EP0589745B1 - Inlet control system of a turbomachine - Google Patents

Inlet control system of a turbomachine Download PDF

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Publication number
EP0589745B1
EP0589745B1 EP93402171A EP93402171A EP0589745B1 EP 0589745 B1 EP0589745 B1 EP 0589745B1 EP 93402171 A EP93402171 A EP 93402171A EP 93402171 A EP93402171 A EP 93402171A EP 0589745 B1 EP0589745 B1 EP 0589745B1
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EP
European Patent Office
Prior art keywords
vane
compressor
control system
vanes
turbomachine
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.)
Expired - Lifetime
Application number
EP93402171A
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German (de)
French (fr)
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EP0589745A1 (en
Inventor
Pierre Biscay
Alain Jean-Pierre Farrando
Philippe Denis Joubert
Jean-Bernard Martin
Hubert Hippolyte Vignau
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Safran Helicopter Engines SAS
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Turbomeca SA
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Publication date
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Publication of EP0589745A1 publication Critical patent/EP0589745A1/en
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Classifications

    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02Surge control
    • F04D27/0246Surge control by varying geometry within the pumps, e.g. by adjusting vanes
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F04D29/4213Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps suction ports
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04DNON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00Details, component parts, or accessories
    • F04D29/40Casings; Connections of working fluid
    • F04D29/42Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44Fluid-guiding means, e.g. diffusers
    • F04D29/46Fluid-guiding means, e.g. diffusers adjustable
    • F04D29/462Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00Geometry
    • F05D2250/50Inlet or outlet
    • F05D2250/51Inlet
    • YGENERAL 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
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S415/00Rotary kinetic fluid motors or pumps
    • Y10S415/914Device to control boundary layer

