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EP1770244A1 - Compressor blade with chanferred tip - Google Patents

Compressor blade with chanferred tip Download PDF

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Publication number
EP1770244A1
EP1770244A1 EP06121050A EP06121050A EP1770244A1 EP 1770244 A1 EP1770244 A1 EP 1770244A1 EP 06121050 A EP06121050 A EP 06121050A EP 06121050 A EP06121050 A EP 06121050A EP 1770244 A1 EP1770244 A1 EP 1770244A1
Authority
EP
European Patent Office
Prior art keywords
blade
compressor
chamfer
apex
tangential
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Withdrawn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
EP06121050A
Other languages
German (de)
French (fr)
Inventor
Claude Lejars
Nicolas Triconnet
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1770244A1 publication Critical patent/EP1770244A1/en
Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F04D29/26—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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps 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
    • F05D2240/307—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 tip 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/29—Three-dimensional machined; miscellaneous
    • F05D2250/292—Three-dimensional machined; miscellaneous tapered

Definitions

  • the present invention relates to the field of gas turbine engines, and in particular the compressors of these engines.
  • It relates more particularly to a compressor blade for such an engine, having orthogonal axes longitudinal, tangential and radial, said blade extending radially between a foot and a top and longitudinally between a leading edge and a trailing edge, said blade being intended to rotate inside an outer shell of stator whose surface is covered with an abradable material.
  • a gas turbine engine traditionally comprises a combustion section and a turbine section disposed downstream of a compression section.
  • An annular passage for the flow of a gas stream extends axially through these different sections of the engine.
  • the gas stream is compressed by the compression section before being mixed and burned with a fuel in the combustion section.
  • the gases from this combustion then pass through the turbine section to provide propulsion thrust and drive the turbines, the latter being connected by a drive shaft to rotating members of the compression section.
  • the compression section of a gas turbine engine may comprise several compressors arranged successively in the axial direction of the engine, in order to increase the compression of the gas flow.
  • the compression section comprises successively a fan, a low pressure compressor and a high pressure compressor.
  • Each of these compressors comprises a rotating part (the rotor), a fixed part (the stator) and an envelope (the casing).
  • An inner rotor shell and an outer stator shell radially delimit the annular flow vein of the gas stream passing through the compressor.
  • the stator has a plurality of rows of stator vanes attached to the outer stator shell and also extending across the flow channel to the inner rotor shell.
  • the rotor of a compressor comprises meanwhile a plurality of rows of compressor blades which extend radially across flow vein from the inner rotor shell to the vicinity of the outer stator shell.
  • a technical solution which does not relate to the present invention, consists in covering the external shell of the stator with a layer of abrasive material, which is capable of abrading the top of the blade as soon as the blade comes into contact with the blade. the material.
  • Another technical solution consists in covering the external stator shell with a layer of an abradable material, that is to say that is capable of being abraded by the top of the blade if this last comes into contact with said material, which can occur in particular due to vibrations propagating in the engine.
  • the Applicant has found that when the top of the blade comes into contact with the abradable material, the top of the blade undergoes mechanical forces due to contact with the material.
  • the present invention proposes to provide, for a compressor whose external stator shroud is covered with an abradable material, a compressor blade to protect against the appearance of such cracks and a fortiori against the breaking of dawn .
  • the invention achieves its object by the fact that the apex of the blade has at least one chamfer to reduce the contact surface that may exist between the top of the blade and the abradable material.
  • the surface of the apex of the blade is shaped in such a way that in operation, when the blade is being unscrewed, this surface extends in a plane substantially tangential to the outer stator shell.
  • the contact surface that may exist between the apex of the blade and the abradable material substantially corresponds to the surface of the apex of the blade.
  • the chamfered part of the blade according to the present invention does not extend in a plane substantially tangential to the outer stator shell.
  • the contact surface may exist between the top of the blade according to the present invention and the abradable material is smaller than that which is likely to exist in the case known blades.
  • This reduction of the contact surface makes it possible to reduce the radial and tangential forces experienced by the top of the blade during the possible contact with the layer of abradable material and, consequently, to minimize vibrations in the blade.
  • said at least one chamfer extends over substantially the entire length of the blade, the length of the blade being obviously taken along the longitudinal direction of the blade.
  • leading and trailing edges constitute, at the top of the blade, the ends of a rope and, seen in a plane orthogonal to the rope, the chamfer advantageously comprises a portion inclined with respect to a tangential plane. at the top of dawn.
  • the blade has extrados and intrados surfaces extending radially between the foot and the crown, and longitudinally between the leading edge and the trailing edge, so that the radial height of the intrados is advantageously slightly larger than the radial height of the extrados.
  • said at least one chamfer is disposed on the side of the extrados.
  • the apex of the blade comprises a single chamfer and the angle of inclination of the chamfer is substantially the same over the entire length of the rope.
  • the angle of inclination opens towards the upper surface of the blade.
