EP2818724A1 - Turbomachine, structure de circulation et procédé - Google Patents

Turbomachine, structure de circulation et procédé Download PDF

Info

Publication number
EP2818724A1
EP2818724A1 EP13174062.3A EP13174062A EP2818724A1 EP 2818724 A1 EP2818724 A1 EP 2818724A1 EP 13174062 A EP13174062 A EP 13174062A EP 2818724 A1 EP2818724 A1 EP 2818724A1
Authority
EP
European Patent Office
Prior art keywords
housing
circulation structure
turbomachine
flow guide
structural
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
EP13174062.3A
Other languages
German (de)
English (en)
Other versions
EP2818724B1 (fr
Inventor
Georg Zotz
Giovanni Dr. Brignole
Harsimar Dr. Sahota
Vitalis Mairhanser
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MTU Aero Engines AG filed Critical MTU Aero Engines AG
Priority to EP13174062.3A priority Critical patent/EP2818724B1/fr
Priority to US14/315,066 priority patent/US10151206B2/en
Publication of EP2818724A1 publication Critical patent/EP2818724A1/fr
Application granted granted Critical
Publication of EP2818724B1 publication Critical patent/EP2818724B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • 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
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/56—Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/563—Fluid-guiding means, e.g. diffusers adjustable specially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps 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
    • F04D29/66—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
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • 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
    • F04D29/66—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
    • F04D29/682—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid extraction
    • 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
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2230/60—Assembly methods
    • 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
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making

