EP2473743A1 - Aube mobile de compresseur pour un compresseur axial - Google Patents

Aube mobile de compresseur pour un compresseur axial

Info

Publication number
EP2473743A1
EP2473743A1 EP10743094A EP10743094A EP2473743A1 EP 2473743 A1 EP2473743 A1 EP 2473743A1 EP 10743094 A EP10743094 A EP 10743094A EP 10743094 A EP10743094 A EP 10743094A EP 2473743 A1 EP2473743 A1 EP 2473743A1
Authority
EP
European Patent Office
Prior art keywords
blade
chord
compressor
profile
profiles
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.)
Granted
Application number
EP10743094A
Other languages
German (de)
English (en)
Other versions
EP2473743B1 (fr
Inventor
Georg Kröger
Christian Cornelius
Eberhard Nicke
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.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Siemens AG
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
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 Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Priority to EP10743094.4A priority Critical patent/EP2473743B1/fr
Publication of EP2473743A1 publication Critical patent/EP2473743A1/fr
Application granted granted Critical
Publication of EP2473743B1 publication Critical patent/EP2473743B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • 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
    • 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
    • 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
    • F05D2250/712—Shape curved concave
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/02—Formulas of curves
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S416/00—Fluid reaction surfaces, i.e. impellers
    • Y10S416/05—Variable camber or chord length

