)

Country Link
US (1) US9011081B2 (fr)
EP (1) EP2462320B1 (fr)
CN (1) CN102472111B (fr)
DE (1) DE102009036406A1 (fr)
WO (1) WO2011015193A2 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11421702B2 (en) 2019-08-21 2022-08-23 Pratt & Whitney Canada Corp. Impeller with chordwise vane thickness variation

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EP2696031B1 (fr) 2012-08-09 2015-10-14 MTU Aero Engines AG Aube pour une turbomachine et turbomachine correspondante
DE102012222953A1 (de) * 2012-12-12 2014-06-26 Honda Motor Co., Ltd. Flügelprofil für einen Axialströmungskompressor
WO2014128898A1 (fr) * 2013-02-21 2014-08-28 三菱重工業株式会社 Aube de rotor de turbine
US9896950B2 (en) * 2013-09-09 2018-02-20 Rolls-Royce Deutschland Ltd & Co Kg Turbine guide wheel
US20150275675A1 (en) * 2014-03-27 2015-10-01 General Electric Company Bucket airfoil for a turbomachine
FR3022295B1 (fr) * 2014-06-17 2019-07-05 Safran Aircraft Engines Aube de turbomachine comportant une ailette anti-tourbillons
US20160024930A1 (en) * 2014-07-24 2016-01-28 General Electric Company Turbomachine airfoil
US9995166B2 (en) * 2014-11-21 2018-06-12 General Electric Company Turbomachine including a vane and method of assembling such turbomachine
JP6639275B2 (ja) * 2016-03-10 2020-02-05 株式会社東芝 水力機械のガイドベーン及び水力機械
US11168566B2 (en) 2016-12-05 2021-11-09 MTU Aero Engines AG Turbine blade comprising a cavity with wall surface discontinuities and process for the production thereof
GB201702382D0 (en) * 2017-02-14 2017-03-29 Rolls Royce Plc Gas turbine engine fan blade
DE102017216620A1 (de) * 2017-09-20 2019-03-21 MTU Aero Engines AG Schaufel für eine Strömungsmaschine
EP3561226A1 (fr) * 2018-04-24 2019-10-30 Siemens Aktiengesellschaft Surface portante de compresseur
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine
FR3101914B1 (fr) * 2019-10-10 2021-11-12 Safran Aircraft Engines Aube de redresseur à calage variable comportant des ailettes aérodynamiques
GB202216273D0 (en) * 2022-11-02 2022-12-14 Rolls Royce Plc Fan blade for a gas turbine engine

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Publication number Priority date Publication date Assignee Title
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Also Published As

Publication number Publication date
CN102472111B (zh) 2017-03-01
US9011081B2 (en) 2015-04-21
WO2011015193A3 (fr) 2011-09-15
WO2011015193A2 (fr) 2011-02-10
US20120128480A1 (en) 2012-05-24
EP2462320A2 (fr) 2012-06-13
CN102472111A (zh) 2012-05-23
DE102009036406A1 (de) 2011-02-10

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