  • the angle of inclination is between 5 ° and 20 °.
  • the residual surface of the blade tip has a width of between 0.1 and 0.9 mm.
  • this residual surface extends in a plane tangential to the outer shell of the stator when the motor is in operation.
  • FIG. 1 partially represents a compression section 10 of a gas turbine engine 12.
  • This compression section has an annular flow stream 14 of the gas flow which extends in the longitudinal direction of the engine and radially between a ferrule internal 16 of a rotor disk and an outer shell 18 of a stator.
  • the inner ferrule is adapted to be rotated about a longitudinal axis 20 of the motor in the direction indicated by the arrow 22, while the outer shell of the stator remains fixed.
  • the direction of flow of the gas flow through the vein is shown in the figures by the arrow F.
  • the rotor disc has a plurality of rows of compressor blades 24 which extend radially between the inner ferrule 16 of the rotor disk and the outer ferrule 18 of the stator.
  • Each of the compressor blades 24 has a foot 28 which is engaged in a recess of the rotor disc, a lower blade portion 26 and an apex 30 opposite the foot 28.
  • the stator comprises a plurality of rows of straightener vanes 33 fixed integrally to the outer shell 18 of the stator and which also extend through the flow passage of the gas stream between the outer shell 18 of the stator and the inner ferrule 16 of rotor.
  • the rows of compressor blades 24 and rectifier 33 are arranged alternately in the axial direction 20 of the motor 12.
  • FIG. 2 represents the compressor vane 24 according to the invention, which preferentially but not necessarily belongs to the compressor vane row which is located at the downstream end of the compressor section.
  • the compressor blade 24 is provided with an orthogonal base having a longitudinal axis X, a tangential axis Y and a radial axis Z.
  • the longitudinal axis X extends in the direction of the flow F
  • the tangential axis Y extends in the direction of rotation 22 of the inner ferrule 16 of the rotor
  • the axis Z extends radially from the inner ferrule 16 to the outer ferrule 18.
  • Each compressor blade 24 comprises a lower surface 32 and an extrados surface 34 extending radially between the lower blade portion 26 and the top 30 of the compressor blade 24 on the one hand, and longitudinally between a leading edge 36 and a trailing edge 38.
  • the inner periphery of the outer stator shell 18 is covered with a layer of abradable material 40, that is to say capable of being abraded by the top of the compressor blade. if it is brought into contact with the material. This contact can occur due to the vibrations of the motor, given the small clearance existing between the top of the compressor blade 24 and the layer of material covering the stator outer shell 18.
  • the top of the blade has a chamfer 42.
  • This chamfer 42 extends preferentially over the entire length of the rope 44 of the top 30 of the blade 24 while extending substantially between the leading edge 36 and the trailing edge 38.
  • the chamfer 42 has a flat surface 46 inclined at an angle ⁇ with respect to a plane tangential to the apex of the blade.
  • the chamfer may have a curved surface, concave or convex.
  • the radial height h1 of the lower surface 32 is slightly greater than the radial height h2 of the upper surface 34.
  • the angle of inclination ⁇ is between 5 ° and 20 °. For this value range, there was a clear decrease in the modulus of tangential and radial forces applied to the top of the blade.
  • the edge of the chamfer 42 does not extend completely to the intrados 32 so that the apex of the blade has a residual contour surface 48 whose width is considered in one direction. Tangential is referenced e in FIG .
  • this residual surface 48 extends in a plane tangential to the outer shell of the stator 18 when the motor is in operation and has a width of between 0.1 and 0.9 mm.
  • the conformation of the top of the compressor blade 24 according to the present invention makes it possible to reduce the surface likely to come into contact with the layer of abradable material and, consequently, to minimize the mechanical stresses that the blade undergoes when it comes into contact with the layer of abradable material 40. This reduction in effort limits the appearance of vibrations likely to bring the dawn into resonance and, consequently, to cause its rupture.
  • compressor blades of a double-body turbomachine have been described, the present invention also applies to a single-body (without blower) turbomachine or to a triple-shaft turbomachine in which an intermediate compressor is arranged between the compressor. low pressure and the high pressure compressor.
  • the present invention further relates to a compressor rotor having at least one blade row according to the present invention, and a turbomachine comprising such a compressor rotor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The blade has orthogonal base with a longitudinal axis (X), tangential axis (Y), and radial axis (Z). The blade extends radially between a root and a tip (30), and longitudinally between a leading edge and a trailing edge. The blade is rotated inside an outer stator shell whose surface is covered of an abradable material. The tip has a chamfer (42) in order to reduce a contact surface (48) between the tip and the material. The surface (48) presents a width in the range of 0.1 mm to 0.9 mm in a tangential direction.

Description

La présente invention concerne le domaine des moteurs à turbine à gaz, et notamment les compresseurs de ces moteurs.The present invention relates to the field of gas turbine engines, and in particular the compressors of these engines.

Elle concerne plus particulièrement une aube de compresseur pour un tel moteur, ayant des axes orthogonaux longitudinal, tangentiel et radial, ladite aube s'étendant radialement entre un pied et un sommet et longitudinalement entre un bord d'attaque et un bord de fuite, ladite aube étant destinée à tourner à l'intérieur d'une virole externe de stator dont la surface est recouverte d'un matériau abradable.It relates more particularly to a compressor blade for such an engine, having orthogonal axes longitudinal, tangential and radial, said blade extending radially between a foot and a top and longitudinally between a leading edge and a trailing edge, said blade being intended to rotate inside an outer shell of stator whose surface is covered with an abradable material.