Definitions

  • the invention relates to a turbomachine having at least one circulation structure according to the preamble of patent claim 1, a circulation structure for a turbomachine and a method for introducing a circulation structure into a housing of a turbomachine.
  • Circulation structures or recirculation structures for turbomachines such as gas turbines and in particular their compressors are known as so-called “Casing Treatments” and "Hub Treatments".
  • the primary purpose of the circulation structures is to increase an aerodynamically stable operating range of the compressor by optimizing a surge margin.
  • An optimized surge margin allows higher compressor pressures and thus a higher compressor load.
  • the faults responsible for a local stall and ultimately for pumping the compressor occur at the housing-side ends of the blades of one or more compressor stages or at the hub-side, radially inner ends of the vanes, since in these areas the aerodynamic load in the compressor is highest ,
  • the flow structures in the area of the blade ends are stabilized by the circulation structures.
  • a turbomachine having such a circulation structure is in DE102008010283A1 shown.
  • the circulation structure is arranged in the compressor of the turbomachine, in particular of a gas turbine, and has an annular space which is oriented coaxially with the axis of rotation of a rotor of the turbomachine and is open to the main flow path. When viewed in the main flow direction of the main flow path, a plurality of chambers which can be flowed through in the axial direction are positioned upstream of the annular space.
  • a turbomachine with an alternative circulation structure is in the EP1478828B1 shown. This circulation structure likewise has an annular space oriented coaxially to the axis of rotation of a rotor of the turbomachine and opened to the main flow path, in which, however, a multiplicity of flow guide elements are arranged.
  • the object of the invention is to provide a turbomachine having at least one circulation structure, which allows a simple introduction of the circulation structure in a housing of the turbomachine. Furthermore, it is an object of the invention to provide a circulation structure which can be easily incorporated into a housing of a turbomachine. It is another object of the invention to provide a method for easy introduction of a circulation structure in a housing of a turbomachine.
  • a turbomachine according to the invention has at least one circulation structure, which has an annular space with flow-guiding elements, which surrounds a main flow path and is open to it.
  • a housing of the turbomachine for accommodating the circulation structure is divided in an axial parting plane into a front housing area and a rear housing area.
  • the circulation structure is divided in an axial parting plane into a front structural region and in a rear structural region into an axial parting plane.
  • the division of the turbomachine housing for accommodating the circulation structure into at least two housing areas in combination with the division of the circulation structure into at least two structural areas simplifies the manufacture and introduction of the circulation structure.
  • the front structural region and the rear structural region can thereby be formed by individual insert elements or insertion elements, lining segments or liners and the like, which are separate in the circumferential direction and can be assembled into a ring, or by annular segments closed in the circumferential direction.
  • the axial division of the turbomachine housing and the circulation structure enables, for example, the front structural region of the circulation structure to be introduced directly into the front housing region of the turbomachine, since alternative milling paths and tools can be inserted through the lateral access provided by the axial division. In this way, moreover, the circulation structure can be increased or made more compact.
  • the terms "front” and “rear” refer in each case in the flow direction of a main flow path through the main stream.
  • the introduction of the circulation structure can also be simplified if the same axial separation plane of the housing in the mounted state is equal to the axial parting plane of the circulation structure.
  • the rear structural area in the mounted state can be set back slightly in relation to the parting planes, so that a minimum annular gap is formed between the structural areas in the installed state.
  • the flow guide elements are formed in the front structural area, which is inserted into the front housing area.
  • the front structure portion is composed of a plurality of insert segments circumferentially partitioned from each other and made separately from the front housing portion.
  • the front structural portion is a single circumferentially closed ring member made separately from the front housing portion. The separate production of the front housing portion and the front structural area, the production of the flow guide can be simplified.
  • the flow guide elements are introduced directly into the front housing area. This eliminates the need for separate insert or insertion segments or on a separate ring member for forming the front structural area, which in principle fewer parts must be mounted. In addition, the weight of the turbomachine or its housing is reduced by the integral design of the front structural area in the front housing area.
  • the rear structural portion is an integral front body portion of a trim member inserted into the rear housing portion.
  • the cladding element may consist of a plurality of individual circumferentially divided cladding segments, which together form a closed ring, or be a single cladding ring.
  • the body portion may include a holding portion of the trim member for attaching the trim element to the rear Be housing area, so that no additional sections must be attached to the cladding element or its segments.
  • the cladding element carries a squish or enlacing covering which extends over the cladding element in the circumferential direction and forms a closed ring, so that a blade-tip-side flow around a blade row opposite the cladding element is prevented.