Definitions

  • the invention relates to a Ver Whyrlaufschaufei for an axial compressor according to the features of the preamble of claim 1.
  • Compressor blades for axial compressors are known from the prior art in a large scale.
  • EP 0 991 866 B1 discloses a compressor blade having a profile whose suction side contour has a radius of curvature smaller than half the length of the chord on a suction side intersection with a reference line perpendicular to the chord at 5% of the chord length.
  • Unevenness of the flow at the exit of subsonic compressor blades is reduced due to the reduction of the pressure gradient.
  • the pressure gradient in front and middle area in the passages between the blades are reduced.
  • the leading edge region is rotated in the direction of the suction side of the airfoil, whereby the front, ie upstream, region of the airfoil has a reverse curvature compared to the rearward, ie downstream, region of the airfoil.
  • the object of the invention is to provide a compaction has terlaufschaufei with a blade tip, which drove particularly low leakage currents and radial clearance losses during loading ⁇ in a turbomachine.
  • a compressor rotor for an axial compressor with a curved blade, which comprises a pressure side wall and a suction side wall, which in each case from a common leading edge to a common trailing edge and on the other hand to form a span of a mounting side blade end to an airfoil tip, wherein for each airfoil height present along the span, the airfoil has a profile with a suction side contour and a pressure side contour, an at least partially curved skeleton line and a straight chord, which contours, skeleton line and chord each extend from one on the leading edge arranged leading edge point to a rear edge point arranged on the trailing edge, wherein that at least one of the skeleton lines of the profile in a region of the blade tip (ie some skeleton lines of the blade spit zseit profiles) have at least two turning points.
  • the invention is based on the finding that losses in the radial gap can be reduced if a gap vortex which is also responsible for the losses is correspondingly influenced.
  • the gap vortex which is generated and driven by the gap mass flow, compared to a conventional airfoil tip profile, now later, ie at a downstream point, arise.
  • the splitting vortex which thus arises later relative to the conventional profile, can be explained by a lower load on the improved profile at the leading edge.
  • the gap vortex Due to the suction-side contour of the profile bend, the gap vortex develops along a line which also has a bend downstream of the bend of the suction side contour.
  • the Early bending of the gap vortex coincides with the strong to ⁇ the mass flow density increased in the radial gap to its maximum and the subsequent decrease of the same together.
  • the gap vortex line depends on its kink at a larger angle from the suction side wall than in the herkömmli ⁇ chen profile of the case. As a result, the gap ⁇ vortex continues to run away from the suction side at a greater distance than in conventional profiling.
  • the larger angle is due to the larger gradient of the mass flow density of the Spaltströmung both in the increase and in the waste.
  • the first of the two turning points in the case of perpendicular projection on the chord on this one first projection point, which is removed from the leading edge point between 10% and 30% of the length of the chord.
  • the second of the two points of inflection in the case of a vertical projection on the chord, predetermines the chord on this one second projection point, which is 30% to 50% of the length of the chord from the leading edge point.
  • the two turning points lie apart Minim ⁇ least 3% of the length of the chord.
  • the skeleton lines of the profiles comprise a front portion which extends from the leading edge point up to extends an end point of the front portion, the Pro ⁇ jection point is at a vertical projection on the chord from the leading edge point between 2% and 10% of the length of Pro ⁇ filsehne removed, wherein at least some of the front sections, preferably all of the front sections of the blade tip side profiles a Radius of curvature aufwei ⁇ sen, which is greater than 100 times the chord.
  • the front portions of the skeleton line of blade tip side profiles respectively correspond to a straight line, or at least almost.
  • the profile is symmetrical in the relevant front section-virtually without buckling-which means that even the local velocity distribution around the blade tip side leading edge region of the blade leaves virtually no pressure potential from the pressure side to the suction side.
  • the pressure ⁇ potential between the pressure side and suction side in the leading edge ⁇ area as the cause of the occurrence of the crevasse vortex and thus as a cause for the gap losses is considered here causes this relief of the leading edge region attenuation and a delayed, ie downstream ⁇ kick the crevice vortex
  • the Saugateenkon ⁇ tur and the pressure side contour of blade tip side profiles in the front portion of the skeleton line are symmet ⁇ risch trained or in a wedge shape with almost straight contour sections on the suction side and pressure side.