Un moteur à turbine à gaz comprend traditionnellement une section de combustion et une section de turbine disposée en aval d'une section de compression. Un passage annulaire pour l'écoulement d'un flux gazeux s'étend axialement à travers ces différentes sections du moteur. Le flux gazeux est comprimé par la section de compression avant d'être mélangé et brûlé avec un combustible dans la section de combustion. Les gaz issus de cette combustion traversent ensuite la section de turbine afin de fournir une poussée de propulsion et d'entraîner les turbines, ces dernières étant reliées par un arbre d'entraînement à des éléments rotatifs de la section de compression.A gas turbine engine traditionally comprises a combustion section and a turbine section disposed downstream of a compression section. An annular passage for the flow of a gas stream extends axially through these different sections of the engine. The gas stream is compressed by the compression section before being mixed and burned with a fuel in the combustion section. The gases from this combustion then pass through the turbine section to provide propulsion thrust and drive the turbines, the latter being connected by a drive shaft to rotating members of the compression section.

La section de compression d'un moteur à turbine à gaz peut comporter plusieurs compresseurs disposés successivement selon la direction axiale du moteur, afin d'augmenter la compression du flux gazeux.The compression section of a gas turbine engine may comprise several compressors arranged successively in the axial direction of the engine, in order to increase the compression of the gas flow.

Par exemple, dans le cas d'un moteur à double corps, considérée axialement depuis la partie amont du moteur, la section de compression comporte successivement une soufflante, un compresseur basse pression et un compresseur haute pression. Chacun des ces compresseurs comprend une partie tournante (le rotor), une partie fixe (le stator) et d'une enveloppe (le carter). Une virole interne de rotor et une virole externe de stator délimitent radialement la veine annulaire d'écoulement du flux gazeux traversant le compresseur.For example, in the case of a double-body engine, considered axially from the upstream portion of the engine, the compression section comprises successively a fan, a low pressure compressor and a high pressure compressor. Each of these compressors comprises a rotating part (the rotor), a fixed part (the stator) and an envelope (the casing). An inner rotor shell and an outer stator shell radially delimit the annular flow vein of the gas stream passing through the compressor.

Le stator comporte une pluralité de rangées d'aubes de redresseur fixées sur la virole externe de stator et s'étendant également en travers de la veine d'écoulement jusqu'à la virole interne de rotor.The stator has a plurality of rows of stator vanes attached to the outer stator shell and also extending across the flow channel to the inner rotor shell.

Le rotor d'un compresseur comporte quant à lui une pluralité de rangées d'aubes de compresseurs qui s'étendent radialement en travers de la veine d'écoulement depuis la virole interne de rotor jusqu'à proximité de la virole externe de stator.The rotor of a compressor comprises meanwhile a plurality of rows of compressor blades which extend radially across flow vein from the inner rotor shell to the vicinity of the outer stator shell.

Pour améliorer le rendement du compresseur, il est profitable de minimiser le jeu existant entre le sommet de l'aube de compresseur et la virole externe de stator. Une solution technique, qui ne concerne pas la présente invention, consiste à recouvrir la virole externe de stator d'une couche d'un matériau abrasif, qui soit apte à abraser le sommet de l'aube dès lors que cette dernière vient en contact avec le matériau.To improve the efficiency of the compressor, it is advantageous to minimize the clearance existing between the top of the compressor blade and the outer shell of the stator. A technical solution, which does not relate to the present invention, consists in covering the external shell of the stator with a layer of abrasive material, which is capable of abrading the top of the blade as soon as the blade comes into contact with the blade. the material.

Une autre solution technique, concernant la présente invention, consiste à recouvrir la virole externe de stator d'une couche d'un matériau abradable, c'est-à-dire qui soit apte à être abrasée par le sommet de l'aube si cette dernière vient en contact avec ledit matériau, ce qui peut se produire notamment en raison de vibrations se propageant dans le moteur.Another technical solution, concerning the present invention, consists in covering the external stator shell with a layer of an abradable material, that is to say that is capable of being abraded by the top of the blade if this last comes into contact with said material, which can occur in particular due to vibrations propagating in the engine.

La demanderesse a constaté que lorsque le sommet de l'aube vient en contact avec le matériau abradable, le sommet de l'aube subit des efforts mécaniques du fait du contact avec le matériau.The Applicant has found that when the top of the blade comes into contact with the abradable material, the top of the blade undergoes mechanical forces due to contact with the material.

Ces efforts mécaniques constituent une source de vibrations qui se propagent dans l'aube. Au-delà d'une certaine intensité et/ou fréquence, les vibrations peuvent faire entrer l'aube en résonance selon l'un de ces modes vibratoires, ce qui entraîne une fatigue de l'aube, voire une rupture.These mechanical forces constitute a source of vibrations that propagate in the dawn. Above a certain intensity and / or frequency, the vibrations can bring the dawn into resonance in one of these vibratory modes, which leads to fatigue of the blade, or even a break.

La demanderesse a d'ailleurs constaté que des criques longitudinales pouvaient apparaître dans une zone critique située notamment à proximité du pied de l'aube, qui est dès lors susceptible de rompre à cet endroit.The Applicant has also found that longitudinal cracks could appear in a critical area located particularly near the foot of the dawn, which is therefore likely to break at this location.