  • a circulation structure according to the invention for a turbomachine has a structural housing which is divided in an axial parting plane into a front structural area and into a rear structural area.
  • the at least two-part design of the circulation structure simplifies their manufacture and in particular their integration into a turbomachine housing.
  • the effect of the circulation structure can be improved if it has flow guidance elements in the front structural area.
  • the flow guide elements can have different lateral spacings from one another, different geometries and / or different positions relative to each other.
  • the flow guide elements can thus have variable circumferential positioning and geometries or courses, whereby the circulation structure can be adjusted specifically to the particular application.
  • a housing of the turbomachine is provided, which is divided in an axial parting plane into a front housing area and into a rear housing area. Then, a front structural portion of the circulation structure is inserted in the front housing portion, and a rear structural portion of the circulation structure is inserted in the rear housing portion. Subsequently, the housing areas are joined in the parting plane.
  • the method allows a simple by the axial separation of the turbomachine housing in the region of the circulation structure and the axial separation of the circulation structure Introducing and in particular an optimal alignment of the circulation structure.
  • introduction means both an insertion of structural regions of the circulation structure produced separately from the turbomachine housing and an integral design of the structural regions in the turbomachine housing, for example by means of a milling process.
  • air passages between flow guide elements are worked out in each case in a single processing run.
  • An exemplary tool is a end mill.
  • the tool guide is preferably chosen such that flow characteristics of the flow guide elements remain unaffected or virtually unaffected.
  • the rear structural area can be turned off, for example.
  • the rear structure portion is integrally formed in the rear housing portion, whereby fewer parts have to be mounted.
  • the front structural area is worked out directly in the front housing area, for example by means of milling operations, virtually only the housing areas are to be mounted.
  • transition radii of the flow guide from the bottom of the air ducts they can be edited separately after Fräse the air channels. This can be done, for example, by means of an alternative end mill with a reduced milling radius compared with the end mill used to form the air channels.
  • FIG. 1 is a longitudinal section through a main flow path or flow channel 1 of a turbomachine in the region of its stator 2 shown.
  • a section through a introduced into the stator 2 circulation structure 4 is shown.
  • the flow channel 1 is from a main flow as shown in FIG. 1 flows through from left to right.
  • the turbomachine is, for example, a gas turbine and in particular an aircraft engine.
  • the stator housing 2 forms a partial housing of the turbomachine and is preferably a compressor of the turbomachine.
  • FIG. 1 shown region of the turbomachine in the flow channel 1 is an adjustable in the stator housing 2 mounted vane ring 6 and a rotor associated blade row 8.
  • the vane ring 6 is arranged in front of the blade row 8 or the blade row 8 behind the blade ring 6.
  • the stator housing 2 is subdivided into a front housing area 10 and into a rear housing area 12 for receiving the circulation structure 4 in an axial dividing plane Ts.
  • the housing portions 10, 12 are each one with the flow channel 1 and the axial Dividing plane Ts open front annular recess 14 and rear annular recess 16 is provided.
  • the ring extensions 14, 16 are arranged in the axial direction or flow direction opposite to each other and together form an approximately U-shaped annular recess.
  • the circulation structure 4 is divided into a front structural area 18 and a rear structural area 20 in an axial dividing plane Tz.
  • the axial parting plane Tz is positioned in such a way that it lies on the axial parting plane Ts of the stator housing 2 in the mounted state shown.
  • the dividing planes Ts, Tz are thus identical or congruent.
  • the rear structure area 20 is slightly recessed in the mounted state with respect to the parting planes Ts, Tz, such that FIG. 1 shown in the assembled state, a minimum annular gap 21 is formed between the structural areas.
  • the rear structure portion 20 may be led to the parting planes Ts, Tz and the front structure portion 18 opposite to the parting planes Ts, Tz reset to form the annular gap 21.
  • the circulation structure 4 defines an annular space 22 which surrounds the flow channel 1 in the radial direction and is open to it.
  • the circulation structure 4 is oriented coaxially with the axis of rotation of the rotor.
  • the front structural portion 18 is formed as an insert member 24 inserted into the front annular recess 14, in which a plurality of circumferentially spaced apart flow directing members 26 are positioned.
  • the insert element 24 is in the embodiment shown, a circumferentially closed ring segment. However, it may also consist of a plurality of circumferentially separated and in the assembled state forming a closed ring segments.
  • the flow guide elements 26 have a blade-like profile and are in the circumferential direction via individual approximately in the axial direction extending air channels 28 (s. FIGS. 3 to 7 ) Figures spaced apart.
  • the rear structural region 20 is designed to be circumferentially symmetrical and, in the exemplary embodiment shown, has a peripheral groove facing the flow guide elements 26.
  • the structural region 20 is integrated in a cladding element 30, which in the embodiment shown consists of a plurality of cladding segments which are separated from one another in the circumferential direction and form a closed ring in the mounted state.
  • the trim element 30 is a single circumferentially closed ring element.
