EP1961920A1 - Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst - Google Patents

Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst Download PDF

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Publication number
EP1961920A1
EP1961920A1 EP08151676A EP08151676A EP1961920A1 EP 1961920 A1 EP1961920 A1 EP 1961920A1 EP 08151676 A EP08151676 A EP 08151676A EP 08151676 A EP08151676 A EP 08151676A EP 1961920 A1 EP1961920 A1 EP 1961920A1
Authority
EP
European Patent Office
Prior art keywords
treatment zone
housing
housing according
casing
cavity
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
EP08151676A
Other languages
English (en)
French (fr)
Other versions
EP1961920B1 (de
Inventor
Yann Lebret
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1961920A1 publication Critical patent/EP1961920A1/de
Application granted granted Critical
Publication of EP1961920B1 publication Critical patent/EP1961920B1/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F04D29/66—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
    • 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
    • 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
    • F05D2240/14—Casings or housings protecting or supporting assemblies within
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • 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
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/182—Two-dimensional patterned crenellated, notched
    • 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
    • F05D2250/60—Structure; Surface texture
    • 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
    • F05D2250/60—Structure; Surface texture
    • F05D2250/61—Structure; Surface texture corrugated

Definitions

  • the invention relates to a casing supporting series of vanes fixed between which series of vanes are arranged in rotation about a longitudinal axis, the radially outer end of said vanes being close to the internal face of the casing; a crankcase used in an aviation turbojet.
  • the present invention relates to the production of a compressor, in particular of the axial type, in particular a compressor operating at low pressure but also a compressor operating at high pressure, comprising a casing as mentioned above.
  • the present invention also relates to a turbomachine, in particular a turbojet, comprising such a housing or such a compressor.
  • Compressors of this type used in particular in turbojet engines, consist of a rotor comprising either a succession of separate disks stacked one after the other, or a single drum intended to receive the series of blades of the different stages. .
  • this rotor comprises grooves made by machining in order to form between two neighboring stages a space in which are interposed the vanes of the stator stages secured to a fixed part having a housing.
  • This casing forms a section of the radially outermost zone of the vein along which the air circulates in the turbomachine.
  • the moving blades are secured individually to the drum at the housing, distributed regularly and in number equal to that of the blades, whose shape is determined to cooperate by complementarity of shape with the foot of the blade, this which ensures the radial immobilization, for example by a fastening of the dovetail type.
  • immobilization in translation, in particular axial, the foot of the blade relative to its housing it is provided most often separately for each blade by a ball system, pin, clip, flange, spacer etc.
  • pumping is a phenomenon that is sought to avoid within the engine since it results in sudden oscillations of air pressure and air flow, which subject the blades to considerable mechanical stresses which could lead to their weakening or even their rupture.
  • This phenomenon can be initiated by oscillations of pressure at the top of the blade, with a strong interaction between the boundary layer at the top of the blade with the boundary layer of the crankcase.
  • the rotating detachment is a phenomenon that is created when winnowing conditions (operating point) and rotational speeds are met.
  • this phenomenon is triggered when the profile is put into so-called positive incidence, it is then created a non-stationary phenomenon leading to a local detachment of a blade, detachment that will spread from one blade to another, during of the rotation.
  • the present invention aims to provide a housing to overcome the disadvantages of crankcase treatments of the prior art while avoiding excessive energy loss.
  • the present invention therefore aims to reduce locally the pumping phenomenon, increasing the current pumping margin, without reducing the efficiency of the engine.
  • the casing comprises at least one ring located opposite one of the series of blades, at least one casing treatment area facing the vanes comprising at least one groove (groove or furrow) delimiting a closed contour.
  • the housing has different zones: so-called “smooth” zones (that is to say without specific crankcase treatment), as well as areas that will support crankcase treatment.
  • the number of these areas supporting the crankcase treatment and the angular coverage covered by these zones depends on the machine considered, and can be reduced to an area covering 360 degrees in some cases.
  • each of these zones may advantageously be located on an angular sector corresponding to 1.5 to 2.5 no blades.
  • crankcase treatment areas which are each located at an angular sector restricted to 1.5 to 2.5 no moving blades, local evacuation of the crankcase is allowed. the air of the boundary layer in the space between the blade and the housing, opposite the treatment zone, in order to avoid the phenomenon of pumping.
