EP3477049A1 - Ring mit erhebungen für verdichter einer strömungsmaschine - Google Patents

Ring mit erhebungen für verdichter einer strömungsmaschine Download PDF

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Publication number
EP3477049A1
EP3477049A1 EP18194178.2A EP18194178A EP3477049A1 EP 3477049 A1 EP3477049 A1 EP 3477049A1 EP 18194178 A EP18194178 A EP 18194178A EP 3477049 A1 EP3477049 A1 EP 3477049A1
Authority
EP
European Patent Office
Prior art keywords
compressor
boss
blade
protuberance
connecting surface
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
EP18194178.2A
Other languages
English (en)
French (fr)
Other versions
EP3477049B1 (de
Inventor
Stéphane Hiernaux
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 Aero Boosters SA
Original Assignee
Safran Aero Boosters SA
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 Safran Aero Boosters SA filed Critical Safran Aero Boosters SA
Publication of EP3477049A1 publication Critical patent/EP3477049A1/de
Application granted granted Critical
Publication of EP3477049B1 publication Critical patent/EP3477049B1/de
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
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • 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
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/121—Fluid guiding means, e.g. vanes related to the leading edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/122—Fluid guiding means, e.g. vanes related to the trailing edge of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/123—Fluid guiding means, e.g. vanes related to the pressure side of a stator vane
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F05D2240/124—Fluid guiding means, e.g. vanes related to the suction side of a stator vane
    • 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
    • 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