  • the cladding element 30 is provided on its the blade row 8 side facing with a circumferential Anstreifbelag 32.
  • the rear structural portion 20 is formed by an integral front body portion 34 of the trim member 30 which is inserted into the stator rear annular extension 16.
  • the body portion 34 is a holding portion for attaching the trim member 30 to the rear housing portion 12.
  • the body portion 34 has a downstream retaining ring 36 adapted for mounting the trim member 30 in an upstream and in the rear housing portion 12 introduced annular retaining groove 38 engages positively.
  • FIG. 2 a tool guide for forming a circulation structure 4 is shown, which is integrally incorporated into a two-part stator housing 2. Die Statorgenosuse 2 Sind in der Figur 2 hinder.
  • the stator housing 2 is as described above in FIG. 1 in a front housing portion 10 and in a rear housing portion 12 in two parts. In the front housing area 10, a front structural area 18 of the circulation structure 4 and in the rear housing area 12 a rear structural area 20 of the circulation structure 4 are arranged.
  • the flow guide elements 26 are introduced into the front housing area 10 by means of a milling tool 40, for example a milling cutter.
  • the tool guide is such that between the flow guide 26 formed air channels 28 (s. FIGS. 3 to 5 ) are produced in each case in a single machining operation.
  • the end mill 40 has a milling width which corresponds to a circumferential spacing of the flow guide elements 26 from each other.
  • the rear umsymmetrische structural area 20 is also formed in this embodiment by means of the end mill 40 in the stator housing 2, and in particular in the rear housing portion 12.
  • the rear structural portion 20 may be pre-rotated in the rear housing portion 12 prior to milling with the end mill 40, or may only be rotated (see FIG. FIG. 9 ).
  • the flow guide elements 26 or the air channels 28 formed between the flow guide elements 26 can have a uniform circumferential positioning.
  • the air channels 28 then have a uniform concave basic contour 42, a uniform angle of incidence ⁇ in the circumferential direction, a uniform radial height h and a uniform circumferential width b L.
  • the flow guide 26 have a constant circumferential width b s with a uniform circumferential positioning.
  • the width bs corresponds to the width of the end mill 40.
  • the flow guide 26 may also have a varying width b S1 , b S2 , the air guide channels, however, have a uniform width b L , so that both the flow guide 26 and the air channels 28 have a variable circumferential positioning.
  • the angle of attack ⁇ 1 , ⁇ 2 of the air channels 28 and / or the radial height h 1 , h 2 of the air channels 28 can vary.
  • FIGS. 2 to 5 In all prescribed embodiments of the FIGS. 2 to 5 is the same, that for the introduction of the circulation structure 4 in the stator housing 2, first the stator housing 2 in an axial dividing plane Ts in a front housing portion 10 and in a rear housing portion 12 is divided. Thereafter, the front structural portion 18 of the circulation structure 4 is inserted into the front housing portion 10 and the rear structural portion 20 of the circulation structure 4 is inserted into the rear housing portion 12. Subsequently, the front housing portion 10 and the rear housing portion 12 are joined.
  • the formation of the air channels 28 and thus the flow guide 26 is preferably carried out in each case in a single machining operation.
  • FIGS. 6 and 7 the embodiment of current-conducting elements 26 is shown, whose transition radius r r has been reworked to the base contour 42 of the air-conducting channels 28.
  • the transition radii r r are reduced compared to the original transition radius r u .
  • the formation of the reduced transition radii r r is preferably carried out by means of alternative end mills 44, which have a reduced cutting radius and a reduced milling width compared to the original end mill 40.
  • the reduced cutter 44 may be shown in overlapping tracks or as shown in FIG FIG. 7 shown to be guided in adjacent tracks.
  • the reduced cutter 44 are driven into different depths between the flow guide 26, so that in addition to a reduction of the transition radii r r also the basic contour 42 is changed to itself.
  • a quasi-flat basic contour 42 can thus be created, which extends almost tangentially to the circumferential direction.
  • FIG. 7 By way of example, it is thus also possible to provide a quasi-flat basic contour 42 which extends obliquely to the circumferential direction.
  • FIG. 8 a tool guide for introducing a circulation structure 4 is shown in a one-piece stator housing 2 of a turbomachine.
  • the circulation structure 4 has a front asymmetric structure region 18 with a plurality of flow guide elements 26 and a rear circumferentially symmetric structure region 20.
  • the circulation structure 4 is introduced into the stator housing 2 directly by means of a mechanical treatment.
  • the rear structural area 20 can be machined out of the stator housing 2 by a corresponding milling guide.
  • the rear structural area 20 may be preprocessed in a turning operation as indicated by gap 46.
  • the rear structural portion 20 can also be rotated completely.
  • a turbomachine having at least one circulation structure, which has an annular space with flow guide elements, which surrounds a main flow path and is open to it, wherein a housing of the flow machine for receiving the circulation structure is divided in an axial parting plane into a front housing area and a rear housing area, and that the circulation structure is divided in an axial parting plane into a front structural region and a rear structural region, an axially divided two-part circulation structure, and a method.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP13174062.3A 2013-06-27 2013-06-27 Turbomachine et procédé Active EP2818724B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
EP13174062.3A EP2818724B1 (fr) 2013-06-27 2013-06-27 Turbomachine et procédé
US14/315,066 US10151206B2 (en) 2013-06-27 2014-06-25 Turbomachine, circulation structure and method