Definitions

  • the present invention relates to a system for setting the air supply conditions of a turbomachine.
  • the invention relates in particular to a system of setting for a compressor air intake system centrifugal, and more particularly of the centrifugal compressor external from an auxiliary power unit to a gas turbine.
  • the invention is more particularly applicable in the case of an annular pipe generally used in turbomachinery, and in particular in the suction part of the compressors, and which allows these suction machines directly, or through a plenum, ambient air to properly feed their part axial input.
  • means for adjusting the supply conditions of the tubomachine such as guide vanes, are arranged around the axis of the machine and at intervals regular on a given diameter.
  • These blades are generally with variable angular setting and they can be rotated simultaneously between two extreme positions.
  • the adjustment system allows to reduce significantly the flow through the compressor and therefore the power needed to train it.
  • Such an adaptation is necessary during the phases of starting certain rotary compressor machines external or auxiliary.
  • control means and the cylinder actuation then have a complex structure and expensive.
  • the blades are in the fully closed position, or almost complete, and it is necessary to disassemble in parts the air intake device to perform a endoscopic inspection of certain organs of the auxiliary power, and for example blades of the compressor. This inspection also requires ability to control when the turbomachine is stopped, the adjustment system, in order to bring the blades into their so-called fully open position.
  • the object of the invention is to propose a system for setting of the type mentioned above which allows simultaneously remedy the disadvantages that come to be mentioned.
  • the system of the invention allows the adjustment of the air supply conditions of a turbomachine of the type comprising a series of guide vanes mounted movable between an open position and a closed position of a pipe air inlet of the turbomachine. At least one of the guide vanes has an orifice opening onto the profiled body of the blade. Said blades are arranged in a crown, and each blade is pivotally mounted around an axis parallel to the axis of the crown.
  • said opening orifice crosses the body of the blade and is arranged under the shape of a slit extending in the middle part of the blade substantially in the longitudinal direction of the gas flow the along the dawn, so as to connect the lower surface and the dawn surface and to create a secondary air flow capable of avoiding excessive heating of the turbomachine compressor and allowing endoscopic inspection of the blades.
  • the invention also provides a centrifugal compressor characterized in that it comprises an air intake system produced in accordance with the teachings of the invention.
  • the invention also provides an auxiliary power unit gas turbine, characterized in that it comprises a compressor external centrifugal load with which the air intake system is fitted an adjustment system produced in accordance with the teachings of the invention.
  • FIG. 1 represents a diagram of an auxiliary group of gas turbine power with an external compressor of load can be fitted with an adjustment system according to the invention.
  • Figure 2 is a half sectional view of a charge compressor of an auxiliary power unit equivalent to that shown in Figure 1 and equipped of a system according to the invention.
  • Figure 3 is a half sectional view of a charge compressor air inlet line shown in Figure 2.
  • Figure 4 is a half cross-sectional view of the annular line of the charge compressor, according to the line 4-4 of figure 3, and in which the blades are shown in the open position complete.
  • Figure 5 is a view similar to that of Figure 4, but in which the guide vanes are shown in the fully closed position.
  • Figure 6 is a view similar to those of Figures 4 and 5, but in which the guide vanes are shown in the corresponding intermediate position to a gyratory flow downstream of these.
  • Figure 7 is a perspective view of a blade director with a port for communication of its upper surface with its lower surface, corresponding to a mode for carrying out the invention.
  • the adjustment system according to the invention finds in particular to apply in the case of auxiliary groups gas turbine power, as will be described more in detail later, but of course they can be used in other turbomachinery or industrial devices having for example a compressor with one or more stages, fitted with variable pitch guide vanes, such that turboshaft engines, turbopropellers, turbochargers, auxiliary power units to direct debit, etc.
  • this compressor can be of the type axial, radial or mixed.
  • the air inlet can be radial, axial or mixed.
  • Figure 1 there is shown by way of example a diagram of an auxiliary power unit with turbine to gas, comprising a charge compressor fitted with a adjustment system according to the invention.
  • this set designated by the general reference 1 comprises a turbine engine 2 shown diagrammatically in the area bounded by a dashed line outline.
  • This turbine engine 2 is used to drive a charge compressor 3 supplying compressed air to an accessory pneumatic assembly, such as for example an air conditioning system 4 of an airplane or other devices operated by compressed air such as than pneumatic turbine engines or the like.
  • an accessory pneumatic assembly such as for example an air conditioning system 4 of an airplane or other devices operated by compressed air such as than pneumatic turbine engines or the like.
  • Turboshaft 2 is also suitable for drive an electric generator 5.
  • a drive shaft 6 which comprises by example a conventional type reducer (not shown).
  • the burnt gases 11 are expanded in a turbine two-stage axial 12 to provide the desired power to the drive shaft 6, before being ejected into the atmosphere through an exhaust nozzle 13 arranged downstream of the turbine.
  • the rotation of the shaft 6 ensures the training of power compressor 8, charge compressor 3, the electric generator 5 and possibly others accessories.
  • the compressor has an annular air inlet pipe 14 allowing air to be drawn into a plenum 15 and to power a centrifugal mobile 16.
  • the centrifugal mobile 16 has a series blades 17 for transforming into pneumatic energy mechanical energy transmitted by the drive shaft 6.
  • Air leaks at the top of mobile vanes 17 are limited by a static cover 18.
  • the charge compressor also has a diffusion assembly consisting of a diffuser 19, a radial vane diffuser 20 and a volute 21 which is intended to supply compressed air to the pneumatic assembly 4 mentioned previously.
  • the radial air flow is then transformed in axial flow to properly power the mobile centrifugal 16.
  • the air 22 is compressed by the blades 17 in rotation and is pushed tangentially across broadcast.
  • the kinetic energy of the air leaving the mobile 16 is then transformed into pressure in the diffuser smooth 19 and in the radial vane diffuser 20.
  • Means for adjusting feeding conditions are also provided to adjust the air flow and pressure level supplied to the assembly pneumatic 4.
  • These means consist of a system of setting designated by the general reference 23 in the figure 2, which comprises a series of guide vanes 24 arranged in the radial part of the annular inlet pipe air 14.
  • the vanes 24 are arranged in a crown on the radial part of the gas inlet, at regular intervals, on a control diameter centered on the axis 25 of the machine.
  • the vanes 24 are of variable pitch and are simultaneously orientable through control shafts 26 and a mechanical assembly control aid 28.
  • the adjustment system significantly reduces air flow passing through the compressor and thereby the necessary power to train him through the tree 6 of the turbine engine 2.
  • heating may occur excessive downstream of guide vanes 24 which is detrimental the mechanical strength of the entire compressor, and in particular to the holding of the centrifugal mobile 16, of the diffuser radial 20 and / or volute 21.
  • At least one blade 24 has an orifice 27 for sound communication upper surface with its lower surface.
  • the orifice 27 can be made in the form of a through slot longitudinal, that is to say which extends in the part median of directing dawn 24 substantially according to the longitudinal direction of gas flow along dawn.
  • Ports 27 for communication can be arranged in all of the guide vanes, in a single blade, in two diametrically opposite blades, in three blades arranged at 120 ° relative to the others, or in any other configuration of blades.
  • the holes are inoperative because the small pressure difference between the intrados and extrados of guide vanes.
  • the adjustment system according to the invention is particularly simple to carry out since it requires no additional mechanical parts and also allows a slight reduction in the mass of the system.
  • the endoscopic inspection is very simple, in the fully closed position, by inserting the endoscope through an orifice 27.
  • flow gyratory imposed on the gas flow downstream of the blades guidelines 24 may cause unwanted aerodynamic noise due to noise disturbance caused to the environment immediate, due to the corresponding energy loss inside the annular pipe and because of the risks of vibratory excitation of mechanical parts arranged near this pipe.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)

Description

La présente invention concerne un système de réglage des conditions d'alimentation en air d'une turbomachine.The present invention relates to a system for setting the air supply conditions of a turbomachine.

