EP3798453A1 - Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication - Google Patents

Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication Download PDF

Info

Publication number
EP3798453A1
EP3798453A1 EP19199850.9A EP19199850A EP3798453A1 EP 3798453 A1 EP3798453 A1 EP 3798453A1 EP 19199850 A EP19199850 A EP 19199850A EP 3798453 A1 EP3798453 A1 EP 3798453A1
Authority
EP
European Patent Office
Prior art keywords
flow
flg
flow guide
cross
radial
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Withdrawn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
EP19199850.9A
Other languages
German (de)
English (en)
Inventor
Martin Reimann
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.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP19199850.9A priority Critical patent/EP3798453A1/fr
Publication of EP3798453A1 publication Critical patent/EP3798453A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage 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
    • F04D29/02—Selection of particular materials
    • F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/18—Rotors
    • F04D29/22—Rotors specially for centrifugal pumps
    • F04D29/2238—Special flow patterns
    • F04D29/2255—Special flow patterns flow-channels with a special cross-section contour, e.g. ejecting, throttling or diffusing effect
    • 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
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • 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

Definitions

  • the invention relates to a flow guide of a radial turbo-machine, the flow guide having several flow channels side by side through which a flow fluid to be guided flows in parallel in an operation, the flow channels each having a specific channel cross-section along a spatial flow line for each line point, which is delimited by a channel cross-sectional contour becomes.
  • Information such as radial, axial, tangential or circumferential direction always relate to a central axis around which the flow guide extends essentially with a symmetry.
  • this central axis is the axis of rotation of a rotor of a turbo machine or radial turbo machine.
  • the flow fluid emerges essentially radially from the upstream impeller and, after a generally relatively radial flow path, turns around 180 ° from a radially outward one Direction of flow in a radially inwardly directed flow direction diverted. Following this 180 ° bend, the flow fluid flows radially inward towards the axis of rotation of the turbomachine and is then deflected in the axial direction in order to get into the essentially axial inlet of the following impeller.
  • Both the axial installation space and the radial installation space are limited on the one hand by rotor dynamic requirements - in particular the endeavor that the length of the rotor between the radial bearings should not be unfavorably long - and on the other hand by the desire to reduce the costs for the housing of the radial turbo machine as a result too large a radial installation space requirement should not increase unnecessarily.
  • Rotating flow guides for example impellers of radial turbomachines, describe on the rotor of a radial turbomachine in cross section essentially an annular surface which is likewise segmented in sections in the circumferential direction by the rotor blades that extend in the impeller. This results in an almost rectangular cross-section of the flow channels in the impeller defined by the adjacent blades, a cover plate and the hub contour of the impeller.
  • This possible modularity can be found in the Figure 1 read in the axial longitudinal section through a radial turbomachine, the Figure 1 neither the modularity pretends to have a cross-sectional shape for the flow channels.
  • the invention has set itself the task of improving the aerodynamic efficiency of a flow guide without requiring additional radial or axial installation space. Furthermore, the invention has set itself the goal of specifying a manufacturing method for such a flow guide. In addition, the invention specifies the construction of a radial turbomachine with such a flow guide, in particular as a return stage.
  • the findings according to the invention can be used among the stationary components not only for return stages of radial turbomachines, but also for, for example, inflows to impellers or outflows from impellers without a further impeller being arranged upstream or downstream.
  • Another application of the flow guide according to the invention results in particular for diffusers, in particular for radial turbomachines.
  • the invention can also be used for rotating flow guides.
  • a flow guide of the type defined at the outset is proposed according to the invention with the additional features of the characterizing part of claim 1.
  • the respective back-referenced sub-claims contain advantageous developments of the invention.
  • a rotor or an impeller, a stator or a return stage each with such a flow guide and a radial turbo machine with at least one such return stage or flow guide are proposed.
  • a method for producing such a flow guide is proposed.
  • a flow fluid to be conveyed is generally the flow fluid that is conveyed by the corresponding turbo machine or radial turbo machine or that essentially serves as a drive or output for the operation of the turbo machine.
  • the flow fluid to be carried is the medium that mainly either emits or absorbs significant technical work.