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP13174062.3A EP2818724B1 (fr) 2013-06-27 2013-06-27 Turbomachine et procédé

Publications (2)

Publication Number Publication Date
EP2818724A1 true EP2818724A1 (fr) 2014-12-31
EP2818724B1 EP2818724B1 (fr) 2020-09-23

Family

ID=48745730

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13174062.3A Active EP2818724B1 (fr) 2013-06-27 2013-06-27 Turbomachine et procédé

Country Status (2)

Country Link
US (1) US10151206B2 (fr)
EP (1) EP2818724B1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106968988A (zh) * 2017-04-25 2017-07-21 西北工业大学 一种轴向前移、径向倾斜的反叶片角向缝处理机匣
EP3375984A1 (fr) 2017-03-17 2018-09-19 MTU Aero Engines GmbH Dispositif de circulation pour une turbomachine, procédé de fabrication d'un dispositif de circulation et turbomachine
EP3734081A1 (fr) * 2019-04-30 2020-11-04 Borgwarner Inc. Dispositif de modification de flux pour compresseurs

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10066640B2 (en) * 2015-02-10 2018-09-04 United Technologies Corporation Optimized circumferential groove casing treatment for axial compressors
GB201600510D0 (en) * 2016-01-12 2016-02-24 Rolls Royce Plc And Rolls Royce Corp Casing arrangement
US10394454B2 (en) * 2017-01-13 2019-08-27 Arm Limited Partitioning of memory system resources or performance monitoring
US10465539B2 (en) * 2017-08-04 2019-11-05 Pratt & Whitney Canada Corp. Rotor casing
US10876423B2 (en) 2018-12-28 2020-12-29 Honeywell International Inc. Compressor section of gas turbine engine including hybrid shroud with casing treatment and abradable section

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63183204A (ja) * 1987-01-26 1988-07-28 Ishikawajima Harima Heavy Ind Co Ltd 軸流回転装置の失速防止構造
EP1286022A1 (fr) * 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
EP1478828B1 (fr) 2002-02-28 2006-12-20 MTU Aero Engines GmbH Structure de recirculation de turbocompresseurs
DE102008010283A1 (de) 2008-02-21 2009-08-27 Mtu Aero Engines Gmbh Zirkulationsstruktur für einen Turboverdichter
EP2434165A1 (fr) * 2009-10-16 2012-03-28 Mitsubishi Heavy Industries, Ltd. Compresseur pour turbocompresseur d'échappement

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6318799Y2 (fr) * 1980-12-02 1988-05-26
US5607284A (en) * 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US6234747B1 (en) * 1999-11-15 2001-05-22 General Electric Company Rub resistant compressor stage
DE102008017844A1 (de) * 2008-04-08 2009-10-15 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit Fluid-Injektorbaugruppe
DE102013210169A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
DE102013210168A1 (de) * 2013-05-31 2014-12-04 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für eine Strömungsmaschine
EP3081779A1 (fr) * 2015-04-14 2016-10-19 MTU Aero Engines GmbH Élément de canal d'écoulement de compresseur de turbine à gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS63183204A (ja) * 1987-01-26 1988-07-28 Ishikawajima Harima Heavy Ind Co Ltd 軸流回転装置の失速防止構造
EP1286022A1 (fr) * 2001-08-14 2003-02-26 United Technologies Corporation Traitement de l'enveloppe pour compresseurs
EP1478828B1 (fr) 2002-02-28 2006-12-20 MTU Aero Engines GmbH Structure de recirculation de turbocompresseurs
DE102008010283A1 (de) 2008-02-21 2009-08-27 Mtu Aero Engines Gmbh Zirkulationsstruktur für einen Turboverdichter
EP2434165A1 (fr) * 2009-10-16 2012-03-28 Mitsubishi Heavy Industries, Ltd. Compresseur pour turbocompresseur d'échappement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3375984A1 (fr) 2017-03-17 2018-09-19 MTU Aero Engines GmbH Dispositif de circulation pour une turbomachine, procédé de fabrication d'un dispositif de circulation et turbomachine
CN106968988A (zh) * 2017-04-25 2017-07-21 西北工业大学 一种轴向前移、径向倾斜的反叶片角向缝处理机匣
CN106968988B (zh) * 2017-04-25 2019-02-26 西北工业大学 一种轴向前移、径向倾斜的反叶片角向缝处理机匣
EP3734081A1 (fr) * 2019-04-30 2020-11-04 Borgwarner Inc. Dispositif de modification de flux pour compresseurs

Also Published As

Publication number Publication date
US10151206B2 (en) 2018-12-11
US20150003976A1 (en) 2015-01-01
EP2818724B1 (fr) 2020-09-23