L'invention concerne notamment un système de réglage pour un système de prise d'air d'un compresseur centrifuge, et plus particulièrement du compresseur centrifuge externe d'un groupe auxiliaire de puissance à une turbine à gaz.The invention relates in particular to a system of setting for a compressor air intake system centrifugal, and more particularly of the centrifugal compressor external from an auxiliary power unit to a gas turbine.

L'invention trouve plus particulièrement à s'appliquer dans le cas d'une conduite annulaire généralement utilisée dans les turbomachines, et notamment dans la partie d'aspiration des compresseurs, et qui permet à ces machines d'aspirer directement, ou à travers un plénum, l'air ambiant pour alimenter convenablement leur partie axiale d'entrée.The invention is more particularly applicable in the case of an annular pipe generally used in turbomachinery, and in particular in the suction part of the compressors, and which allows these suction machines directly, or through a plenum, ambient air to properly feed their part axial input.

Dans la partie radiale de la conduite d'entrée des gaz, des moyens de réglage des conditions d'alimentation de la tubomachine, tels que des aubes directrices, sont disposés autour de l'axe de la machine et à intervalles réguliers sur un diamètre donné.In the radial part of the inlet pipe gases, means for adjusting the supply conditions of the tubomachine, such as guide vanes, are arranged around the axis of the machine and at intervals regular on a given diameter.

Ces aubes, agencées en couronne, sont généralement à calage angulaire variable et elles sont orientables de manière simultanée entre deux positions extrêmes.These blades, arranged in a crown, are generally with variable angular setting and they can be rotated simultaneously between two extreme positions.

Dans l'une de ces positions extrêmes de calage, appelée position d'ouverture complète, toutes les aubes sont orientées sensiblement radialement.In one of these extreme stall positions, called fully open position, all vanes are oriented substantially radially.

Dans l'autre position de calage extrême, appelée position de fermeture complète, toutes les aubes sont orientées tangentiellement par rapport à l'entrée annulaire des gaz.In the other extreme setting position, called fully closed position, all blades are oriented tangentially to the annular entry gases.

En modifiant à la demande le calage angulaire des aubes, il est possible de régler avec précision les conditions d'alimentation du compresseur et donc d'adapter le débit et le niveau de pression fournis aux différents circuits alimentés par ce compresseur.By modifying the angular setting of the blades, it is possible to fine-tune the compressor supply conditions and therefore adapt the flow rate and the pressure level supplied to the different circuits powered by this compressor.

En particulier, et dans le cas de la fermeture complète, le système de réglage permet de réduire de manière importante le débit qui traverse le compresseur et de ce fait, la puissance nécessaire pour l'entraíner. Une telle adaptation est nécessaire lors des phases de démarrage de certaines machines tournantes à compresseur externe ou auxiliaire.In particular, and in the case of closure complete, the adjustment system allows to reduce significantly the flow through the compressor and therefore the power needed to train it. Such an adaptation is necessary during the phases of starting certain rotary compressor machines external or auxiliary.

Dans les dispositifs d'adaptation classique du type décrit précédemment et pour une plage déterminée de calage angulaire des aubes, celles-ci imposent au flux gazeux un écoulement giratoire en direction de l'entrée du compresseur. Ce fonctionnement est recherché pour satisfaire une certaine incidence sur les aubes mobiles du compresseur. Pour certains régimes de fonctionnement, et dans le cas de la position de fermeture complète, il peut se produire un échauffement excessif à l'intérieur du compresseur qui résulte du débit gazeux insuffisant qui traverse alors la turbomachine. Cet échauffement peut être préjudiciable à la tenue mécanique de l'ensemble.In conventional adaptation devices of the type described above and for a determined range of angular setting of the blades, these impose on the flow gaseous gyratory flow towards the entrance compressor. This operation is sought for satisfy some impact on the vanes compressor. For certain operating modes, and in the case of the fully closed position, it may overheat indoors compressor resulting from insufficient gas flow which then passes through the turbomachine. This heating can be detrimental to the mechanical strength of the assembly.

Afin de remédier à cet inconvénient, il a déjà été proposé de réaliser des moyens de commande du système de réglage dans lesquels un vérin d'actionnement des aubes assure un jeu très faible entre les aubes, en position de fermeture, afin de maintenir un débit gazeux minimal à travers le compresseur et afin d'éviter que ce dernier ne s'échauffe excessivement.In order to remedy this drawback, it has already been proposed to realize control means of the adjustment in which a blade actuating cylinder ensures very little play between the blades, in the position of closing, in order to maintain a minimum gas flow at through the compressor and to prevent it from overheating.

Toutefois, les moyens de commande et le vérin d'actionnement sont alors d'une structure complexe et coûteuse.However, the control means and the cylinder actuation then have a complex structure and expensive.