La présente invention se propose de fournir, pour un compresseur dont la virole externe de stator est recouverte d'un matériau abradable, une aube de compresseur permettant de se prémunir contre l'apparition de telles criques et a fortiori contre la rupture de l'aube.The present invention proposes to provide, for a compressor whose external stator shroud is covered with an abradable material, a compressor blade to protect against the appearance of such cracks and a fortiori against the breaking of dawn .

L'invention atteint son but par le fait que le sommet de l'aube présente au moins un chanfrein en vue de réduire la surface de contact susceptible d'exister entre le sommet de l'aube et le matériau abradable.The invention achieves its object by the fact that the apex of the blade has at least one chamfer to reduce the contact surface that may exist between the top of the blade and the abradable material.

Dans les aubes de compresseur déjà connues, la surface du sommet de l'aube est conformée de telle manière qu'en fonctionnement, lors du dévrillage de l'aube, cette surface s'étende dans un plan sensiblement tangentiel à la virole externe de stator.In the compressor blades already known, the surface of the apex of the blade is shaped in such a way that in operation, when the blade is being unscrewed, this surface extends in a plane substantially tangential to the outer stator shell.

Par conséquent, la surface de contact susceptible d'exister entre le sommet de l'aube et le matériau abradable correspond sensiblement à la surface du sommet de l'aube.Consequently, the contact surface that may exist between the apex of the blade and the abradable material substantially corresponds to the surface of the apex of the blade.

Au contraire, lors du fonctionnement du moteur, la partie chanfreinée de l'aube selon la présente invention ne s'étend pas dans un plan sensiblement tangentiel à la virole externe de stator.On the contrary, during operation of the motor, the chamfered part of the blade according to the present invention does not extend in a plane substantially tangential to the outer stator shell.

Dès lors, on comprend que lorsque le moteur est en fonctionnement, la surface de contact susceptible d'exister entre le sommet de l'aube selon la présente invention et le matériau abradable est plus petite que celle qui est susceptible d'exister dans le cas des aubes connues.Therefore, it is understood that when the engine is in operation, the contact surface may exist between the top of the blade according to the present invention and the abradable material is smaller than that which is likely to exist in the case known blades.

Cette réduction de la surface de contact permet de réduire les efforts radiaux et tangentiels subis par le sommet de l'aube lors de l'éventuel contact avec la couche de matériau abradable et, par conséquent, de minimiser les vibrations dans l'aube.This reduction of the contact surface makes it possible to reduce the radial and tangential forces experienced by the top of the blade during the possible contact with the layer of abradable material and, consequently, to minimize vibrations in the blade.

De manière préférentielle, ledit au moins un chanfrein s'étend sur sensiblement toute la longueur de l'aube, la longueur de l'aube étant évidemment prise selon la direction longitudinale de l'aube.Preferably, said at least one chamfer extends over substantially the entire length of the blade, the length of the blade being obviously taken along the longitudinal direction of the blade.

Par ailleurs, les bords d'attaque et de fuite constituent, au sommet de l'aube, les extrémités d'une corde et, vu dans un plan orthogonal à la corde, le chanfrein comporte avantageusement une partie inclinée par rapport à un plan tangentiel au sommet de l'aube.Moreover, the leading and trailing edges constitute, at the top of the blade, the ends of a rope and, seen in a plane orthogonal to the rope, the chamfer advantageously comprises a portion inclined with respect to a tangential plane. at the top of dawn.

De manière connue, l'aube comporte des surfaces extrados et intrados s'étendant radialement entre le pied et le sommet, et longitudinalement entre le bord d'attaque et le bord de fuite, telle manière que la hauteur radiale de l'intrados est avantageusement légèrement plus grande que la hauteur radiale de l'extrados.In known manner, the blade has extrados and intrados surfaces extending radially between the foot and the crown, and longitudinally between the leading edge and the trailing edge, so that the radial height of the intrados is advantageously slightly larger than the radial height of the extrados.

On comprend donc que ledit au moins un chanfrein est disposé du côté de l'extrados.It is therefore understood that said at least one chamfer is disposed on the side of the extrados.

Selon un mode de réalisation préférentiel, le sommet de l'aube comporte un unique chanfrein et l'angle d'inclinaison du chanfrein est sensiblement le même sur toute la longueur de la corde.According to a preferred embodiment, the apex of the blade comprises a single chamfer and the angle of inclination of the chamfer is substantially the same over the entire length of the rope.

Préférentiellement, l'angle d'inclinaison s'ouvre vers l'extrados de l'aube.Preferably, the angle of inclination opens towards the upper surface of the blade.

De façon avantageuse, l'angle d'inclinaison est compris entre 5° et 20°.Advantageously, the angle of inclination is between 5 ° and 20 °.

De façon encore avantageuse, la surface résiduelle du sommet de l'aube présente une largeur comprise entre 0,1 et 0,9 mm.Still advantageously, the residual surface of the blade tip has a width of between 0.1 and 0.9 mm.

De manière préférentielle, cette surface résiduelle s'étend dans un plan tangentiel à la virole externe de stator lorsque le moteur est en fonctionnement.Preferably, this residual surface extends in a plane tangential to the outer shell of the stator when the motor is in operation.

D'autres caractéristiques et avantages de l'invention apparaîtront mieux à la lecture de la description qui suit d'un mode de réalisation de l'invention donné à titre d'exemple non limitatif.Other features and advantages of the invention will appear better on reading the following description of an embodiment of the invention given by way of non-limiting example.

