EP2321534B1 - Fond intermédiaire de carter pour une turbomachine - Google Patents

Fond intermédiaire de carter pour une turbomachine Download PDF

Info

Publication number
EP2321534B1
EP2321534B1 EP09782156.5A EP09782156A EP2321534B1 EP 2321534 B1 EP2321534 B1 EP 2321534B1 EP 09782156 A EP09782156 A EP 09782156A EP 2321534 B1 EP2321534 B1 EP 2321534B1
Authority
EP
European Patent Office
Prior art keywords
intermediate housing
housing floor
part joint
layer
joint face
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.)
Not-in-force
Application number
EP09782156.5A
Other languages
German (de)
English (en)
Other versions
EP2321534A1 (fr
Inventor
Wolfgang Zacharias
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Publication of EP2321534A1 publication Critical patent/EP2321534A1/fr
Application granted granted Critical
Publication of EP2321534B1 publication Critical patent/EP2321534B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/083—Sealings especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
    • F04D17/08—Centrifugal pumps
    • F04D17/10—Centrifugal pumps for compressing or evacuating
    • F04D17/12—Multi-stage pumps
    • F04D17/122—Multi-stage pumps the individual rotor discs being, one for each stage, on a common shaft and axially spaced, e.g. conventional centrifugal multi- stage compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/162—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of a centrifugal 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
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/62—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps
    • F04D29/624—Mounting; Assembling; Disassembling of radial or helico-centrifugal pumps especially adapted for elastic fluid pumps