De plus, à l'arrêt de la turbomachine, les aubes directrices sont en position de fermeture complète, ou quasi complète, et il est nécessaire de démonter en partie le dispositif de prise d'air pour effectuer une inspection endoscopique de certains organes du groupe de puissance auxiliaire, et par exemple des aubages du compresseur. Cette inspection nécessite également de pouvoir commander à l'arrêt de la turbomachine, le système de réglage, afin d'amener les aubes dans leur position dite d'ouverture complète.In addition, when the turbomachine stops, the blades are in the fully closed position, or almost complete, and it is necessary to disassemble in parts the air intake device to perform a endoscopic inspection of certain organs of the auxiliary power, and for example blades of the compressor. This inspection also requires ability to control when the turbomachine is stopped, the adjustment system, in order to bring the blades into their so-called fully open position.

On connaít par ailleurs, par les documents FR-A-2 294 345 (United Turbine, sur lequel se base la preambule de la revendication 1), FR-A- 2 438 156 ( Alsthom Atlantique), FR-A- 2 139 741 (SNECMA), DE-A- 3 717 590 (Teledyne Industries) et BE-A-672 432 (Davidson & Co), divers systèmes de compresseurs à aubes, dans lesquels les aubes sont soit dépourvues d'une communication entre l'intrados et l'extrados, soit pourvues d'une communication de très faible section et dont la position, la configuration ne permettent ni de limiter l'échauffement du compresseur, ni d'inspecter l'intérieur du compresseur par une technique d'endoscopie.We also know by documents FR-A-2 294,345 (United Turbine, on which the preamble of claim 1 is based), FR-A- 2,438,156 (Alsthom Atlantic), FR-A- 2 139 741 (SNECMA), DE-A- 3 717 590 (Teledyne Industries) and BE-A-672 432 (Davidson & Co), various vane compressor systems, in which the blades are either devoid of communication between the lower and upper surfaces, either with a communication of very small section and whose position, the configuration neither allow nor limit compressor heating, or inspect the interior of the compressor by an endoscopy technique.

L'invention a pour but de proposer un système de réglage du type mentionné précédemment qui permet de remédier simultanément aux inconvénients qui viennent d'être mentionnés. The object of the invention is to propose a system for setting of the type mentioned above which allows simultaneously remedy the disadvantages that come to be mentioned.

Tel qu'il est revendiqué, le système de l'invention permet le réglage des conditions d'alimentation en air d'une turbomachine du type comportant une série d'aubes directrices montées mobiles entre une position d'ouverture et une position de fermeture d'une conduite d'entrée d'air de la turbomachine. L'une au moins des aubes directrices comporte un orifice débouchant sur le corps profilé de l'aube. Lesdites aubes sont agencées en couronne, et chaque aube est montée pivotante autour d'un axe parallèle à l'axe de la couronne. Selon l'invention, ledit orifice débouchant traverse le corps de l'aube et est agencé sous la forme d'une fente s'étendant dans la partie médiane de l'aube sensiblement selon la direction longitudinale de l'écoulement gazeux le long de l'aube, de façon à mettre en communication l'intrados et l'extrados de l'aube et à créer un flux d'air secondaire apte à éviter un échauffement excessif du compresseur de la turbomachine et à permettre l'inspection endoscopique des aubages.As claimed, the system of the invention allows the adjustment of the air supply conditions of a turbomachine of the type comprising a series of guide vanes mounted movable between an open position and a closed position of a pipe air inlet of the turbomachine. At least one of the guide vanes has an orifice opening onto the profiled body of the blade. Said blades are arranged in a crown, and each blade is pivotally mounted around an axis parallel to the axis of the crown. According to the invention, said opening orifice crosses the body of the blade and is arranged under the shape of a slit extending in the middle part of the blade substantially in the longitudinal direction of the gas flow the along the dawn, so as to connect the lower surface and the dawn surface and to create a secondary air flow capable of avoiding excessive heating of the turbomachine compressor and allowing endoscopic inspection of the blades.

Selon d'autres caractéristiques et avantages de l'invention :

  • l'orifice est agencé dans la partie centrale de l'aube ;
  • en position de fermeture, le bord de fuite et le bord d'attaque de deux aubes consécutives sont sensiblement adjacents, les aubes étant jointives.
According to other characteristics and advantages of the invention:
  • the orifice is arranged in the central part of the blade;
  • in the closed position, the trailing edge and the leading edge of two consecutive blades are substantially adjacent, the blades being contiguous.

L'invention propose également un compresseur centrifuge caractérisé en ce qu'il comporte un système de prise d'air réalisé conformément aux enseignements de l'invention.The invention also provides a centrifugal compressor characterized in that it comprises an air intake system produced in accordance with the teachings of the invention.

L'invention propose encore un groupe auxiliaire de puissance à turbine à gaz, caractérisé en ce qu'il comporte un compresseur centrifuge externe de charge dont le système de prise d'air est équipé d'un système de réglage réalisé conformément aux enseignements de l'invention.The invention also provides an auxiliary power unit gas turbine, characterized in that it comprises a compressor external centrifugal load with which the air intake system is fitted an adjustment system produced in accordance with the teachings of the invention.