  • said treatment zone extends axially over a distance representing 2/3 to 9/10 of the length of the blades in the axial direction.
  • the ratio between the open surface and the solid surface is of the order of 2
  • crankcase treatment zone is formed directly on the inner wall of the crankcase.
  • crankcase treatment zone is formed on a plate attached to the crankcase.
  • said plate is made, in whole or in part of the surface, of an abradable material.
  • the housing further comprises a cavity formed behind and radially outside the treatment zone.
  • This cavity has the same axial extent (depending on the length of the housing) and / or transverse (depending on the width of the blade) that the treatment area, or a smaller extent in one and / or the other of directions, or a greater extent in one and / or the other direction.
  • the housing has on the same annular portion, a plurality of treatment zones and said cavity of each treatment zone is in communication with said cavity of another treatment zone. This makes it possible to promote the circulation of air between the treatment zones.
  • FIG. 1 a portion of a housing 10 limited by an angular sector whose direction corresponds to the height of the sheet, and extending in an axial direction which corresponds to the width of the sheet. More specifically, on the figure 1 this portion of the casing 10 is viewed in the direction of its radially inner face turned in the direction of a rotor wheel not shown on FIG. figure 1 .
  • the inner surface of the housing portion shown has an oval-shaped closed contour groove 12, for example machined directly into the housing.
  • the groove 12 forms a local housing treatment zone which does not extend over the annular peripheral assembly of the housing 10.
  • this groove 12 is a crankcase treatment area which extends over an angular sector limited to 1.5 to 2.5 P blade pitch.
  • crankcase treatment corresponds to a topology quite different from that usually encountered for this type of crankcase treatment.
  • the gap 30 located between the blade 20 and the casing treatment zone comprising the groove 12 has at two locations a corresponding radial enlargement in the hollow of the groove 12. This configuration makes it possible to achieve the local disturbances of the rotational detachment phenomenon mentioned in the preamble.
  • the housing 10 may have, over its entire periphery, several grooves 12 similar (for example two, three or more) distributed regularly.
  • the groove 12 may have a width of between 5% and 25% of the pitch, to delimit an axially extending oval shape (large dimension of the oval shape) over a distance of between 60% and 90% of the length of the inter-blade channel and transversely (small dimension of the oval shape) over a distance of between 10% and 90% of the width of the inter-blade channel.
  • this contoured closed contour groove 12 may be formed on a plate attached to the housing 10, this plate may be made of abradable material.
  • the shape of the groove (or groove), the depth and the surface covered is the result of an optimization depending on how the dawn does the work.
  • the objective of this crankcase treatment located on a few centimeters to a few tens of centimeters, is to modify the energy distribution of the boundary layer, to restore energy to the boundary layer of the weakened zone of the dawn subject to detachment, and also to play the role of a disrupter that prevents detachment from settling and spreading to adjacent blades.
  • groove or grooves can start before the leading edge and end after the trailing edge, and it may be necessary to use treatments with concentric grooves, or to have a set of mirror grooves by performing two adjacent treatments having a plane of symmetry between them.
  • the groove 12 'always has a closed contour which is no longer oval but which corresponds to a set of rectilinear sections interconnected to form an irregular geometrical figure, here with eight sides.
  • the housing 10 which, in addition to a closed contour groove 12 of oval shape similar to that shown on the figure 1 , has an annular rear cavity 14 extending, opposite the crankcase treatment area, over the entire periphery of the housing.
  • the grooves 12 open into this cavity 14, which thus allows communication between different treatment areas that may be present on different angular sectors.
  • FIG. 7 and 8 there is shown a second variant of the second embodiment, in which an annular rear cavity 14 has been provided opposite a treatment zone similar to that of the second variant of the first embodiment shown in the drawings.
  • Figures 3 and 4 namely a closed contour contour groove 12 'of irregular octagonal shape, which opens into the cavity 14.
  • this cavity 14 preferably has a depth corresponding to one time to three times the depth of the treatment zone (of the closed contour groove 12 or 12 '), and a width in the axial direction which is preferably greater than that of the treatment zone, in particular greater than 10 to 20% (in this case the width of the treatment zone corresponds to the axial distance covered by the closed contour groove 12 or 12 ').
  • the cavity 14 can be obtained by machining.
  • the treatment zone extends axially over a distance representing at least 2/3 of the length of the blades 20 in the axial direction.
  • the depth of the cavity 14 is between 1 and 4 times the depth of the treatment zone.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08151676A 2007-02-21 2008-02-20 Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst Active EP1961920B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0753399A FR2912789B1 (fr) 2007-02-21 2007-02-21 Carter avec traitement de carter, compresseur et turbomachine comportant un tel carter.

