EP2202385A1 - Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren - Google Patents

Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren Download PDF

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Publication number
EP2202385A1
EP2202385A1 EP08172885A EP08172885A EP2202385A1 EP 2202385 A1 EP2202385 A1 EP 2202385A1 EP 08172885 A EP08172885 A EP 08172885A EP 08172885 A EP08172885 A EP 08172885A EP 2202385 A1 EP2202385 A1 EP 2202385A1
Authority
EP
European Patent Office
Prior art keywords
groove
axis
housing
machine
blade
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Withdrawn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
EP08172885A
Other languages
English (en)
French (fr)
Inventor
Stéphane Hiernaux
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aero Boosters SA
Original Assignee
Techspace Aero SA
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Techspace Aero SA filed Critical Techspace Aero SA
Priority to EP08172885A priority Critical patent/EP2202385A1/de
Publication of EP2202385A1 publication Critical patent/EP2202385A1/de
Withdrawn legal-status Critical Current

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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
    • F01D5/145—Means for influencing boundary layers or secondary circulations
    • 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
    • F01D25/04—Antivibration arrangements
    • F01D25/06—Antivibration arrangements for preventing blade vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/184—Two-dimensional patterned sinusoidal
    • 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
    • F05D2250/611—Structure; Surface texture corrugated undulated