D'autres caractéristiques et avantages de l'invention apparaítront à la lecture de la description détaillée qui va suivre pour la compréhension de laquelle on se reportera aux dessins annexés dans lesquels :Other characteristics and advantages of the invention will appear on reading the detailed description which follows for the understanding of which reference will be made to the accompanying drawings in which :

La figure 1 représente un schéma d'un groupe auxiliaire de puissance à turbine à gaz comportant un compresseur externe de charge pouvant être équipé d'un système de réglage selon l'invention.FIG. 1 represents a diagram of an auxiliary group of gas turbine power with an external compressor of load can be fitted with an adjustment system according to the invention.

La figure 2 est une demi-vue en coupe d'un compresseur de charge d'un groupe auxiliaire de puissance équivalent à celui représenté sur la figure 1 et équipé d'un système selon l'invention.Figure 2 is a half sectional view of a charge compressor of an auxiliary power unit equivalent to that shown in Figure 1 and equipped of a system according to the invention.

La figure 3 est une demi-vue en coupe d'une conduite d'entrée d'air du compresseur de charge illustré à la figure 2.Figure 3 is a half sectional view of a charge compressor air inlet line shown in Figure 2.

La figure 4 est une demi-vue en coupe transversale de la conduite annulaire du compresseur de charge, selon la ligne 4-4 de la figure 3, et dans laquelle les aubes directrices sont représentées en position d'ouverture complète.Figure 4 is a half cross-sectional view of the annular line of the charge compressor, according to the line 4-4 of figure 3, and in which the blades are shown in the open position complete.

La figure 5 est une vue similaire à celle de la figure 4, mais dans laquelle les aubes directrices sont représentées en position de fermeture complète.Figure 5 is a view similar to that of Figure 4, but in which the guide vanes are shown in the fully closed position.

La figure 6 est une vue analogue à celles des figures 4 et 5, mais dans laquelle les aubes directrices sont représentées en position intermédiaire correspondant à un écoulement giratoire en aval de celles-ci.Figure 6 is a view similar to those of Figures 4 and 5, but in which the guide vanes are shown in the corresponding intermediate position to a gyratory flow downstream of these.

La figure 7 est une vue en perspective d'une aube directrice comportant un orifice de mise en communication de son extrados avec son intrados, correspondant à un mode de réalisation de l'invention.Figure 7 is a perspective view of a blade director with a port for communication of its upper surface with its lower surface, corresponding to a mode for carrying out the invention.

Le système de réglage selon l'invention trouve notamment à s'appliquer dans le cas des groupes auxiliaires de puissance à turbine à gaz, comme cela sera décrit plus en détail par la suite, mais bien entendu, ils peuvent être utilisés dans d'autres turbomachines ou appareils industriels possédant par exemple un compresseur à un ou plusieurs étages, muni d'aubes directrices à calage variable, tels que des turbomoteurs, des turbopropulseurs, des turbocompresseurs, des groupes auxiliaires de puissance à prélèvement, etc.The adjustment system according to the invention finds in particular to apply in the case of auxiliary groups gas turbine power, as will be described more in detail later, but of course they can be used in other turbomachinery or industrial devices having for example a compressor with one or more stages, fitted with variable pitch guide vanes, such that turboshaft engines, turbopropellers, turbochargers, auxiliary power units to direct debit, etc.

Bien entendu, ce compresseur peut être de type axial, radial ou mixte. De même l'entrée d'air peut être radiale, axiale ou mixte.Of course, this compressor can be of the type axial, radial or mixed. Likewise, the air inlet can be radial, axial or mixed.

Sur la figure 1, on a représenté à titre d'exemple un schéma d'un groupe auxiliaire de puissance à turbine à gaz, comportant un compresseur de charge équipé d'un système de réglage selon l'invention. In Figure 1, there is shown by way of example a diagram of an auxiliary power unit with turbine to gas, comprising a charge compressor fitted with a adjustment system according to the invention.

Dans le mode de réalisation représenté sur cette figure, cet ensemble désigné par la référence générale 1 comporte un turbomoteur 2 représenté schématiquement dans la zone délimitée par un contour en trait mixte.In the embodiment shown in this figure, this set designated by the general reference 1 comprises a turbine engine 2 shown diagrammatically in the area bounded by a dashed line outline.

Ce turbomoteur 2 est utilisé pour entraíner un compresseur de charge 3 fournissant de l'air comprimé à un ensemble pneumatique accessoire, tel que par exemple un système de conditionnement d'air 4 d'un avion ou à d'autres dispositifs actionnés par de l'air comprimé tels que des moteurs à turbine pneumatique ou analogue.This turbine engine 2 is used to drive a charge compressor 3 supplying compressed air to an accessory pneumatic assembly, such as for example an air conditioning system 4 of an airplane or other devices operated by compressed air such as than pneumatic turbine engines or the like.