  • the term “in an operation” is understood by the invention to mean the state of operation of the corresponding machine or turbo-machine, during which, for example, the rotor of the machine rotates and technical work is transferred to or away from the flow fluid.
  • the invention does not necessarily understand a parallel flow as the geometrically parallel flow through the various flow channels through a flow fluid, but preferably the division of the flow fluid into several partial flows that flow through the respective flow channels of the flow guide according to the invention next to one another, whereby they usually have a common one before the division Main stream formed and are preferably combined again downstream to form a common main stream according to the flow guidance according to the invention.
  • the invention understands a spatial flow line to be essentially a three-dimensional line-like course which is characteristic of the spatial shape of a flow channel of the flow guide.
  • the flow line essentially describes the path of the averaged movement of the flow fluid through a flow channel of the flow guide.
  • the spatial flow line can also be referred to as a line of the main flow direction of the flow fluid.
  • the respective flow channel is defined by channel cross-sections at each individual point of the flow line.
  • the channel cross-sections are limited to the outside by a channel cross-sectional contour, which at the same time represents the objective boundary of the flow channel.
  • the flow channels are essentially hose-like cavities in the surrounding material that constitutes the flow guide.
  • the invention understands a pie-like segmentation to mean an imaginary division of a channel cross-section into any (preferably but not necessarily the same) pieces with regard to the circumferential angle, the radial rays defining the individual pieces preferably running from the point of intersection of the flow line through the respective channel cross-section.
  • This segmentation selected by the definition of the independent claim is part of a criterion for describing the difference in the flow channel cross-sections between a conventional, essentially almost rectangular shape and flow channel cross-sections according to the invention in a less rectangular shape.
  • the invention understands the inner angle of the two tangents on the channel cross-sectional contour to be the angle which, through its opening, faces the opening of the circumferential angle of the channel cross-sectional segment of the imaginary segmentation.
  • the respective flow channel is formed at least in sections in such a way that an imaginary pie-like circumferential segmentation starting from a center point of the channel cross-section form circumferential segments with a circumferential angle ⁇ between two adjacent segmenting radial rays, with tangents on the channel cross-sectional contour at the points of intersection of the Radial rays form an interior angle ⁇ with the channel cross-sectional contour, the following applies to every conceivable circumferential segmentation for each circumferential segment: 1/10 *
  • the angular width of the inner angle of the two tangents on the channel cross-sectional contour faces the angular width of the circumferential angle.
  • the two radial rays and the tangents accordingly form a quadrilateral, with both both the circumferential angle ⁇ and the interior angle ⁇ are interior angles of the quadrangle.
  • the flow guide according to the invention based on the criterion 1/10
  • ⁇ relates to an idealized form of flow guidance and does not take into account any actual surface properties, for example.
  • the criterion is preferably to be understood as referring to the draft or a virtual model of the actual flow guidance.
  • the flow guide is designed in such a way that the channel cross section of a flow channel has a cross-sectional shape that varies at least in sections along the flow line.
  • This design enables an aerodynamically optimal adaptation to the operating conditions in such a way that the best possible fluidic efficiency is achieved.
  • the variation of the cross-sectional shape can relate both to the size of the cross-section and to the type of shape.
  • the cross-sectional delimitation contour it can be designed as a circular radius, elliptical, angular or in the manner of a free-form line.
  • the cross-sectional contour is not angular.
  • a flow guide which is designed as a stator. These include, for example, return stages of radial turbomachines, inflow areas to impellers or outflow areas or diffusers downstream of impellers.
  • Another possibility for implementing the invention results from a flow guide which is designed as a rotor, in particular as an impeller of a radial turbo-machine.
  • the flow guide according to the invention is particularly expediently part of a radial turbo-machine. It makes sense here if the flow guide is either part of the Radial turbomachine is upstream and / or downstream of an impeller.
  • the flow guide according to the invention can be manufactured particularly expediently by means of so-called additive manufacturing processes.
  • a virtual model of the flow guidance is generated.
  • the flow guidance is produced using the additive manufacturing process.
  • the flow guide according to the invention can also be produced by means of a casting process.
  • the model for the casting process can particularly preferably be generated by means of an additive manufacturing process. For this purpose, the steps of the manufacturing method already explained above for manufacturing the flow guide would be applied mutatis mutandis to the manufacture of the model for the casting of the flow guide.