Definitions

  • the invention relates to a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom.
  • a turbomachine such as a radial turbocompressor is configured as a single shaft compressor having a shaft with impellers threaded thereon and a housing surrounding the impellers.
  • the shaft is mounted radially and axially outside of the housing by means of bearings, wherein flow channels are formed from and to the wheels in the interior of the housing by the provision of housing internals.
  • the wheels are, for example, designed as radial impellers, which have, for example, an axial inflow direction and a radial outflow direction.
  • the impellers are flowed through one after the other so that process gas is gradually compressed from impeller to impeller.
  • a ring diffuser is provided, through which the process gas is guided radially outward.
  • the process gas is deflected and guided radially inward through a return channel to the next impeller.
  • the housing internals are provided with a corresponding shape, so that the ring diffuser, the deflection channel and the return channel are formed by the interaction of the housing internals in the housing.
  • the housing internals are conventionally designed as housing intermediate floors.
  • Each housing intermediate floor is formed by two halves, so that the housing intermediate floor is divisible horizontally.
  • a housing intermediate bottom by attaching the one half in the lower part of the housing (horizontally divided turbomachine) or in the lower part of Inner housing (vertically divided turbomachine) and are mounted by applying the other half in the upper part.
  • the two halves form at their contact surfaces of a parting line, which due to manufacturing inaccuracies and / or deformation of the halves caused by a compressive stress during operation of the radial turbo compressor diverge and thus can be gas permeable.
  • a leakage occurs through the parting line, which is considerable, especially in radial turbochargers with high pressure differences.
  • the leakage in Radial turbo compressors with high pressure ratio and small flow rate is disadvantageous. Due to the leakage, the efficiency of the radial turbocompressor is reduced, whereby the required power consumption is increased in the fulfillment of predefined boundary conditions by the radial turbocompressor.
  • the maximum possible prediction accuracy with respect to pressure ratio and flow rate of the radial turbocharger is subject to higher tolerances, since the actual effect of the possibly gaping parting line on the operating parameters of the radial turbocompressor is difficult to predict.
  • the object of the invention is to provide a housing intermediate bottom for a turbomachine and a turbomachine with the housing intermediate bottom, wherein the turbomachine has a high efficiency.
  • the object is achieved by a housing intermediate floor of the type mentioned, which has the additional features of the characterizing part of claim 1.
  • the housing intermediate floor in the turbomachine of the housing intermediate bottom is provided with the parting line and the two parting surfaces.
  • the recess formed in the one part of the joint surface is provided with the coating, wherein protrudes from the one part of the joint surface, the coating, so that the coating has the supernatant.
  • the two parting surfaces are placed against each other so that the coating rests against the other parting surface facing it. Once the parting surfaces are arranged touching each other, the coating is compressed at its supernatant. As a result, the coating lies tightly and flat against the parting surface facing it, so that the parting line is sealed by the coating.
  • leakage of process gas through the parting line is prevented or at least reduced, as a result of which the turbomachine has improved efficiency.
  • the intermediate housing bottom is sealed off from the coating in the assembled state at the parting line, so that such structural inaccuracies can not lead to a deterioration in the performance parameters of the turbomachine.
  • the performance parameters of the turbomachine can be better predicted by conventional methods, so that the turbomachine can be designed accurately.
  • the risk is reduced that it is determined in a possible test run the turbomachine that the turbomachine can not meet the required performance parameters.
  • corresponding rectification actions on the turbomachine would be necessary, which can be omitted according to the invention.
  • the coating is a honeycomb layer.
  • the honeycomb layer can be produced inexpensively from correspondingly shaped metal strips, with which a honeycomb structure of the honeycomb layer is formed.
  • the honeycomb structure is formed such that the sheet metal strips are compressed in the assembled state of the housing intermediate bottom of the other part of the joint surface.
  • the honeycomb layer is preferably soldered into the trough.
  • the coating is preferably a flame-sprayed or plasma-sprayed sprayed coating.
  • the sprayed layer is preferably Ni-Al-Cr-based.
  • a trough and in the other part of the joint surface is provided, in each of which one of the coatings is housed, wherein the coatings are arranged overlapping each other.
  • one partial joint surface is the honeycomb layer and for the other partial joint surface to be the sprayed layer.
  • the honeycomb layer is provided with its supernatant on one part of the joint surface and the sprayed layer on the other part of the joint surface. If the part-joint surfaces are placed against one another during assembly, the honeycomb layer is optionally pressed into the sprayed layer under its own deformation, so that the honeycomb layer forms a dense structure in the parting joint with the sprayed layer.
  • the thickness of the sprayed layer is preferably dimensioned at the other parting surface at least as large as the supernatant of the honeycomb layer, so that in the assembled state of the housing intermediate bottom, the honeycomb layer is pressed into the sprayed layer.
  • the spray layer extends in the assembled state of the housing intermediate base only in the honeycomb interstices of the honeycomb layer, since the honeycomb layer abuts the bottom of the trough - with a certain margin for manufacturing tolerances - of the other part joint surface.
  • the parting line with the honeycomb layer and the sprayed layer is stable and tightly sealed.
  • the supernatant is carried out on the sprayed layer.
  • the housing intermediate bottom is formed from a lower half and an upper half, which in the assembled state form the parting line in a plane in which the axis of rotation of the turbomachine lies.
  • the housing intermediate bottom is formed from the approximately equal halves, so that the housing intermediate floor is easy to assemble and disassemble. It is preferred that on the lower half of the one part of the joint surface with the honeycomb layer and on the upper half of the other part of the joint surface is provided with the sprayed layer. Alternatively, it is preferred that on the upper half of a parting surface with the Honeycomb layer and on the lower half of the other part of the joint surface is provided with the sprayed layer.
  • the turbomachine is a radial turbocompressor having a radial turbocompressor stage with a ring diffuser, a deflection channel and a return channel, which are formed by at least two housing intermediate floors.
  • a radial turbo compressor 1 comprises a housing 2 or a housing 2 and an inner housing 33 and a rotor 3.
  • a suction nozzle 4 and a discharge nozzle 5 is provided, wherein the suction nozzle 4 opens in the interior of the housing 2 in an inlet 6 and an opening provided in the interior of the housing 2 exit spiral 7 opens into the discharge nozzle 5.
  • each of an impeller 9 of the rotor 3 is formed.
  • Each impeller 9 has an axial inflow direction pointing in the direction of the rotation axis 24 of the rotor 3 and a radial outflow direction pointing outwards.
  • a ring diffuser 10 which extends radially outward within the housing 2 and downstream of the impeller 9 this is followed.
  • the annular diffuser 10 is followed in the flow direction by a deflection channel 11, in which process gas is deflected by the ring diffuser 10 into a return channel 12, in which the process gas flows radially inwards towards the impeller 9 of the next radial turbocompressor stage 8.
  • a first intermediate housing bottom 13 and a second housing intermediate bottom 14 is provided for the Radialturbover Whyrtre 8, which are provided with such a contour and arranged to each other such that under cooperation of the first housing intermediate bottom 13 and the second housing intermediate bottom 14 of the ring diffuser 10, the deflection channel 11 and the return channel 12 are formed in the housing 2.
  • the first housing intermediate bottom 13 has a cylindrical outer side 15 and is located on the inside of the housing 2, wherein the first housing intermediate bottom 13 is locked with an annular web 16 on the housing 2.
  • the first housing intermediate bottom 13 and the second housing intermediate bottom 14 are similar in their construction, so that in the following only the first housing intermediate bottom 13 is referred to.
  • the first housing intermediate bottom 13 has a lower half 17 and an upper half 18, so that of the lower half 17 and the upper half 18, a parting line 19 is formed.
  • the lower half 17 and the upper half 18 are formed substantially geometrically the same, so that the parting line 19 lies in a plane in which the axis of rotation 24 of the radial turbocompressor 11 is located.
  • the lower half 17 has a part-joint surface 20 and the upper half 18 has a part-joint surface 21, wherein the part-joint surfaces 20, 21 formed identically in their outline are, so that when the lower half 17 is applied to the upper half 18 to form the parting line 19, the parting surfaces 20 and 21 completely overlap.
  • a plan view of the parting surface 20 of the lower half 17 is shown.
  • a trough 22 is provided, the border of which is always arranged at a distance from the edge of the parting surface 20.
  • the trough 22 is completely surrounded by the parting surface 20.
  • a honeycomb layer 23 is housed, which completely fills the trough 22.
  • the honeycomb layer 23 is constructed of metal strips 25 which are wave-shaped and are joined together to form honeycomb.
  • a solder 27 is provided, with which the honeycomb layer 23 is secured in the trough 22.
  • the honeycomb layer 23 has a ridge height 28 which is greater than the depth of the trough 22. This results in the honeycomb layer 23, a projection 29 which projects from the parting surface 20.
  • the in the assembled state of the housing intermediate bottom 13 of the parting surface 20 of the lower half 17 facing parting surface 21 of the upper half 18 has a trough 30, the edge of which runs parallel to the border of the trough 22.
  • the trough 30 tends to be larger in its extent along the parting surface 21 than the trough 22, so that the trough 30 completely covers the trough 22. Thereby, it is prevented that the honeycomb layer 23, which is arranged in the trough 22, comes into contact with the edge of the trough 30 and the parting surface 20.
  • a spray layer 31 is provided, which completely fills the trough 30.
  • the depth of the trough 30 results in a layer thickness 32, which is formed due to production either equal to the supernatant 29 or greater.
  • the upper half 18 When mounting the housing intermediate bottom 13, the upper half 18 is set with its parting surface 21 on the parting surface 20 of the lower half 17, wherein the troughs 22 and 30 come to cover. Due to the supernatant 29 of the honeycomb layer 23 provided on the trough 22, this wears into the sprayed layer 31. As a result, a dense and stable configuration is created in the parting line 19 with the honeycomb layer 23 and the sprayed layer 31.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (11)