Le turbomoteur 2 est également adapté pour entraíner une génératrice électrique 5.Turboshaft 2 is also suitable for drive an electric generator 5.

Ces différents organes 2, 3 et 5 sont accouplés au moyen d'un arbre d'entraínement 6 qui comporte par exemple un réducteur de type classique (non représenté).These different organs 2, 3 and 5 are coupled by means of a drive shaft 6 which comprises by example a conventional type reducer (not shown).

Lorsque le turbomoteur 2 fonctionne, de l'air ambiant est aspiré en 7 à une entrée d'un compresseur 8 du turbomoteur. L'air comprimé de sortie du compresseur est mélangé à un carburant 9 avant d'être injecté dans une chambre de combustion 10 pour y brûler de manière continue.When the turbine engine 2 is running, air ambient is sucked in 7 to an inlet of a compressor 8 of the turbine engine. Compressed air from the compressor is mixed with a fuel 9 before being injected into a combustion chamber 10 for continuous burning therein.

Les gaz brûlés 11 sont détendus dans une turbine axiale à deux étages 12 pour fournir la puissance souhaitée à l'arbre d'entraínement 6, avant d'être éjectés dans l'atmosphère à travers une tuyère d'échappement 13 disposée en aval de la turbine.The burnt gases 11 are expanded in a turbine two-stage axial 12 to provide the desired power to the drive shaft 6, before being ejected into the atmosphere through an exhaust nozzle 13 arranged downstream of the turbine.

La rotation de l'arbre 6 assure l'entraínement du compresseur de puissance 8, du compresseur de charge 3, de la génératrice électrique 5 et éventuellement d'autres accessoires.The rotation of the shaft 6 ensures the training of power compressor 8, charge compressor 3, the electric generator 5 and possibly others accessories.

Comme on peut le constater sur la figure 2, le compresseur comporte une conduite annulaire d'entrée d'air 14 permettant d'aspirer de l'air dans un plénum 15 et d'alimenter un mobile centrifuge 16.As can be seen in Figure 2, the compressor has an annular air inlet pipe 14 allowing air to be drawn into a plenum 15 and to power a centrifugal mobile 16.

Le mobile centrifuge 16 comporte une série d'aubages 17 permettant de transformer en énergie pneumatique l'énergie mécanique transmise par l'arbre d'entraínement 6.The centrifugal mobile 16 has a series blades 17 for transforming into pneumatic energy mechanical energy transmitted by the drive shaft 6.

Les fuites d'air au sommet des aubages mobiles 17 sont limitées par un couvercle statique 18. Air leaks at the top of mobile vanes 17 are limited by a static cover 18.

Le compresseur de charge comporte également un ensemble de diffusion constitué d'un diffuseur 19, d'un diffuseur radial à aubes 20 et d'une volute 21 qui est destinée à alimenter en air comprimé l'ensemble pneumatique 4 mentionné précédemment.The charge compressor also has a diffusion assembly consisting of a diffuser 19, a radial vane diffuser 20 and a volute 21 which is intended to supply compressed air to the pneumatic assembly 4 mentioned previously.

Lorsque le compresseur de charge 3 fonctionne, l'air ambiant, désigné par la référence générale 22 sur la figure 2 est aspiré dans le plénum d'alimentation 15 sur l'ensemble de la périphérie de l'entrée d'air.When the charge compressor 3 is running, ambient air, designated by the general reference 22 on Figure 2 is drawn into the supply plenum 15 over the entire periphery of the air inlet.

L'écoulement radial de l'air est alors transformé en écoulement axial pour alimenter convenablement le mobile centrifuge 16. L'air 22 est comprimé par les aubages 17 en rotation et est refoulé tangentiellement dans l'ensemble de diffusion.The radial air flow is then transformed in axial flow to properly power the mobile centrifugal 16. The air 22 is compressed by the blades 17 in rotation and is pushed tangentially across broadcast.

L'énergie cinétique de l'air en sortie du mobile 16 est alors transformée en pression dans le diffuseur lisse 19 et dans le diffuseur radial à aubes 20.The kinetic energy of the air leaving the mobile 16 is then transformed into pressure in the diffuser smooth 19 and in the radial vane diffuser 20.

A la sortie de l'ensemble de diffusion, l'air est collecté dans la volute 21 pour être envoyé à l'ensemble pneumatique 4.At the outlet of the diffusion assembly, the air is collected in volute 21 to be sent to the whole pneumatic 4.

Des moyens de réglage des conditions d'alimentation du compresseur sont également prévus pour régler le débit d'air et le niveau de pression fournis à l'ensemble pneumatique 4.Means for adjusting feeding conditions are also provided to adjust the air flow and pressure level supplied to the assembly pneumatic 4.