Definitions

  • the invention relates to a compressor with a profiled inter-blade surface.
  • the invention also relates to an axial turbomachine, in particular an aircraft turbojet engine or an aircraft turboprop engine.
  • the document US 2007/0059177 A1 discloses a turbojet compressor.
  • the compressor has an annular row of vanes.
  • a platform is associated with each blade and has a three-dimensional relief extending between two successive blades.
  • Each relief has two bumps separated by a sinusoidal channel sinking radially into the platform. This geometry improves the aerodynamic efficiency of an axial flow compressor blade. However, it shows a high corner detachment in extrados of the blades.
  • the object of the invention is to solve at least one of the problems posed by the prior art. More specifically, the invention aims to optimize the compression ratio and the detachments in the corner at the extrados. The invention also aims to provide a simple solution, resistant, lightweight, economical, reliable, easy to produce, and convenient maintenance.
  • the invention can be understood as a bump with two main peaks, and / or a convexity with two radial extremums; between two consecutive blades of a compressor.
  • the invention relates to an axial turbomachine compressor according to claim 1.
  • the subject of the invention is also a turbomachine, in particular an aircraft turbojet, comprising a compressor, which is remarkable in that the compressor is in accordance with the invention, preferentially the row of blades comprises at least: fifty or eighty. blades.
  • each embodiment of the invention is combinable with each object of the invention.
  • the terms “internal” and “external” refer to a positioning relative to the axis of rotation of an axial turbomachine.
  • the axial direction corresponds to the direction along the axis of rotation of the turbomachine.
  • the radial direction is perpendicular to the axis of rotation. Upstream and downstream are in reference to the main flow direction of the flow in the turbomachine.
  • the figure 1 represents in simplified manner an axial turbomachine. It is in this case a double-flow turbojet engine.
  • the turbojet engine 2 comprises a low-pressure compressor 4, a high-pressure compressor 6, a combustion chamber 8 and one or more turbine levels 10.
  • the mechanical power of the turbine 10 transmitted via the central shaft up to the rotor 12 sets in motion the two compressors 4 and 6.
  • the latter comprise several rows of rotor blades associated with rows of stator vanes.
  • the rotation of the rotor about its axis of rotation 14 thus makes it possible to generate an air flow and to compress this last to the entrance of the combustion chamber 8.
  • a blower 16 or fan 16 is coupled to the rotor 12 and generates a stream of air which splits into a primary stream 18 and a secondary stream 20 passing through an annular duct (partially shown).
  • the secondary flow can be accelerated so as to generate a thrust reaction necessary for the flight of an aircraft.
  • the primary 18 and secondary 20 streams are annular.
  • the figure 2 is a sectional view of a compressor of an axial turbomachine such as that of the figure 1 .
  • the compressor may be a low-pressure compressor 4. There may be observed a portion of the fan 16 and the separation nozzle 22 of the primary flow 18 and the secondary flow 20.
  • the rotor 12 comprises several rows of rotor blades 24, in this case three. It may be a bladed monobloc drum, or include dovetail blades.
  • the rotor vanes 24 may extend radially from an individual platform, or from an inner ring 25 of the rotor 12.
  • the low-pressure compressor 4 comprises several rectifiers, in this case four, each containing a row of stator vanes 26.
  • the rectifiers are associated with the fan 16 or with a row of rotor vanes to straighten the air flow, so as to convert the speed of the flow into pressure, in particular into static pressure.
  • the stator vanes 26 extend essentially radially from an outer casing 28. They can be fixed and immobilized by means of fixation pins 30. They pass radially through the primary flow 18.
  • the stator vanes can be fixedly oriented by 28.
  • the blades of the same row are identical and aligned. Each row may comprise one hundred twenty blades (26; 24).
  • Internal ferrules 32 may be suspended at the inner ends of the stator vanes 26.
  • the inner ferrules 32 may cooperate sealingly with the rotor 12 to improve the compression ratio of the compressor 4.
  • the row may be one of the rows presented in connection with the preceding figures.
  • the vanes and their support, optionally the inner ferrule 32, are represented in plan.
  • the axis of rotation 14 is traced to a figurative position, and provides a spatial marker.
  • Each blade 26 comprises a leading edge 34, a trailing edge 36, and a lower surface 38 and an extrados surface 40. These surfaces (38; 40) can be curved and curved respectively. Each of these surfaces extends from the leading edge 34 to the corresponding trailing edge 36.
  • the blade 26 may comprise a stack of aerodynamic profiles 41 arched, whose sides generate the intrados surface 38 and the extrados surface 40. At the trailing edges 36, the contours of the profiles 41, in intrados and / or extrados, are parallel and / or tangent to the axis of rotation 14 of the compressor.
  • the consecutive blades 26 of the annular row define between it a passage 42, also called inter-blade passage 42.
  • This passage 42 is partitioned circumferentially by the blades 26, and delimited by the intrados and extrados surfaces.
  • the passage 42 may have a connecting surface 44 between the two consecutive blades 26, and may connect the intrados surface 38 which faces the extrados surface 40 through the passage 42.
  • the connecting surface 44 may be defined axially by an upstream axis 46 and a downstream axis 48 which connect the leading edges 34 and the trailing edges 36 respectively. These axes (46; 48) can be parallel, and can generally define a parallelogram or a trapezoid.
  • the connecting surface 44 may be generally flat.
  • the connecting surface 44 may be a tubular surface part or a cone surface part, in particular because of the radius of the ferrule and the optional diameter variation of the ferrule 32 along the axis of the ferrule. rotation 14. It may comprise four corners 50 corresponding to the intersections between the edges (34; 36) and the support, in this case the ferrule 32, for example internal.