  • each front portion of an angle of incidence with respect to a ankom ⁇ Menden gas flow whereby in addition to or instead of the almost straight front camber line portion of at least some of the angle of attack, but preferably all Anstell ⁇ angle of the blade sharp side profiles are smaller than the angle of attack of the remaining Profiles of the airfoil.
  • the angle of the front portion Skelettlinien- Schaufelspitz sided profiles this case are smaller than 10 °, preferably even 0 °.
  • the metal entry angle of the blade tip-side profiles is significantly smaller than the metal entry angle of the others Profiles of the airfoil. It can thus be said that the leading edge region of the blade tip, in
  • leading edge points preferably all leading edge points of the blade tip-side profiles
  • the leading edge of the profiles for blade tips is preceded by an extension of the profile to the front - in the upstream direction - compared to the rest of the leading edge. This has the consequence that no radia ⁇ ler pressure gradient in the leading edge region of the blade airfoil can work top, so that it can not come to a potential between pressure side and suction side and in the radial pressure distribution.
  • the remaining area of the airfoil, from a mounting-side airfoil end to a blade height of at least 80% of the span, may be profiled in a conventional manner.
  • the invention in principle relates to a modi fied ⁇ blade tip arranged in a ring compressor rotor blades for axial compressors.
  • the skeleton lines comprise a rear portion, which in each case extends from a starting point of the rear portion to the Hin ⁇ terkantentician, wherein the rear portion of ⁇ at least some, preferably all shovel tip skeleton lines has a greater curvature than the rear portions of skeleton lines of the other profiles of the show ⁇ felblatts. Consequently, the outlet metal angles of blade tip-side profiles are smaller than the outlet metal angles of profiles at the level of half the span or in the region of the attachment-side, ie hub-side
  • the trailing edge is therefore more curved in the blade tip area than in the remaining area of the blade.
  • the increased curvature leads to a larger work conversion in the preferably rear 40% of the airfoil, so that overall the load of the airfoil is shifted to the rear.
  • This embodiment can serve as a balance of relief on the leading edge to achieve despite the relief of the blade tip side profile in the front region of the chord still a high work transformation.
  • the flow of the following guide blade in the outer annular wall region can thus also be improved by reducing the blockage in the blade tip region of the compressor blade. This reduces the local misfire of the downstream vanes.
  • Preferred dimensions are at least some, preferably all of the blade tip-side profiles in the "Aft-Loaded Design” and the other, ie not schaufelspitz solutionen profiles in the "Front Loaded Design” configured.
  • the person responsible for the gap losses spina bifida can be extremely efficient affected if the Saugsei ⁇ tenkontur and the pressure side contour at least three consecutive curved sections with alternating sign have, which adjoin adjacent curved portions in each case a turning point.
  • the blade tip is freestanding.
  • the respective profiles are selected so that adjusts itself in a maximum at ⁇ closing suction side of the Sauguzeenkontur with a maximum length of 15% of the length of the chord, a gradient of speed, the slope is maximum.
  • the gap vortex is severely underserved for its size, which causes it to move away from the surface of the suction side at a larger angle.
  • the further explanation of the invention is based on the embodiment shown in the drawing.
  • FIGs 2, 3, 6 the velocity distributions along the
  • FIG 8 shows the topology of Spaltwirbeltraj ectors for the profile according to the invention and the conventional profile and
  • Figures 9, 10 are perspective views of the freest ⁇ rising blade tip of a erfindungsge ⁇ MAESSEN Ver Whyrlaufschaufei.
  • FIG 9 and FIG 10 each show a freestanding compressor ⁇ moving blade 10 from different perspectives.
  • their Airfoil 12 includes a pressure sidewall 14 and a suction sidewall 16, which on the one hand in each case open from a ⁇ common itself, is traversed by the gas flow leading edge 18 to a common trailing edge 20 and on the other dung a span of a in Figures 9 and 10 with formation not shown fastening side airfoil end to a blade tip 22 extend.
  • the attachment-side airfoil end can be a platform and a platform arranged thereon in a known manner Shovel be provided. Actuating depending on the type and manner of the blade root of the Befes- Verêtrlaufschaufei 10 ent ⁇ neither dovetail, firtree or hammer-shaped.
  • the compressor rotor may also be welded to a rotor. Mounted in the rotor of an axial compressor the Orien ⁇ orientation of the blade 12 is such that the
  • Airfoil 12 extends from the front edge 18 to the trailing edge 20 in approximately the axial direction of the axial compressor, which is designated in the coordinate system associated with FIG 9 and FIG with the axis X.
  • the radial direction of the axial displace ⁇ dichters coincides with the Z-axis of the coordinate system shown, and the tangential direction, that is, the circumferential direction with the Y-axis. A span of the airfoil 12 is thus detected in the Z-axis direction.
  • compressor blades 10 are designed for axial compressors in such a way that along a rectilinear or slightly curved, not shown