Similar Documents

Publication Publication Date Title
EP2818724B1 (fr) Turbomachine et procédé
EP2179143B1 (fr) Refroidissement de fente entre une paroi de chambre de combustion et une paroi de turbine d'une installation de turbine à gaz
EP3093447B1 (fr) Rotor d'une turbine a gaz ayant un guidage d'air de refroidissement ameliore
EP2824282A1 (fr) Turbine à gaz avec système de refroidissement de turbine à haute pression
EP3287611B1 (fr) Turbine à gaz
EP3176370B1 (fr) Ensemble d'aubes directrices pour turbomachine
DE102012015449A1 (de) Gasturbinenbrennkammer mit Mischluftöffnungen und Luftleitelementen in modularer Bauweise
EP3121372A1 (fr) Roue de turbine refroidie pour un réacteur
EP2927594B1 (fr) Chambre de combustion d'une turbine à gaz
DE60217049T2 (de) Ölluftseparatorplug
EP3121373B1 (fr) Roue de turbine refroidie, plus particulièrement pour un réacteur
DE102008025249A1 (de) Sammelraum und Verfahren zur Fertigung
DE112015003934T5 (de) Gasturbine
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
DE102016116222A1 (de) Gasturbine
EP2597257B1 (fr) Aubage
EP2378066A2 (fr) Rotor pour une turbomachine
EP2628900A1 (fr) Aube directrice de turbine dotée d'un élément d'étranglement
EP3159487B1 (fr) Stator d'une turbine à gaz ayant un guidage d'air de refroidissement amélioré
EP3309359B1 (fr) Ensemble d'aubes mobiles pour un moteur à turbine à gaz
EP3561228A1 (fr) Aube, segment d'aube et module pour une turbomachine et turbomachine
EP3312388B1 (fr) Pièce de rotor, compresseur, turbine et procédé de fabrication associés
EP3327258A1 (fr) Roue de guidage d'entrée pour une turbomachine
EP2650520B1 (fr) Turbine à gaz d'aéronef avec canal de décharge dans un pied d'aube de guidage d'un canal de flux secondaire
EP2963243A1 (fr) Turbomachine avec aubes rotoriques avec extrémités abaissées en direction du bord de fuite

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

17P Request for examination filed

Effective date: 20130627

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

AX Request for extension of the european patent

Extension state: BA ME

R17P Request for examination filed (corrected)

Effective date: 20150616

RBV Designated contracting states (corrected)

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: EXAMINATION IS IN PROGRESS

17Q First examination report despatched

Effective date: 20181018

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/64 20060101ALI20200123BHEP

Ipc: F04D 27/02 20060101AFI20200123BHEP

Ipc: F04D 29/56 20060101ALI20200123BHEP

Ipc: F04D 29/52 20060101ALI20200123BHEP

Ipc: F04D 29/68 20060101ALI20200123BHEP

INTG Intention to grant announced

Effective date: 20200207

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

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

Free format text: STATUS: THE PATENT HAS BEEN GRANTED

AK Designated contracting states

Kind code of ref document: B1

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

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502013015144

Country of ref document: DE

REG Reference to a national code

Ref country code: IE

Ref legal event code: FG4D

Free format text: LANGUAGE OF EP DOCUMENT: GERMAN

REG Reference to a national code

Ref country code: AT

Ref legal event code: REF

Ref document number: 1316644

Country of ref document: AT

Kind code of ref document: T

Effective date: 20201015

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201224

Ref country code: NO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

Ref country code: BG

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20201223

Ref country code: HR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: FI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LV

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: RS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20200923

REG Reference to a national code

Ref country code: LT

Ref legal event code: MG4D

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SM

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: RO

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: NL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: PT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210125

Ref country code: LT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: EE

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: CZ

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: ES

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: AL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: IS

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20210123

Ref country code: PL

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502013015144

Country of ref document: DE

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: SK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: DK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

Ref country code: SI

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

26N No opposition filed

Effective date: 20210624

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MC

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20210630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LU

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210627

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210630

Ref country code: IE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210627

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210630

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: BE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210630

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 1316644

Country of ref document: AT

Kind code of ref document: T

Effective date: 20210627

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: AT

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20210627

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: HU

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT; INVALID AB INITIO

Effective date: 20130627

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: CY

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MK

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: TR

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: MT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20200923

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20250618

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20250620

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20250626

Year of fee payment: 13