  • the connecting surface 44 may comprise an upstream zone 47 extending downstream from the upstream axis 46, and a downstream zone 49 extending upstream from the downstream axis 48.
  • the connecting surface 44 has an axial asymmetry with respect to the axis of rotation 14. It has a protrusion 52, in particular a main protrusion 52. This protrusion 52 can occupy most of the The axial majority of the protuberance 52 may be contained in the upstream half of the row of blades 26. It forms an addition of radial material on the connecting surface 44. The addition of material can be observed by compared to zones 47 and 49.
  • the protrusion 52 also includes a first boss 54 with a first boss 56, and a second boss 58 with a second boss 60. These bosses 54 and 58 may be the major bosses of the protuberance 52, i.e. they form the main volume reliefs.
  • the bumps (54; 58) may extend over at most the axial majority of the blades 26.
  • the first bump may extend axially on 30% of the rope 62 of the first blade 26, and / or the second bump 58 may extend axially on 20% of the rope 62 of the second blade 26.
  • These bumps (54; 58) may be recessed axially from the leading edges 34, in particular by 10% the axial length of a rope 62.
  • first top 56 may have a main elongation parallel to the rope 62 of the first blade 26.
  • the first bump 54 may extend over 50% of the inter-blade passage 42 and extend from the intrados surface 38. Its top 56 may be at a distance from the intrados surface 38. A channel 64 may be formed against the first bump 54, between the intrados surface 38 of the first blade 26 and the first top 56.
  • the second bump 58 may extend circumferentially over 10% of the passage 42, its top 60 may be attached to the upper surface 40 of the second dawn 26.
  • the first bump 54 and the second bump 58 may be at the same level axially. Their vertices (56; 60) can be aligned axially. The bumps (54; 58) can be separated from one another, and in particular spaced from each other along the circumference. A collar 66, such as a mountain collar, can circumferentially separate them.
  • the curve 67 is the curve of the shortest neck 66 between the vertices 56 and 60. This curve 67 as well as all the points of the neck 66 are in elevation relative to the regular surface in the absence of protuberance, represented by the zones 47 and 49, of constant radius.
  • the bumps (54; 58) and the protuberance 52 are represented by means of level lines 68. These level lines 68 indicate radial level variations with respect to a reference surface, in this case the connecting surface. 44.
  • the figure 4 is a section of the figure 3 along the IV-IV axis. The position as the inclination of the axis of rotation 14 are figurative and can vary in concrete embodiments.
  • the blades may comprise connecting radii 70 at their radial ends.
  • the connecting spokes 70 may surround their respective blades 26.
  • the connecting surface 44 can extend from the connecting spokes 70 so as to connect them in pairs.
  • the radial thickness of the connecting radii 70 is smaller than that of the bumps and possibly of the protuberance 52.
  • This annular surface 33 may have a constant radius RC outside the passages.
  • the annular surface 33 may have axial symmetry.
  • the zones 47 and 49 can extend the annular surface 33 and be axially tangential thereto. They may have constant radius arcs RC depending on the circumference.
  • a first dotted line 72 extends the areas 47 and 49, and connects them.
  • a second dotted line 74 illustrates the general profile of the protuberance 52.
  • the radial spacing between these dashed lines (72; 74) highlights the overmaterial, that is to say the radial development formed by the protrusion 52 on the Likewise, the continuous line 76 which is separated from the second dotted line 74 highlights the radial development that the first bump 54 forms on the protuberance 52, ie the local thickening of the connecting surface 44.
  • continuous line 76 may pass through the first vertex 56. The latter may be flat.
  • the clean radial thickness of the first bump 54 may be twice the thickness of the protuberance 52. These thicknesses may be maximum thicknesses.
  • the bumps (54; 58) have inclinations greater than those of the protuberance 52.
  • the general plane 80 can join at least one or more or each corner of the surface. 44. Upstream and downstream, the protrusion 52 has lower slopes than the adjacent slopes of the bumps.
  • the present teaching can also be applied to an outer shell or to a casing via a symmetry along the axis A-A.
  • the figure 5 is a section of the figure 3 along the VV axis.
  • the section is perpendicular to the axis of rotation 14, and passes through the two bumps (54; 58) as the protuberance 52.
  • the connecting surface 44 has a constant radius RC.
  • This constant radius RC may correspond to that of the first zone 47 and / or that of the second zone 49.
  • the connecting surface 44 shows a variable radius RV.
  • the first top 56 of the first bump 54 is disposed between the neck 66 and the channel 64.
  • the connecting surface 44 is profiled. It has an increase of radial material relative to its base, in particular generated by the zones (47; 49). At a given point of the axis of rotation 14 disposed at the level of the bumps, the radius RV of the connecting surface 44 may vary as it traverses the connecting surface 44 in the circumferential direction 15, in particular by moving a dawn 26 to its neighbor, ie between the intrados surface 38 and the extrados surface 40. Although only two blades are shown, the present teaching can be applied to their entire annular row, or to several, or to each annular row d stator blades of the compressor. Similarly, the bonding surface can be reproduced identically between each blade next to the same row. This can form several annular rows of identical bumps (54; 58) and several identical annular rows of protuberances 52.
  • the teachings of each figure may be independently combined with the teachings of each of the other figures.
  • the invention provides a combination of the teachings of all the figures and / or with a combination of the whole of the technical solution.