  • Stacking axis different or identical profiles are ⁇ strung to ⁇ whose enclosed space the Define the blade 12.
  • each profile has a centroid on the stack axis.
  • a profile is understood in detail to mean an endless polyline, which comprises a suction-side contour and a pressure-side contour of an airfoil.
  • the contours meet on the one hand in a leading edge point and on the other hand in a trailing edge point, which are also part of the profile and lie on the corresponding edge of the airfoil.
  • Such a profile exists for each existing along the span shovel ⁇ leaf height.
  • the profile represents the contour of a cross section through the airfoil for a specific blade height, wherein the cross section ⁇ either perpendicular to the radial direction of the Axialver or slightly inclined - according to a Ringkanalkontrakom - may be oriented.
  • printed page contours 40 of three profiles 28, 30 are shown in solid line.
  • a plurality of suction side contours 42 of profiles 28, 30 of different blade blade heights are also shown in solid lines.
  • FIG 9 and FIG 10 curved blade 12 has a comparison with the prior art according to the invention modified blade tip region 43, the specific configuration and operation will be described in more detail below.
  • FIG 1 two fundamentally different profiles 28, 30 are shown.
  • the first, shown in dotted line type profile 28 shows a cross section through the Ver Whyrlauf- blade or vane 10 according to FIG 10 in a blade height of half the span of the blade 12.
  • the profile 28 may be a conventional, known from the prior art Pro ⁇ fil.
  • the profile shown in solid line 30 shows a cross section through the inventive compressor rotor 10 according to FIG 10 in the area 43 of the blade tip 22.
  • Each profile 28, 30 of FIG 1 has a skeleton line associated therewith, for reasons of clarity in 1 shows only one skeleton line 32 of the blade tip-side profile 30 is shown in dashed line style.
  • the skeleton line 32 begins at a leading edge point 24, terminates at an associated trailing edge point 26, and is always centered between the pressure side contour 40 and suction side contour 42. It is also known as the profile center line.
  • profiles are also defined in the prior art with the aid of a straight chord.
  • the chord is a straight line which extends from the leading edge ⁇ point to the trailing edge point.
  • FIG. 1 only one profile chord 34 for the blade tip-side profile 30 is shown. Since the profile chord 34 is subsequently used for the geometrical definition of significant points of the profile 30, its length is normalized to one, wherein in the leading edge point 24, the length of the chord 0% and in the trailing edge point 26, the length of the chord 100%. This also means a relative chord length.
  • the normalized chord 34 is indicated by x / c.
  • the profile 30 shown in FIG 1 is representative of the radially outermost of the blade tip side profiles 30.
  • the conventional profile 28 shown in FIG 1 is on the one hand representative of the known from the prior art profiles and on the other hand for the other profiles of the compressor blade 10th Sub the remaining sections 28 are the ones to understand which are not arranged schaufelspitzsei- tig and thus for example in the soapy mounting area of the blade 12 or the center between airfoil tip 22, and may be arranged to the fastening-side show ⁇ felblattende.
  • the transition from the conventional profile 28 to the blade tip-side profile 30 takes place, as shown in FIG 10, steplessly.
  • a characteristic feature of a compressor runner 10 according to the invention is that the skeleton lines 32 of the blade tip-side profiles 30 have at least two turning points 36, 38.
  • the skeleton line 32 upstream of the front ⁇ th inflection point 36 has a first curvature section A with a first curvature and downstream of the first turning point 36 to the second inflection point 38 has a second curvature B with a second curvature.
  • the signs of the first curvature and the second curvature are different.
  • a third curvature section C follows, whose curvature in turn has a different sign than that of the second curvature.
  • the predominantly convex curved suction side contour 42 has a concave shape in a section D between 35% and 50% of the relative chord length.
  • the mainly concavely curved ge ⁇ pressure side contour 40 has a section E, which is convex. Contrary to the previous known from the prior art profile shapes for compressor blades of axial compressors this concave Sauguzeenkon- turabrough D and convex pressure side contour section E leads to a locally kinking profiling, which is referred to here as a profile kink.
  • first of the two turning ⁇ points 36 when perpendicular to the profile chord on this predetermines a first projection point AP, which is removed from the leading edge point 24 between 10% and 30% of the length of the profile tendon 34 and in the the second of the two
  • the skeleton line 32 of blade tip side profiles 30 in a rear portion G has a greater curvature than the rear portions of skeleton lines of the remaining profiles 28 of the airfoil 12.
  • the rear portion G of the skeleton line 32 extends from the section start point GA to the trailing edge point 26 of the skeleton line 32, which section start point GA when projecting onto the chord 34 on this one projection point GP, which is removed from the leading edge point 24 a maximum of 60% of the length of the chord 34.