Definitions

  • the invention relates to a turbomachine stator casing treatment for reducing and / or controlling vane head vortices of a moving wheel. More particularly, the invention relates to a turbomachine compressor stator casing, to a turbomachine compressor and to a method for reducing and / or controlling the blade head vortex of a turbomachine compressor impeller.
  • a vortex at the head dawn starts and can negatively influence the flow of fluid along the blades.
  • This phenomenon is illustrated in figure 1 .
  • the head vortex 4 ' is originated in the pressure difference between the intrados and extrados of the blade 3' in motion.
  • the general direction of the flow is indicated by the arrow 1 'and the direction of movement of the blades is indicated by the arrow 2'.
  • the groove networks practiced are intended to form a volume where the nascent vortex can circulate and dissipate at least partially.
  • the presence of a series of grooves distributed evenly around the periphery of the inner surface of the housing according to these various teachings certainly allows a non-stationary action on vortex phenomena at the head of dawn but these different treatments involve a rather heavy implementation from a machining point of view.
  • the object of the invention is to improve the reduction and / or the control of the blade head vortices of a turbomachine wheel and to simplify the implementation of the corresponding treatment.
  • the invention consists of a turbomachine stator casing, comprising an inner surface substantially symmetrical in revolution about the axis of the machine, the casing being intended to receive a rotor provided with at least one row of blades whose ends describe a circular motion near the inner surface of the housing during the rotation of the rotor, the inner surface of the housing having at least one circular groove facing the front portion of the head of the row of blades, the groove being intended reducing and / or controlling the vane head vortex; where the groove describes a ripple along its circular direction.
  • This groove profile provides the advantage of creating a continuous leak between the blade head and the housing and an intermittent leak at a specific position of the blade head.
  • the groove describes an endless loop.
  • the corrugation of the groove is in the plane of the internal surface.
  • the center line of the groove describes a sinusoid.
  • n 1
  • the width of the groove is constant.
  • the depth of the groove is constant.
  • the housing comprises a single groove per stator blade row and the width of the corrugation of the groove measured in a direction parallel to the axis of the machine is equal to or less than one third of the corresponding blade width measured according to the same direction.
  • the groove is made by machining, preferably by means of a milling tool.
  • the invention also consists of a turbomachine compressor comprising a casing and a rotor such as the invention, where the corrugation of the groove is opposite a part of the blade head not exceeding the front half, preferentially the first third of the length of the blades measured along the axis of the machine or an axis contained in the plane of the inner surface at the groove and oriented according to the flow of the fluid.
  • the invention also consists in a method for reducing and / or controlling the vane head vortex of a turbomachine compressor moving wheel rotating in a stator forming a casing of the fluid stream, consisting in producing a circular groove on the inner surface of the casing facing the front part of the blade heads of the moving wheel; where the groove is made so that it describes a ripple along its circular path.
  • the groove describes an endless loop.
  • the groove is made by machining where the machining tool moves relative to the housing along the axis of the machine along the path of the groove during machining.
  • the figure 2 illustrates an elevational view of the blades of a moving wheel, the outer surface of the wheel being folded in the plane of the sheet.
  • the general direction of the flow is indicated by the arrow 1.
  • the direction of displacement of the blades 3 is illustrated by the arrow 2.
  • the crankcase treatment consists of a groove 6 continuous around the periphery of the internal surface of the casing of the turbomachine .
  • This groove forms an endless loop and describes undulations along its profile.
  • the center line of the groove describes undulations along the inner surface of the housing so that the groove evolves opposite the front part of the blade heads 3.
  • the groove is of approximately constant width and depth.
  • the undulation described is a sinusoid whose period corresponds to twice the pitch of blade, that is to say the distance between two neighboring blades.
  • the center line 7 of the groove 6 and its edges upstream and downstream describe along the inner surface of the casing a sinusoidal trajectory.
  • the median plane of the profile is perpendicular to the axis of rotation of the moving wheel.
  • the profile of the groove evolves in an annular band whose upstream edge 8 is at a distance from the leading edge of the blades 3 and the downstream edge 9 is at a distance from the leading edge corresponding to about a third of the length of the blade. 'dawn.
  • the trajectory or the corrugated profile of the center line of the groove has the advantage of generating in addition to its stationary effect a non-stationary effect similar to that of the repeated grooves of the state of the art while being much simpler to put implemented.
  • the continuous volume formed by the groove creates a permanent leak between the intrados and the extrados of the blade head and thus allows stabilization of the head vortex in a stationary manner, that is to say so constant along the periphery of the inner surface of the housing.
  • the fact that the groove covers several axial positions makes it possible to create an intermittent leak between the lower surface and the upper surface of the blade head for a given position of the head. This intermittent leakage induces a pulsed jet that reduces the incidence of flow on the blade head. Depending on the period of the undulation and depending on the speed of rotation of the moving wheel, the pulsed jets generated can induce non-stationary phenomena.
  • the depth p and the width I are generally constant, but it would be possible to vary them.
  • the depth is typically of the order of the clearance between the blade heads and the inner surface of the housing. In practice, the depth is slightly greater in order to compensate for possible wear resulting from friction between the blade heads and the casing. This game usually corresponds to about 1 to 2% of the blade height.
  • n is greater than 1, we obtain a more complex form with this time 2n parameters. This increases the frequency content, which makes it possible to interact on several fundamental frequencies of the flow (for example the Crow and Widnall frequencies of vorticity stability) or of the dawn (for example, the bending modes of the head of dawn). In practice n is equal to 2 or 3 but higher values are possible.
  • the frequency of the sinusoid (s) it is also possible to induce a non-stationary force on the blade head to damp the oscillations of certain modes of the blades.
  • the oscillations to which the vanes are subjected are, for example, of the "bending" type corresponding to a bending deformation of the blade and also of the "Stripe” type, which is a so-called deformation of the blade.
  • the frequency content of the groove can therefore be selected so as to generate forces countering certain oscillations inherent in certain operating modes of the machine and particularly harmful for the lifetime of the blade.
  • crankcase treatment is particularly easy. It requires the machining of the groove by means of a machining machine where the cutting tool is moved relative to the housing or vice versa, according to the desired profile.
  • the housing is moved in rotation relative to the cutting tool which is moved only according to the axis of the turbomachine. It is the axial displacement of the synchronized cutting tool with the rotational displacement of the housing which defines the corrugations of the groove.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP08172885A 2008-12-24 2008-12-24 Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren Withdrawn EP2202385A1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08172885A EP2202385A1 (de) 2008-12-24 2008-12-24 Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08172885A EP2202385A1 (de) 2008-12-24 2008-12-24 Bearbeitung des Kompressorgehäuses eines Turbotriebwerks, die in der Anlegung einer Ringnut besteht, die eine Wellenbewegung beschreibt, um die Wirbel am Leitschaufelkopf zu kontrollieren