La description se réfère aux figures annexées sur lesquelles :

  • La figure 1 est une vue partielle et en coupe longitudinale d'une section de compression d'un moteur à turbine à gaz ;
  • La figure 2 représente une aube de compresseur selon la présente invention lorsque son sommet est en contact avec une couche d'abradable d'une virole externe de stator ;
  • La figure 3 est une vue de dessus d'une aube de compresseur selon la présente invention ;
  • La figure 4 est une vue en coupe partielle dans un plan orthogonal à la corde du sommet d'une aube selon la présente invention.
The description refers to the appended figures in which:
  • Figure 1 is a partial view in longitudinal section of a compression section of a gas turbine engine;
  • FIG. 2 represents a compressor blade according to the present invention when its top is in contact with an abradable layer of an outer stator shell;
  • Figure 3 is a top view of a compressor blade according to the present invention;
  • Figure 4 is a partial sectional view in a plane orthogonal to the rope of the top of a blade according to the present invention.

La figure 1 représente partiellement une section de compression 10 d'un moteur à turbine à gaz 12. Cette section de compression présente une veine annulaire 14 d'écoulement des flux gazeux qui s'étend dans la direction longitudinale du moteur et radialement entre une virole interne 16 d'un disque de rotor et une virole externe 18 d'un stator. La virole interne est apte à être mise en rotation autour d'un axe longitudinal 20 du moteur dans le sens indiqué par la flèche 22, tandis que la virole externe de stator reste fixe. Le sens d'écoulement du flux gazeux à travers la veine est représenté sur les figures par la flèche F. FIG. 1 partially represents a compression section 10 of a gas turbine engine 12. This compression section has an annular flow stream 14 of the gas flow which extends in the longitudinal direction of the engine and radially between a ferrule internal 16 of a rotor disk and an outer shell 18 of a stator. The inner ferrule is adapted to be rotated about a longitudinal axis 20 of the motor in the direction indicated by the arrow 22, while the outer shell of the stator remains fixed. The direction of flow of the gas flow through the vein is shown in the figures by the arrow F.

Le disque de rotor comporte une pluralité de rangées d'aubes de compresseur 24 qui s'étendent radialement entre la virole interne 16 du disque de rotor et la virole externe 18 de stator. Chacune des aubes de compresseurs 24 présente un pied 28 qui vient s'emmancher dans un évidement du disque de rotor, une partie inférieure de pale 26 ainsi qu'un sommet 30 opposé au pied 28. The rotor disc has a plurality of rows of compressor blades 24 which extend radially between the inner ferrule 16 of the rotor disk and the outer ferrule 18 of the stator. Each of the compressor blades 24 has a foot 28 which is engaged in a recess of the rotor disc, a lower blade portion 26 and an apex 30 opposite the foot 28.

Le stator comporte quant à lui une pluralité de rangées d'aubes de redresseur 33 fixées solidairement à la virole externe 18 de stator et qui s'étendent également à travers la veine d'écoulement du flux gazeux entre la virole externe 18 de stator et la virole interne 16 de rotor. Comme on le voit sur la figure 1, les rangées d'aubes de compresseur 24 et de redresseur 33 sont disposées alternativement selon la direction axiale 20 du moteur 12. The stator comprises a plurality of rows of straightener vanes 33 fixed integrally to the outer shell 18 of the stator and which also extend through the flow passage of the gas stream between the outer shell 18 of the stator and the inner ferrule 16 of rotor. As can be seen in FIG. 1, the rows of compressor blades 24 and rectifier 33 are arranged alternately in the axial direction 20 of the motor 12.

La figure 2 représente l'aube de compresseur 24 selon l'invention, celle-ci appartenant préférentiellement mais non nécessairement à la rangée d'aubes de compresseur qui est située à l'extrémité aval de la section de compresseur.FIG. 2 represents the compressor vane 24 according to the invention, which preferentially but not necessarily belongs to the compressor vane row which is located at the downstream end of the compressor section.

L'aube de compresseur 24 selon l'invention est munie d'une base orthogonale comportant un axe longitudinal X, un axe tangentiel Y et un axe radial Z. L'axe longitudinal X s'étend dans la direction de l'écoulement F, l'axe tangentiel Y s'étend dans le sens de rotation 22 de la virole interne 16 de rotor, tandis que l'axe Z s'étend radialement depuis la virole interne 16 vers la virole externe 18. The compressor blade 24 according to the invention is provided with an orthogonal base having a longitudinal axis X, a tangential axis Y and a radial axis Z. The longitudinal axis X extends in the direction of the flow F, the tangential axis Y extends in the direction of rotation 22 of the inner ferrule 16 of the rotor, while the axis Z extends radially from the inner ferrule 16 to the outer ferrule 18.

Chaque aube de compresseur 24 comporte une surface intrados 32 et une surface extrados 34 s'étendant radialement entre la partie inférieure de pale 26 et le sommet 30 de l'aube de compresseur 24 d'une part, et longitudinalement entre un bord d'attaque 36 et un bord de fuite 38. Each compressor blade 24 comprises a lower surface 32 and an extrados surface 34 extending radially between the lower blade portion 26 and the top 30 of the compressor blade 24 on the one hand, and longitudinally between a leading edge 36 and a trailing edge 38.