  • the shovel-pointed side profile 30 comprises a skeleton line 32 with a prede ⁇ ren H section.
  • the front portion H of ⁇ skeleton line 32 extends from the leading edge point 24 to a projection point HP of the skeleton line 32, which is located at 10% of the length of the chord 34th
  • the projection point HP results from the projection of an end point HE of the front portion H perpendicular to the chord 34.
  • the skew ⁇ lettline 32 is almost not arched, ie approximately straight.
  • the thickness distribution which is known to be applied perpendicular to the skeleton line 32 on both sides to the same Tei ⁇ len, here chosen so that there is a wedge-shaped leading edge region for the blade tip side profiles 30 in principle.
  • a symmetrical course of the suction side contour 42 and pressure side contour 40 is symmetrically desirable.
  • the VELOCITY ⁇ speed distribution is thereby recorded on that blade height of compressor rotor blades, which is removed 0.5% of the gap ⁇ size of a radial gap between the blade tip 22 and the surrounding annular wall of the axial compressor of the airfoil tip 22nd
  • dashed line type the speed distributions 48, 50 of a conventional profile 28 for the suction side wall 16 and pressure side wall 14 are shown in FIG. 2, FIG. 3 and FIG.
  • the velocity distributions 44, 46 for the suction side wall 16 and pressure side wall 14 of the blade tip-side profile 30 are shown in full line.
  • the respective lower line represents the velocity distribution for the corresponding pressure-side
  • each top line represents the VELOCITY ⁇ speed distribution for the corresponding suction side.
  • Characteristic ⁇ is that the profile shape of the airfoil 12 blade tip side is selected so that the speed increase is achieved to a maximum speed in a maximum location at about 20% of the length of the chord 34 in the shortest possible chord section. Furthermore, a comparatively large decrease in the speed of the suction-side gas flow in a profile chord section that is as short as possible is desired in the subsequent 15% of the chord 34 following the maximum location. Insbeson ⁇ particular this speed course along the suction sides ⁇ wall 16 causes a responsibility for the gap losses ⁇ wortaji gap vortex is evidence ER- with relatively more energy, but continues to be fed only comparatively little energy by the large speed decrease after reaching the maximum velocity that which weakens him all the more. Overall, this leads to redu ⁇ ed radial gap losses.
  • FIG. 3 and FIG. 6 give a further overview of the effects caused by the profile bend.
  • the Mach number distributions of the conventional one are again Profile 28 and the blade tip side profile 30 shown on the relative chord length.
  • FIG 4 describes the schau- felspitz solutione profile 30 in ungestaffelten m'-theta Koordi ⁇ natensystem.
  • the lower illustration, FIG. 5, shows a curvature 52 of the suction side contour 42 and a curvature 54 of FIG. 5
  • Mass flow density for a conventional profile 28 is denoted by 58, that for the blade tip-side profile 30 by 60.
  • For the blade tip-side profile 30 is a clear relationship between the increase in the pressure potential and the increase in the mass flow density in the radial gap recognize.
  • the mass flow density in the radial gap also reached its globa ⁇ les maximum shortly after the profile described crease.
  • the global maximum of the mass flow density for the schaufelspitzsei ⁇ term profile 30 is higher than the conventional one.
  • the Ab ⁇ fall of the mass flow density in the radial gap to its maximum is also greater than in the conventional profiling 28th
  • the gap vortex line for the conventional profile 28 is 62 ⁇ be distinguished, the gap vortex line for the blade tip profile with 64. Relative to the leading edge 18 of the gap ⁇ vortex arises at the blade tip side profile 30 clearly later - based on the relative chord length of the respective profile - and then kinks from the suction side wall 16 at a greater angle than in the conventional profiling 28.
  • the early kinking of the slit vortex coincides with the sharp increase in mass flow density to its maximum and that following decrease of the same together.
  • the larger angle is due to the larger gradient in both the increase and decrease in mass flow density.
  • the relative to the conventional profile 28 relatively late emergence of the crevice vertebra can be explained by the low load on the improved profile 30 at the front edge 18.
  • the invention thus relates to a compressor run 10 for axially flowed compressor preferably stationary gas turbine.
  • the invention provides that in order to reduce radial gap losses, the skeleton line 32 of the blade tip-side profiles 30 of the blade 12 of the compressor blade 10 have at least two inflection points 36, 38. Due to the presence of two turning points 36, 38 are obtained for the suction surface 42 in the portion from 35% to 50% of a Saugnchkonturab mustard D which is concaveaded ⁇ det and a Druckierikon- for the pressure side contour 40 turabrough E, which is convex. With this geometry, it is possible to generate low-loss gap swirl to increase the overall efficiency of a vehicle equipped with these Ver ⁇ tight running blades 10 axial compressor.