  • Figure 1 shows an axial longitudinal section through a radial turbomachine RTM with a flow guide FLG according to the invention.
  • the axis X of the longitudinal section is at the same time the axis of rotation of impellers IMP, which are attached to a shaft SHS of the radial turbo machine RTM.
  • the impellers IMP comprise a hub HUB, blades BLD and a cover plate SHR.
  • the radial turbo-machine RTM comprises a rotor RTR with the shaft SHS and the impellers IMP and a stator STT comprising the other components.
  • a flow fluid FLD first flows through an inflow INL of the stator STT, then an impeller IMP or flow channels FLC of the impeller IMP, downstream of the impeller a feedback stage RST of the stator STT and further downstream another impeller IMP and then an outflow EXT comprising a diffuser DFS and a subsequent spiral VLT, which serves as a collector for an exit from the stator STT in a manner not shown.
  • the stator STT is sealed at various points in the areas of a movement gap by means of a shaft seal SSL.
  • the return stage RST comprises a radially outwardly directed diffuser section RDF, a 180 deflector UTN and a radially inwardly directed return section BCH as well as a deflector TRN in the axial direction to the entry into the downstream impeller IMP.
  • the impellers IMP and the return stage RST are shown in a particularly simplified manner.
  • the IMP wheels are shown here as a classic, idealized modular structure.
  • a hub HUB which is also often referred to as a wheel disk, blades BLD and a cover disk SHR, which is held on the hub HUB by the blades BLD.
  • this modularity is at least not given with regard to a difference in the components of the impeller IMP.
  • the impeller IMP is particularly preferred - as in Figure 4 shown - according to the invention in one piece, for example as a cast component or as a component that has been produced by means of an additive manufacturing process.
  • the flow channel FLC defined by the components hub HUB, blade BLD and cover disk SHR extends through the impeller IMP more like a hose-like cavity with at least some sections of varying cross-sectional shape, varying cross-sectional circumference and varying cross-sectional area.
  • the feedback stage RST in the stator STT is designed in the same way.
  • the flow channel FLC of the return stage RST extends along the individual flow sections RDF, UTN, BCH, TRN with at least sectionally varying cross-sectional shape, cross-sectional circumference, cross-sectional area content like a cave through the stator STT like a hose.
  • Figure 2 shows an essentially axial perspective of a radial turbo compressor with the flow channel of an impeller IMP and several flow channels FLC of a return stage RST.
  • the Figure 3 shows the feedback stage RST from the Figure 2 from the essentially opposite axial perspective with a downstream impeller IMP.
  • the focus of the representations in the Figures 2 , 3 is the shape of the flow channels FLC of the flow guide FLG of the return stage RST.
  • the individual sections RDF, UTN, BCH, TRN each have an individual shape with regard to the cross-sectional shape, the cross-sectional circumference and the cross-sectional area.
  • the cross-sectional shape is more rectangular than in the middle part of the return stage RST, the cross-sectional shape becoming more rectangular again at the exit of the return stage RST.
  • the more rectangular contour of the cross-sectional shape at the entrance and exit of the flow the return stage RST avoids a blockage or dead water areas when entering or leaving the return stage RST.
  • the Figure 4 shows the same aspects implemented on an IMP impeller.
  • the respective flow channel FLC is formed at least in sections in such a way that an imaginary pie-like segmentation starting from a communication point of the channel cross-section CCS forms pieces with a circumferential angle ⁇ between two adjacent segmenting radial rays RR1, RR2, with tangents T1, T2 on the Channel cross-sectional contour CCC form an interior angle ⁇ in the intersection points SC1, SC2 of the radial rays RR1, RR2 with the channel cross-sectional contour CCC, where: 1/10 *
  • Figure 5 shows a somewhat more rectangular cross-sectional shape of the channel cross-section CCS with a cross-sectional contour CCC.
  • the pie-like segments can be arranged as small as desired and displaced as desired in the circumferential direction.
  • the decisive factor for the channel cross-sectional contour CCC according to the invention is a non-angular design of the channel cross-section CCS, at least in sections. After an angular design of the channel cross-section CCS, an arbitrarily small angle ⁇ would be an angle
  • a convex design of the channel cross-sectional contour CCC is preferred. Another possibility is to design the channel cross-sectional contour CCC with convex circumferential pieces KXC and concave circumferential pieces KVC, as in FIG Figure 6 represents. In this way, the flow guidance can also be adapted to special aerodynamic requirements.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19199850.9A 2019-09-26 2019-09-26 Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication Withdrawn EP3798453A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP19199850.9A EP3798453A1 (fr) 2019-09-26 2019-09-26 Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP19199850.9A EP3798453A1 (fr) 2019-09-26 2019-09-26 Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication

Publications (1)

Publication Number Publication Date
EP3798453A1 true EP3798453A1 (fr) 2021-03-31

Family

ID=68072134

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19199850.9A Withdrawn EP3798453A1 (fr) 2019-09-26 2019-09-26 Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication

Country Status (1)

Country Link
EP (1) EP3798453A1 (fr)

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6220816B1 (en) * 1997-12-19 2001-04-24 Societe Nationale D'etude Et De Construction Moteurs D'aviation-S.N.E.C.M.A. Device for transferring fluid between two successive stages of a multistage centrifugal turbomachine
CN101391302A (zh) * 2008-10-10 2009-03-25 华中科技大学 一种热等静压金属包套的整体快速制造方法
AU2012221969A1 (en) * 2011-02-22 2014-03-20 Jea Woong Lee Impeller having cylindrical vanes
WO2016079222A1 (fr) 2014-11-21 2016-05-26 Siemens Aktiengesellschaft Étage de retour
WO2016128388A1 (fr) * 2015-02-11 2016-08-18 Ksb Aktiengesellschaft Composant guidant l'écoulement
US20170030372A1 (en) * 2014-04-10 2017-02-02 Airbus Safran Launchers Sas Fluid-transfer device and method for manufacturing same
WO2017194272A1 (fr) 2016-05-13 2017-11-16 Siemens Aktiengesellschaft Étage de retour pour un turbocompresseur radial et turbocompresseur radial
WO2018166716A1 (fr) 2017-03-15 2018-09-20 Siemens Aktiengesellschaft Étage de retour et turbomachine à énergie fluidique radiale
US20190277140A1 (en) * 2018-03-09 2019-09-12 Mitsubishi Heavy Industries, Ltd. Impeller, centrifugal compressor, gas turbine, and method of manufacturing impeller

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6220816B1 (en) * 1997-12-19 2001-04-24 Societe Nationale D'etude Et De Construction Moteurs D'aviation-S.N.E.C.M.A. Device for transferring fluid between two successive stages of a multistage centrifugal turbomachine
CN101391302A (zh) * 2008-10-10 2009-03-25 华中科技大学 一种热等静压金属包套的整体快速制造方法
AU2012221969A1 (en) * 2011-02-22 2014-03-20 Jea Woong Lee Impeller having cylindrical vanes
US20170030372A1 (en) * 2014-04-10 2017-02-02 Airbus Safran Launchers Sas Fluid-transfer device and method for manufacturing same
WO2016079222A1 (fr) 2014-11-21 2016-05-26 Siemens Aktiengesellschaft Étage de retour
WO2016128388A1 (fr) * 2015-02-11 2016-08-18 Ksb Aktiengesellschaft Composant guidant l'écoulement
WO2017194272A1 (fr) 2016-05-13 2017-11-16 Siemens Aktiengesellschaft Étage de retour pour un turbocompresseur radial et turbocompresseur radial
WO2018166716A1 (fr) 2017-03-15 2018-09-20 Siemens Aktiengesellschaft Étage de retour et turbomachine à énergie fluidique radiale
US20190277140A1 (en) * 2018-03-09 2019-09-12 Mitsubishi Heavy Industries, Ltd. Impeller, centrifugal compressor, gas turbine, and method of manufacturing impeller

Similar Documents

Publication Publication Date Title
EP2993357B1 (fr) Étage de compresseur radial
EP2025945B1 (fr) Machine de traitement des écoulements dotée d'un creux de paroi de canal de ceinture
EP2824282A1 (fr) Turbine à gaz avec système de refroidissement de turbine à haute pression
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
DE102015120127A1 (de) Axialverdichterendwandeinrichtung zur steuerung der leckage in dieser
EP1515000A1 (fr) Aubage d'une turbomachine avec un carenage contouré
EP2787182B1 (fr) Aube directrice pour une turbomachine, grille d'aube directrice et procédé de fabrication d'une aube directrice ou d'une grille d'aube directrice
DE102008013542A1 (de) Strömungsarbeitsmaschine mit mehrstromiger Rotoranordnung
EP3404210A1 (fr) Segment de grille d'aubes d'une turbomachine avec paroi de plateforme non-axisymétrique , grille d'aubes, canal d'aube, plateforme, turbomachine associés
EP2818724B1 (fr) Turbomachine et procédé
EP2993356A1 (fr) Étage de compresseur radial
DE102014203605A1 (de) Schaufelreihengruppe
DE102010037692A1 (de) Geformte Wabendichtung für eine Turbomaschine
EP2808556A1 (fr) Ensemble structurel pour une turbomachine
EP2994615B1 (fr) Rotor pour une turbomachine thermique
EP2913481A1 (fr) Aubes en tandem d'une turbomachine
DE112015005131T5 (de) Kühlstruktur für Turbine, und Gasturbine
EP3388626A1 (fr) Contournage d'une plate-forme de grille d'aube
EP2913479A1 (fr) Aubes en tandem d'une turbomachine
EP3159487B1 (fr) Stator d'une turbine à gaz ayant un guidage d'air de refroidissement amélioré
DE102014222877A1 (de) Laufrad einer Radialturbofluidenergiemaschine, Stufe
DE102019211669A1 (de) Dichtungsvorrichtung und turbomaschine
EP3798453A1 (fr) Guidage de flux d'une turbomachine radiale, étage de retour, turbomachine radiale, procédé de fabrication
EP2913480B1 (fr) Aubes en tandem d'une turbomachine
EP3581760B1 (fr) Pale d'aube pour une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20211001