Comme on le voit sur la figure 2, le pourtour interne de la virole externe de stator 18 est recouverte d'une couche de matériau abradable 40, c'est-à-dire apte à être abrasé par le sommet de l'aube de compresseur si celle-ci est amenée à entrer en contact avec le matériau. Ce contact peut se produire en raison des vibrations du moteur, compte tenu du faible jeu existant entre le sommet de l'aube de compresseur 24 et la couche de matériau recouvrant la virole externe de stator 18. As can be seen in FIG. 2, the inner periphery of the outer stator shell 18 is covered with a layer of abradable material 40, that is to say capable of being abraded by the top of the compressor blade. if it is brought into contact with the material. This contact can occur due to the vibrations of the motor, given the small clearance existing between the top of the compressor blade 24 and the layer of material covering the stator outer shell 18.

Pour minimiser les efforts subis par l'aube de compresseur lorsqu'elle entre en contact avec la couche de matériau abradable 40, le sommet de l'aube, représenté sur la figure 4, présente un chanfrein 42. To minimize the forces experienced by the compressor blade when it comes into contact with the layer of abradable material 40, the top of the blade, shown in Figure 4, has a chamfer 42.

Ce chanfrein 42 s'étend préférentiellement sur toute la longueur de la corde 44 du sommet 30 de l'aube 24 tout en s'étendant substantiellement entre le bord d'attaque 36 et le bord de fuite 38. This chamfer 42 extends preferentially over the entire length of the rope 44 of the top 30 of the blade 24 while extending substantially between the leading edge 36 and the trailing edge 38.

De manière préférentielle, le chanfrein 42 présente une surface plane 46 inclinée d'un angle β par rapport à un plan tangentiel au sommet de l'aube. Toutefois, sans sortir du cadre de la présente invention, le chanfrein peut présenter une surface courbe, concave ou convexe.Preferably, the chamfer 42 has a flat surface 46 inclined at an angle β with respect to a plane tangential to the apex of the blade. However, without departing from the scope of the present invention, the chamfer may have a curved surface, concave or convex.

Il en résulte que la hauteur radiale h1 de l'intrados 32 est légèrement plus grande que la hauteur radiale h2 de l'extrados 34. As a result, the radial height h1 of the lower surface 32 is slightly greater than the radial height h2 of the upper surface 34.

Selon une caractéristique avantageuse de l'invention, l'angle d'inclinaison β est compris entre 5° et 20°. Pour cette plage de valeur, on a constaté une nette diminution du module des efforts tangentiel et radial appliqués sur le sommet de l'aube.According to an advantageous characteristic of the invention, the angle of inclination β is between 5 ° and 20 °. For this value range, there was a clear decrease in the modulus of tangential and radial forces applied to the top of the blade.

Selon une variante avantageuse, le bord du chanfrein 42 ne s'étend pas tout à fait jusqu'à l'intrados 32 de telle sorte que le sommet de l'aube présente une surface de contour résiduelle 48, dont la largeur considérée dans une direction tangentielle est référencée e sur la figure 4. According to an advantageous variant, the edge of the chamfer 42 does not extend completely to the intrados 32 so that the apex of the blade has a residual contour surface 48 whose width is considered in one direction. Tangential is referenced e in FIG .

De manière avantageuse, cette surface résiduelle 48 s'étend dans un plan tangentiel à la virole externe de stator 18 lorsque le moteur est en fonctionnement et présente une largeur comprise entre 0,1 et 0,9 mm.Advantageously, this residual surface 48 extends in a plane tangential to the outer shell of the stator 18 when the motor is in operation and has a width of between 0.1 and 0.9 mm.

La conformation du sommet de l'aube de compresseur 24 selon la présente invention permet de réduire la surface susceptible de venir en contact avec la couche de matériau abradable et, par voie de conséquence, de minimiser les efforts mécaniques que l'aube subit lorsqu'elle vient en contact avec la couche de matériau abradable 40. Cette diminution des efforts limite l'apparition de vibrations susceptibles de faire entrer l'aube en résonance et, par suite, d'entraîner sa rupture.The conformation of the top of the compressor blade 24 according to the present invention makes it possible to reduce the surface likely to come into contact with the layer of abradable material and, consequently, to minimize the mechanical stresses that the blade undergoes when it comes into contact with the layer of abradable material 40. This reduction in effort limits the appearance of vibrations likely to bring the dawn into resonance and, consequently, to cause its rupture.

Bien que l'on ait décrit des aubes de compresseur d'une turbomachine double corps, la présente invention s'applique également à une turbomachine simple corps (sans soufflante) ou à une turbomachine triple corps dans laquelle un compresseur intermédiaire est disposé entre le compresseur basse pression et le compresseur haute pression.Although compressor blades of a double-body turbomachine have been described, the present invention also applies to a single-body (without blower) turbomachine or to a triple-shaft turbomachine in which an intermediate compressor is arranged between the compressor. low pressure and the high pressure compressor.

La présente invention concerne en outre un rotor de compresseur comportant au moins une rangée d'aube selon la présente invention, ainsi qu'une turbomachine comportant un tel rotor de compresseur.The present invention further relates to a compressor rotor having at least one blade row according to the present invention, and a turbomachine comprising such a compressor rotor.