Publications (1)

Publication Number Publication Date
EP2202385A1 true EP2202385A1 (de) 2010-06-30

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EP08172885A Withdrawn EP2202385A1 (de) 2008-12-24 2008-12-24 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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EP (1) EP2202385A1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538024A1 (de) * 2011-06-24 2012-12-26 Alstom Technology Ltd Schaufel einer Strömungsmaschine
EP4060165A1 (de) 2021-03-03 2022-09-21 Safran Aero Boosters Gehäuse für kompressor eines turbotriebwerks
CN116443771A (zh) * 2023-06-16 2023-07-18 太原福莱瑞达物流设备科技有限公司 一种具有防坠功能的堆垛机

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2343944A1 (fr) * 1976-03-09 1977-10-07 Westinghouse Electric Corp Joint tournant en labyrinthe
JPS58113504A (ja) 1981-12-26 1983-07-06 Toshiba Corp 軸流流体機械の動翼構造
US6375416B1 (en) * 1993-07-15 2002-04-23 Kevin J. Farrell Technique for reducing acoustic radiation in turbomachinery
FR2832180A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Revetement abradable pour parois de turbines a gaz
US6582189B2 (en) 1999-09-20 2003-06-24 Hitachi, Ltd. Turbo machines
US20050141990A1 (en) * 2003-11-26 2005-06-30 Volker Guemmer Turbomachine wtih fluid supply
EP1715224A1 (de) * 2005-04-18 2006-10-25 Siemens Aktiengesellschaft Dichtung für eine Strömungsmaschine
US20070160459A1 (en) * 2006-01-12 2007-07-12 Rolls-Royce Plc Blade and rotor arrangement
EP1961920A1 (de) 2007-02-21 2008-08-27 Snecma Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2343944A1 (fr) * 1976-03-09 1977-10-07 Westinghouse Electric Corp Joint tournant en labyrinthe
JPS58113504A (ja) 1981-12-26 1983-07-06 Toshiba Corp 軸流流体機械の動翼構造
US6375416B1 (en) * 1993-07-15 2002-04-23 Kevin J. Farrell Technique for reducing acoustic radiation in turbomachinery
US6582189B2 (en) 1999-09-20 2003-06-24 Hitachi, Ltd. Turbo machines
FR2832180A1 (fr) * 2001-11-14 2003-05-16 Snecma Moteurs Revetement abradable pour parois de turbines a gaz
US20050141990A1 (en) * 2003-11-26 2005-06-30 Volker Guemmer Turbomachine wtih fluid supply
EP1715224A1 (de) * 2005-04-18 2006-10-25 Siemens Aktiengesellschaft Dichtung für eine Strömungsmaschine
US20070160459A1 (en) * 2006-01-12 2007-07-12 Rolls-Royce Plc Blade and rotor arrangement
EP1961920A1 (de) 2007-02-21 2008-08-27 Snecma Gehäuse mit Gehäusebehandlung, Kompressor und Turbinentriebwerk, das ein solches Gehäuse umfasst

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538024A1 (de) * 2011-06-24 2012-12-26 Alstom Technology Ltd Schaufel einer Strömungsmaschine
US9377029B2 (en) 2011-06-24 2016-06-28 General Electric Technology Gmbh Blade of a turbomachine
EP4060165A1 (de) 2021-03-03 2022-09-21 Safran Aero Boosters Gehäuse für kompressor eines turbotriebwerks
BE1029166A1 (fr) 2021-03-03 2022-09-27 Safran Aero Boosters Carter pour compresseur de turbomachine
CN116443771A (zh) * 2023-06-16 2023-07-18 太原福莱瑞达物流设备科技有限公司 一种具有防坠功能的堆垛机
CN116443771B (zh) * 2023-06-16 2023-08-22 太原福莱瑞达物流设备科技有限公司 一种具有防坠功能的堆垛机

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