Ces moyens sont constitués par un système de réglage désigné par la référence générale 23 à la figure 2, qui comprend une série d'aubes directrices 24 disposées dans la partie radiale de la conduite annulaire d'entrée d'air 14.These means consist of a system of setting designated by the general reference 23 in the figure 2, which comprises a series of guide vanes 24 arranged in the radial part of the annular inlet pipe air 14.

Comme on peut le voir sur les figures 2 à 6, les aubes 24 sont disposées en couronne sur la partie radiale de l'entrée des gaz, à intervalles réguliers, sur un diamètre de commande centré sur l'axe 25 de la machine.As can be seen in Figures 2 to 6, the vanes 24 are arranged in a crown on the radial part of the gas inlet, at regular intervals, on a control diameter centered on the axis 25 of the machine.

Les aubes 24 sont à calage variable et sont orientables de manière simultanée par l'intermédiaire d'arbres de commande 26 et d'un ensemble mécanique auxiliaire de commande 28.The vanes 24 are of variable pitch and are simultaneously orientable through control shafts 26 and a mechanical assembly control aid 28.

En modifiant à la demande le calage des aubes 24, on peut régler avec précision les conditions d'alimentation du compresseur, et donc adapter le débit et le niveau de pression fournis aux différents composants alimentés par ce compresseur.By modifying the timing of the blades 24 on demand, you can fine-tune the conditions compressor supply, and therefore adapt the flow and the pressure level supplied to the various components powered by this compressor.

En particulier, et dans la position de fermeture complète illustrée à la figure 5, le système de réglage permet de réduire de manière importante le débit d'air traversant le compresseur et de ce fait la puissance nécessaire pour l'entraíner par l'intermédiaire de l'arbre 6 du turbomoteur 2.In particular, and in the closed position shown in Figure 5, the adjustment system significantly reduces air flow passing through the compressor and thereby the necessary power to train him through the tree 6 of the turbine engine 2.

Dans le cas de la position de fermeture complète illustrée à la figure 5, il peut se produire un échauffement excessif en aval des aubes directrices 24 qui est préjudiciable à la tenue mécanique de l'ensemble du compresseur, et notamment à la tenue du mobile centrifuge 16, du diffuseur radial 20 et/ou de la volute 21.In the case of the fully closed position illustrated in figure 5, heating may occur excessive downstream of guide vanes 24 which is detrimental the mechanical strength of the entire compressor, and in particular to the holding of the centrifugal mobile 16, of the diffuser radial 20 and / or volute 21.

Enfin, à l'arrêt de la turbomachine 1, les aubes directrices 24 sont en position de fermeture complète et il est alors nécessaire de démonter le système de commande 28 pour ramener les aubes directrices en position d'ouverture complète, illustrée à la figure 4, afin de permettre un contrôle endoscopique des aubages 17 et 20 du compresseur de charge 3.Finally, when the turbomachine 1 stops, the blades guidelines 24 are in the fully closed position and it is then necessary to dismantle the control system 28 to return the guide vanes to the open position complete, illustrated in Figure 4, to allow endoscopic control of blades 17 and 20 of the compressor charging 3.

Conformément à l'invention, au moins une aube 24 comporte un orifice 27 de mise en communication de son extrados avec son intrados.According to the invention, at least one blade 24 has an orifice 27 for sound communication upper surface with its lower surface.

Comme cela est illustré à la figure 7, l'orifice 27 peut être réalisé sous la forme d'une fente débouchante longitudinale, c'est-à-dire qui s'étend dans la partie médiane de l'aube directrice 24 sensiblement selon la direction longitudinale de l'écoulement gazeux le long de l'aube.As illustrated in Figure 7, the orifice 27 can be made in the form of a through slot longitudinal, that is to say which extends in the part median of directing dawn 24 substantially according to the longitudinal direction of gas flow along dawn.

Des orifices 27 de mise en communication peuvent être ménagés dans l'ensemble des aubes directrices, dans une seule aube, dans deux aubes diamétralement opposées, dans trois aubes disposées à 120° les unes par rapport aux autres, ou dans toute autre configuration d'aubes.Ports 27 for communication can be arranged in all of the guide vanes, in a single blade, in two diametrically opposite blades, in three blades arranged at 120 ° relative to the others, or in any other configuration of blades.

Bien entendu, le choix de cette configuration, la forme, la taille et la position des orifices dans les aubes permettent d'optimiser les différents paramètres de fonctionnement du système de réglage selon l'invention.Of course, the choice of this configuration, the shape, size and position of the holes in the blades allow to optimize the different parameters of operation of the adjustment system according to the invention.

Par ailleurs, pour des positions de calage angulaire voisines de la position d'ouverture complète du système de réglage, les orifices sont inopérants du fait de la faible différence de pression existant entre les intrados et les extrados des aubes directrices.Furthermore, for stalling positions angular close to the fully open position of the adjustment system, the holes are inoperative because the small pressure difference between the intrados and extrados of guide vanes.