Claims (8)

Aube de compresseur (24) pour disque rotatif d'un moteur à turbine (12) ayant des axes orthogonaux longitudinal (X), tangentiel (Y) et radial (Z), ladite aube (24) s'étendant radialement entre un pied (28) et un sommet (30) et longitudinalement entre un bord d'attaque (36) et un bord de fuite (38), ladite aube (24) étant destinée à tourner à l'intérieur d'une virole externe de stator (18) dont la surface est recouverte d'un matériau abradable (40), le sommet (30) de l'aube (24) présentant au moins un chanfrein (42) en vue de réduire la surface de contact (48) susceptible d'exister entre le sommet de l'aube (24) et le matériau abradable (40), caractérisé en ce que, vue selon une direction tangentielle, la surface de contact résiduelle (48) du sommet de l'aube présente une largeur (e) comprise entre 0,1 et 0,9 mm.A compressor blade (24) for a rotating disk of a turbine engine (12) having orthogonal longitudinal (X), tangential (Y) and radial (Z) axes, said blade (24) extending radially between a foot ( 28) and a top (30) and longitudinally between a leading edge (36) and a trailing edge (38), said blade (24) being intended to rotate inside an outer stator shell (18). ) whose surface is covered with an abradable material (40), the apex (30) of the blade (24) having at least one chamfer (42) to reduce the contact surface (48) that may exist between the apex of the blade (24) and the abradable material (40), characterized in that , seen in a tangential direction, the residual contact surface (48) of the apex of the blade has a width (e) included between 0.1 and 0.9 mm. Aube de compresseur selon la revendication 1, caractérisé en ce que ledit au moins un chanfrein (42) s'étend sur sensiblement toute la longueur de l'aube (24).Compressor blade according to claim 1, characterized in that said at least one chamfer (42) extends over substantially the entire length of the blade (24). Aube de compresseur selon la revendication 1 ou 2, caractérisé en ce qu'au sommet (30) de l'aube (24), les bords d'attaque (36) et de fuite (38) constituent les extrémités d'une corde (44) et en ce que, vu dans un plan orthogonal à la corde, le chanfrein (42) comporte une partie inclinée (46) par rapport à un plan tangentiel au sommet (30) de l'aube.Compressor blade according to claim 1 or 2, characterized in that at the top (30) of the blade (24), the leading (36) and trailing edges (38) constitute the ends of a rope ( 44) and in that , seen in a plane orthogonal to the rope, the chamfer (42) has an inclined portion (46) with respect to a plane tangential to the apex (30) of the blade. Aube de compresseur selon l'une quelconque des revendications 1 à 3, caractérisé en ce que l'aube comporte des surfaces extrados (34) et intrados (32) s'étendant radialement entre le pied (28) et le sommet (30) et longitudinalement entre le bord d'attaque (36) et le bord de fuite (38), et en ce que la hauteur radiale de l'intrados (h1) est légèrement plus grande que la hauteur radiale de l'extrados (h2).Compressor blade according to any one of claims 1 to 3, characterized in that the blade has extrados (34) and intrados (32) surfaces extending radially between the foot (28) and the top (30) and longitudinally between the leading edge (36) and the trailing edge (38), and in that the radial height of the intrados (h1) is slightly greater than the radial height of the extrados (h2). Aube de compresseur selon l'une quelconque des revendications 1 à 4, caractérisé en ce qu'au sommet (30) de l'aube (24), les bords d'attaque (36) et de fuite (38) constituent les extrémités d'une corde (44), en ce qu'il comporte un unique chanfrein (42) et en ce que l'angle d'inclinaison (β) du chanfrein (42) est sensiblement le même sur toute la longueur de la corde (44).Compressor blade according to one of Claims 1 to 4, characterized in that at the top (30) of the blade (24), the leading (36) and trailing (38) edges constitute the ends of the blade. a rope (44), in that it comprises a single chamfer (42) and in that the angle of inclination (β) of the chamfer (42) is substantially the same over the entire length of the rope (44); ). Aube de compresseur selon la revendication 5, caractérisé en ce que l'angle d'inclinaison (β) est compris entre 5° et 20°.Compressor blade according to claim 5, characterized in that the angle of inclination (β) is between 5 ° and 20 °. Rotor de compresseur caractérisé en ce qu'il comporte au moins une rangée d'aubes selon l'une quelconque des revendications 1 à 6.Compressor rotor characterized in that it comprises at least one row of blades according to any one of claims 1 to 6. Turbomachine caractérisée en ce qu'elle comporte un rotor selon la revendication 7.Turbomachine characterized in that it comprises a rotor according to claim 7.
EP06121050A 2005-09-30 2006-09-21 Compressor blade with chanferred tip Withdrawn EP1770244A1 (en)

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FR0510010A FR2891594A1 (en) 2005-09-30 2005-09-30 AUBE COMPRESSOR WITH CHANFREINE TOP

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2309097A1 (en) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Airfoil and corresponding guide vane, blade, gas turbine and turbomachine
FR2962762A1 (en) * 2010-07-19 2012-01-20 Snecma Movable blade for use in rotor disk of high pressure compressor of e.g. turbojet engine of aircraft, has front side surface provided with cutting face at its radially outer end, where cutting face forms non-zero cutting angle with surface
US10669866B2 (en) 2012-12-19 2020-06-02 Rolls-Royce Plc Composite aerofoil structure with a cutting edge tip portion
US10876415B2 (en) 2014-06-04 2020-12-29 Raytheon Technologies Corporation Fan blade tip as a cutting tool