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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)
EP18194178.2A 2017-10-26 2018-09-13 Axialer turbomaschinenverdichter mit ring mit erhebungen Active EP3477049B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
BE2017/5764A BE1025668B1 (fr) 2017-10-26 2017-10-26 Virole a bosses pour compresseur de turbomachine

Publications (2)

Publication Number Publication Date
EP3477049A1 true EP3477049A1 (de) 2019-05-01
EP3477049B1 EP3477049B1 (de) 2023-11-22

Family

ID=60320604

Family Applications (1)

Application Number Title Priority Date Filing Date
EP18194178.2A Active EP3477049B1 (de) 2017-10-26 2018-09-13 Axialer turbomaschinenverdichter mit ring mit erhebungen

Country Status (3)

Country Link
US (1) US11377960B2 (de)
EP (1) EP3477049B1 (de)
BE (1) BE1025668B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4089264A1 (de) * 2021-04-19 2022-11-16 MTU Aero Engines AG Gasturbinen-schaufelanordnung

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20190046118A (ko) * 2017-10-25 2019-05-07 두산중공업 주식회사 터빈 블레이드
BE1026579B1 (fr) * 2018-08-31 2020-03-30 Safran Aero Boosters Sa Aube a protuberance pour compresseur de turbomachine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059177A1 (en) 2005-09-13 2007-03-15 Rolls-Royce Plc Axial compressor blading
EP2487329A1 (de) * 2011-02-08 2012-08-15 MTU Aero Engines GmbH Schaufelkanal mit Seitenwandkonturierung und zugehörige Strömungsmaschine
US20130136621A1 (en) * 2011-11-25 2013-05-30 Mtu Aero Engines Gmbh Blading
DE102015224376A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Schaufelkanal, Schaufelgitter und Strömungsmaschine

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US2918254A (en) * 1954-05-10 1959-12-22 Hausammann Werner Turborunner
US8511978B2 (en) * 2006-05-02 2013-08-20 United Technologies Corporation Airfoil array with an endwall depression and components of the array
US7887297B2 (en) * 2006-05-02 2011-02-15 United Technologies Corporation Airfoil array with an endwall protrusion and components of the array
US8366399B2 (en) * 2006-05-02 2013-02-05 United Technologies Corporation Blade or vane with a laterally enlarged base
FR2928173B1 (fr) * 2008-02-28 2015-06-26 Snecma Aube avec plateforme 3d comportant un bulbe interaubes.
EP2696029B1 (de) * 2012-08-09 2015-10-07 MTU Aero Engines AG Schaufelgitter mit Seitenwandkonturierung und Strömungsmaschine
DE102016211315A1 (de) * 2016-06-23 2017-12-28 MTU Aero Engines AG Lauf- oder Leitschaufel mit erhabenen Bereichen
ES2760552T3 (es) * 2017-04-12 2020-05-14 MTU Aero Engines AG Contorneado de una plataforma de rejilla de álabes

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070059177A1 (en) 2005-09-13 2007-03-15 Rolls-Royce Plc Axial compressor blading
EP2487329A1 (de) * 2011-02-08 2012-08-15 MTU Aero Engines GmbH Schaufelkanal mit Seitenwandkonturierung und zugehörige Strömungsmaschine
US20130136621A1 (en) * 2011-11-25 2013-05-30 Mtu Aero Engines Gmbh Blading
DE102015224376A1 (de) * 2015-12-04 2017-06-08 MTU Aero Engines AG Schaufelkanal, Schaufelgitter und Strömungsmaschine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP4089264A1 (de) * 2021-04-19 2022-11-16 MTU Aero Engines AG Gasturbinen-schaufelanordnung
US11585223B2 (en) 2021-04-19 2023-02-21 MTU Aero Engines AG Gas turbine blade arrangement

Also Published As

Publication number Publication date
US11377960B2 (en) 2022-07-05
EP3477049B1 (de) 2023-11-22
BE1025668A1 (fr) 2019-05-21
BE1025668B1 (fr) 2019-05-27
US20190128121A1 (en) 2019-05-02

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