Le système de réglage selon l'invention est particulièrement simple à réaliser dans la mesure où il ne nécessite aucun organe mécanique supplémentaire et il permet de plus une légère réduction de la masse du système.The adjustment system according to the invention is particularly simple to carry out since it requires no additional mechanical parts and also allows a slight reduction in the mass of the system.

L'inspection endoscopique s'effectue très simplement, en position de fermeture complète, en introduisant l'endoscope par un orifice 27.The endoscopic inspection is very simple, in the fully closed position, by inserting the endoscope through an orifice 27.

Enfin, pour certains régimes de fonctionnement de la turbomachine correspondant à des plages déterminées de débit et d'angle de l'écoulement du flux gazeux, le mouvement giratoire imposé au flux gazeux en aval des aubes directrices 24 peut provoquer un bruit aérodynamique indésirable du fait de la gêne sonore causée à l'environnement immédiat, du fait de la déperdition d'énergie correspondante à l'intérieur de la conduite annulaire et du fait des risques d'excitation vibratoire des pièces mécaniques disposées à proximité de cette conduite.Finally, for certain operating regimes of the turbomachine corresponding to specific ranges of gas flow rate and angle, flow gyratory imposed on the gas flow downstream of the blades guidelines 24 may cause unwanted aerodynamic noise due to noise disturbance caused to the environment immediate, due to the corresponding energy loss inside the annular pipe and because of the risks of vibratory excitation of mechanical parts arranged near this pipe.

La présence d'orifices dans les aubes permet, conformément aux enseignements du document DE-A-2.227.460, d'obtenir une atténuation ou une suppression de ce bruit indésirable.The presence of orifices in the blades allows, in accordance with the teachings of document DE-A-2.227.460, obtain attenuation or suppression of this noise undesirable.

Claims (7)

  1. System (23) for control of the conditions of the supply of air to a turbomachine of the type comprising a series of guide vanes (24) mounted so that they can move between a position in which an air inlet duct (14) of the turbomachine is open and a position in which it is closed, in which at least one of the guide vanes (24) comprises an orifice (27) which opens onto the profiled body of the vane, said vanes (24) being arranged in a ring, and each vane being mounted so that it can pivot about a pin (26) parallel to the axis of the ring, characterized in that the said open orifice (27) passes through the body of the vane and is designed in the form of a slot extending into the middle part of the vane (24) more or less in the longitudinal direction of gaseous flow along the vane, so as to place the pressure face and the suction face of the vane (24) in communication and so as to create a secondary air flow capable of avoiding excessive heating of the compressor of the turbomachine and of allowing the blading to be inspected endoscopically.
  2. Control system according to Claim 1, characterized in that an open orifice (27) is made in just one guide vane (24) so as to attenuate the aerodynamic noise due to vibrational phenomena.
  3. Control system according to Claim 1, characterized in that open orifices (27) are made in two diametrically opposed guide vanes (24) so as to attenuate the aerodynamic noise due to vibrational phenomena.
  4. Control system according to Claim 1, characterized in that open orifices (27) are made in three guide vanes (24) situated 120° apart so as to attenuate the aerodynamic noise due to vibrational phenomena.
  5. Control system according to Claim 1, characterized in that in the closed position, the trailing edge and the leading edge of two consecutive vanes (24) are adjacent, because the vanes (24) are contiguous.
  6. Centrifugal compressor, characterized in that it comprises an air intake system equipped with a control system produced according to any one of the preceding claims.
  7. Gas turbine auxiliary power unit, characterized in that it comprises an external charging centrifugal compressor produced in accordance with Claim 6.
EP93402171A 1992-09-25 1993-09-07 Inlet control system of a turbomachine Expired - Lifetime EP0589745B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9211457A FR2696210B1 (en) 1992-09-25 1992-09-25 System for adjusting the air supply conditions of a turbomachine, centrifugal compressor comprising an adjustment system and auxiliary power unit comprising such a compressor.
FR9211457 1992-09-25

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EP0589745A1 EP0589745A1 (en) 1994-03-30
EP0589745B1 true EP0589745B1 (en) 1998-04-29

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EP93402171A Expired - Lifetime EP0589745B1 (en) 1992-09-25 1993-09-07 Inlet control system of a turbomachine

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EP (1) EP0589745B1 (en)
JP (1) JP2728356B2 (en)
CA (1) CA2106270C (en)
DE (2) DE589745T1 (en)
FR (1) FR2696210B1 (en)

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JP2728356B2 (en) 1998-03-18
FR2696210B1 (en) 1994-10-28
DE589745T1 (en) 1994-09-22
DE69318242T2 (en) 1998-12-24
DE69318242D1 (en) 1998-06-04
FR2696210A1 (en) 1994-04-01
JPH06317183A (en) 1994-11-15
CA2106270A1 (en) 1994-03-26
CA2106270C (en) 1996-11-26
EP0589745A1 (en) 1994-03-30
US5484261A (en) 1996-01-16

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