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100135822A1 (en) * 2008-11-28 2010-06-03 Remo Marini Turbine blade for a gas turbine engine
IT1401661B1 (en) * 2010-08-25 2013-08-02 Nuova Pignone S R L FORM OF AODINAMIC PROFILE BY COMPRESSOR.
FR2964585B1 (en) * 2010-09-15 2012-10-05 Snecma METHOD AND MACHINE TOOL FOR ADJUSTING THE CONTOUR OF A WORKPIECE
GB201017797D0 (en) * 2010-10-21 2010-12-01 Rolls Royce Plc An aerofoil structure
US8790088B2 (en) * 2011-04-20 2014-07-29 General Electric Company Compressor having blade tip features
US20130156584A1 (en) * 2011-12-16 2013-06-20 Carney R. Anderson Compressor rotor with internal stiffening ring of distinct material
US11066937B2 (en) 2014-06-04 2021-07-20 Raytheon Technologies Corporation Cutting blade tips
US9932839B2 (en) * 2014-06-04 2018-04-03 United Technologies Corporation Cutting blade tips
DE102014212652A1 (en) * 2014-06-30 2016-01-14 MTU Aero Engines AG flow machine
US20160238021A1 (en) * 2015-02-16 2016-08-18 United Technologies Corporation Compressor Airfoil
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DE102021130682A1 (en) 2021-11-23 2023-05-25 MTU Aero Engines AG Airfoil for a turbomachine
CN115977999B (en) * 2023-01-12 2024-07-23 山东科技大学 Subsonic compressor, rotor blade and flow stability expansion control method

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US899319A (en) * 1906-10-08 1908-09-22 Charles Algernon Parsons Turbine.
US1828409A (en) * 1929-01-11 1931-10-20 Westinghouse Electric & Mfg Co Reaction blading
DE560589C (en) * 1932-10-04 Franz Burghauser Dipl Ing Device for reducing the blade gap loss of steam and gas turbines
DE815971C (en) * 1949-12-22 1951-10-08 Franz Burghauser Steam or gas turbine blade with little radial clearance loss
GB946794A (en) * 1961-03-06 1964-01-15 Colchester Woods Improvements in and relating to axial flow fans or compressors
FR2615254A1 (en) * 1987-05-13 1988-11-18 Snecma MOBILE BLOWER BLADE COMPRISING AN END END
FR2623569A1 (en) * 1987-11-19 1989-05-26 Snecma VANE OF COMPRESSOR WITH DISSYMMETRIC LETTLE LETCHES
FR2711181A1 (en) * 1993-10-15 1995-04-21 United Technologies Corp Methods and devices for reducing stress on the tips of turbine or compressor blades, as well as motors or compressors using such methods and devices.
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4274806A (en) * 1979-06-18 1981-06-23 General Electric Company Staircase blade tip

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE560589C (en) * 1932-10-04 Franz Burghauser Dipl Ing Device for reducing the blade gap loss of steam and gas turbines
US899319A (en) * 1906-10-08 1908-09-22 Charles Algernon Parsons Turbine.
US1828409A (en) * 1929-01-11 1931-10-20 Westinghouse Electric & Mfg Co Reaction blading
DE815971C (en) * 1949-12-22 1951-10-08 Franz Burghauser Steam or gas turbine blade with little radial clearance loss
GB946794A (en) * 1961-03-06 1964-01-15 Colchester Woods Improvements in and relating to axial flow fans or compressors
FR2615254A1 (en) * 1987-05-13 1988-11-18 Snecma MOBILE BLOWER BLADE COMPRISING AN END END
FR2623569A1 (en) * 1987-11-19 1989-05-26 Snecma VANE OF COMPRESSOR WITH DISSYMMETRIC LETTLE LETCHES
FR2711181A1 (en) * 1993-10-15 1995-04-21 United Technologies Corp Methods and devices for reducing stress on the tips of turbine or compressor blades, as well as motors or compressors using such methods and devices.
US6086328A (en) * 1998-12-21 2000-07-11 General Electric Company Tapered tip turbine blade

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2309097A1 (en) * 2009-09-30 2011-04-13 Siemens Aktiengesellschaft Airfoil and corresponding guide vane, blade, gas turbine and turbomachine
FR2962762A1 (en) * 2010-07-19 2012-01-20 Snecma Movable blade for use in rotor disk of high pressure compressor of e.g. turbojet engine of aircraft, has front side surface provided with cutting face at its radially outer end, where cutting face forms non-zero cutting angle with surface
US10669866B2 (en) 2012-12-19 2020-06-02 Rolls-Royce Plc Composite aerofoil structure with a cutting edge tip portion
US10876415B2 (en) 2014-06-04 2020-12-29 Raytheon Technologies Corporation Fan blade tip as a cutting tool
EP2952685B1 (en) * 2014-06-04 2020-12-30 United Technologies Corporation Airfoil for a gas turbine engine, a gas turbine engine and a method for reducing frictional heating between airfoils and a case of a gas turbine engine

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