Publications (2)

Publication Number Publication Date
EP1961920A1 true EP1961920A1 (de) 2008-08-27
EP1961920B1 EP1961920B1 (de) 2010-04-07

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08151676A Active EP1961920B1 (de) 2007-02-21 2008-02-20 Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst

Country Status (7)

Country Link
US (1) US8100629B2 (de)
EP (1) EP1961920B1 (de)
JP (1) JP5152492B2 (de)
CA (1) CA2621727C (de)
DE (1) DE602008000914D1 (de)
FR (1) FR2912789B1 (de)
RU (1) RU2489602C2 (de)

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EP2202385A1 (de) 2008-12-24 2010-06-30 Techspace Aero S.A. Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren

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US9234526B2 (en) 2010-02-09 2016-01-12 Tsinghua University Centrifugal compressor having an asymmetric self-recirculating casing treatment
WO2011099416A1 (ja) 2010-02-09 2011-08-18 株式会社Ihi 非対称自己循環ケーシングトリートメントを有する遠心圧縮機
EP2535598B1 (de) * 2010-02-09 2018-06-06 IHI Corporation Zentrifugalverdichter mit einer asymmetrischen selbst-rückzirkulierenden gehäusebearbeitung
EP2535597B1 (de) 2010-02-09 2018-06-20 IHI Corporation Zentrifugalverdichter mit einer asymmetrischen selbst-rückzirkulierenden gehäusebearbeitung
DE102011006273A1 (de) 2011-03-28 2012-10-04 Rolls-Royce Deutschland Ltd & Co Kg Rotor einer Axialverdichterstufe einer Turbomaschine
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RU2016137904A (ru) 2014-02-25 2018-03-29 Сименс Акциенгезелльшафт Термобарьерное покрытие компонента турбины с изолирующими трещины техническими элементами в виде канавок
WO2016133582A1 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Turbine shroud with abradable layer having dimpled forward zone
US9151175B2 (en) 2014-02-25 2015-10-06 Siemens Aktiengesellschaft Turbine abradable layer with progressive wear zone multi level ridge arrays
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US9249680B2 (en) 2014-02-25 2016-02-02 Siemens Energy, Inc. Turbine abradable layer with asymmetric ridges or grooves
US9243511B2 (en) 2014-02-25 2016-01-26 Siemens Aktiengesellschaft Turbine abradable layer with zig zag groove pattern
WO2016133982A1 (en) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Forming cooling passages in thermal barrier coated, combustion turbine superalloy components
US10041500B2 (en) 2015-12-08 2018-08-07 General Electric Company Venturi effect endwall treatment
US10422348B2 (en) * 2017-01-10 2019-09-24 General Electric Company Unsymmetrical turbofan abradable grind for reduced rub loads
JP2020510783A (ja) * 2017-03-03 2020-04-09 エリオット・カンパニー キャビティ音響モードによる騒音及び構造の励振を最低限に抑える方法及び構成
DE102018116062A1 (de) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Strukturbaugruppe für einen Verdichter einer Strömungsmaschine

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EP0688400A1 (de) 1993-03-11 1995-12-27 Central Inst Of Aviat Motors C Schaufelspitzeneinrichtung zum schutz gegen strömungsablösung
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2202385A1 (de) 2008-12-24 2010-06-30 Techspace Aero S.A. Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren

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FR2912789B1 (fr) 2009-10-02
EP1961920B1 (de) 2010-04-07
RU2008106633A (ru) 2009-08-27
JP5152492B2 (ja) 2013-02-27
DE602008000914D1 (de) 2010-05-20
CA2621727A1 (fr) 2008-08-21
CA2621727C (fr) 2015-06-16
US8100629B2 (en) 2012-01-24
FR2912789A1 (fr) 2008-08-22
JP2008202598A (ja) 2008-09-04
RU2489602C2 (ru) 2013-08-10
US20080199306A1 (en) 2008-08-21

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