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

Abstract

L'invention concerne une aube mobile de compresseur (10) pour des compresseurs traversés axialement de turbines à gaz de préférence fixes. Il est prévu que, pour réduire des pertes par fente radiale, la ligne d'ossature (32) des profilés (30) côté pointe d'aube de la pale (12) de l'aube mobile de compresseur (10) présente au moins deux points d'inversion (36, 38). Par la présence de deux points d'inversion (36, 38), on obtient pour le contour du côté aspiration (42) dans la partie de 35 % à 50 % une partie de contour du côté aspiration (D) qui est conçue concave et pour le contour du côté refoulement (40) une partie du contour du côté refoulement (E) qui est conçue convexe. A l'aide de cette géométrie, il est possible de générer des tourbillons de fente présentant moins de pertes, afin d'améliorer le rendement global d'un compresseur axial équipé avec ces aubes mobiles de compresseur (10).
EP10743094.4A 2009-09-04 2010-08-10 Aube mobile de compresseur pour un compresseur axial Active EP2473743B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP10743094.4A EP2473743B1 (fr) 2009-09-04 2010-08-10 Aube mobile de compresseur pour un compresseur axial

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP09011392A EP2299124A1 (fr) 2009-09-04 2009-09-04 Aube de rotor pour un compresseur axial
PCT/EP2010/061580 WO2011026714A1 (fr) 2009-09-04 2010-08-10 Aube mobile de compresseur pour un compresseur axial
EP10743094.4A EP2473743B1 (fr) 2009-09-04 2010-08-10 Aube mobile de compresseur pour un compresseur axial

Publications (2)

Publication Number Publication Date
EP2473743A1 true EP2473743A1 (fr) 2012-07-11
EP2473743B1 EP2473743B1 (fr) 2015-07-29

Family

ID=41467191

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09011392A Withdrawn EP2299124A1 (fr) 2009-09-04 2009-09-04 Aube de rotor pour un compresseur axial
EP10743094.4A Active EP2473743B1 (fr) 2009-09-04 2010-08-10 Aube mobile de compresseur pour un compresseur axial

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP09011392A Withdrawn EP2299124A1 (fr) 2009-09-04 2009-09-04 Aube de rotor pour un compresseur axial

Country Status (8)

Country Link
US (1) US8911215B2 (fr)
EP (2) EP2299124A1 (fr)
JP (1) JP5678066B2 (fr)
CN (1) CN102483072B (fr)
ES (1) ES2548254T3 (fr)
HU (1) HUE025789T2 (fr)
RU (1) RU2534190C2 (fr)
WO (1) WO2011026714A1 (fr)

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FR2991373B1 (fr) 2012-05-31 2014-06-20 Snecma Aube de soufflante pour turboreacteur d'avion a profil cambre en sections de pied
DE102012222953A1 (de) * 2012-12-12 2014-06-26 Honda Motor Co., Ltd. Flügelprofil für einen Axialströmungskompressor
CN103867489B (zh) * 2012-12-14 2017-06-16 中航商用航空发动机有限责任公司 压气机叶片、压气机以及航空发动机
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CN103470534A (zh) * 2013-08-23 2013-12-25 哈尔滨汽轮机厂有限责任公司 一种燃气轮机用压气机的高压进口导叶片
US9790796B2 (en) * 2013-09-19 2017-10-17 General Electric Company Systems and methods for modifying a pressure side on an airfoil about a trailing edge
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WO2011026714A1 (fr) 2011-03-10
EP2299124A1 (fr) 2011-03-23
US20120230834A1 (en) 2012-09-13
JP5678066B2 (ja) 2015-02-25
CN102483072A (zh) 2012-05-30
RU2534190C2 (ru) 2014-11-27
ES2548254T3 (es) 2015-10-15
HUE025789T2 (en) 2016-05-30
RU2012112930A (ru) 2013-10-10
EP2473743B1 (fr) 2015-07-29
JP2013503999A (ja) 2013-02-04
US8911215B2 (en) 2014-12-16
CN102483072B (zh) 2015-04-08

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