  1. Fond intermédiaire de carcasse pour une turbomachine ( 1 ), comprenant un joint ( 19 ) où le fond ( 13, 14 ) intermédiaire de carcasse peut, au montage et/ou au démontage, être mis dans la turbomachine (1) et/ou être sorti de la turbomachine ( 1 ) et qui est formé d'au moins deux surfaces ( 20, 21 ) de joint se recouvrant l'une l'autre sur des parties ( 17, 18 ) tournées l'une vers l'autre du fond ( 13, 14 ) intermédiaire de carcasse,
    caractérisé en ce que
    dans la partie du recouvrement est prévue, dans au moins l'une des surfaces ( 20, 21 ) de joint, une cavité ( 22, 30 ) dans laquelle est logé un revêtement ( 23, 31 ) qui, lorsque le fond (13, 14) intermédiaire de carcasse est à l'état démonté, état dans lequel le fond ( 13, 14 ) intermédiaire de carcasse est séparé sur le joint ( 19 ), dépasse de l'une des surfaces ( 20, 21 ) de joint sous la forme d'une partie ( 29 ) saillante de sorte que, lorsque le fond ( 13, 14 ) intermédiaire de carcasse est à l'état monté, le revêtement ( 22, 30 ) s'applique à l'autre surface ( 20, 21 ) du joint tournée vers la une surface ( 20, 21 ) du joint, grâce à quoi le joint ( 19 ) est rendu étanche, dans lequel il est prévu dans la partie du recouvrement dans la une surface ( 21 ) du joint la une cavité ( 22 ) et dans l'autre surface ( 21 ) du joint l'autre cavité ( 30 ), dans lesquelles est logé respectivement l'un des revêtements ( 23, 30 ), les revêtements ( 23, 30 ) se chevauchant l'un l'autre.
  2. Fond intermédiaire de carcasse suivant la revendication 1, dans lequel le revêtement est une couche ( 23 ) en nid d'abeilles.
  3. Fond intermédiaire de carcasse suivant la revendication 2, dans lequel la couche ( 23 ) en nid d'abeilles est brasée dans la cavité ( 22 ).
  4. Fond intermédiaire de carcasse suivant l'une des revendications 1 à 3, dans lequel le revêtement est une couche ( 30 ) projetée à la flamme ou au plasma.
  5. Fond intermédiaire de carcasse suivant la revendication 4, dans lequel la couche ( 30 ) projetée est à base de Ni-Ar-Cr.
  6. Fond intermédiaire de carcasse suivant la revendication 1, dans lequel le revêtement de l'une des surfaces ( 20 ) de joint est la couche ( 23 ) en nid d'abeilles et le revêtement de l'autre surface ( 21 ) de joint est la couche ( 30 ) projetée.
  7. Fond intermédiaire de carcasse suivant la revendication 6, dans lequel l'épaisseur ( 32 ) de la couche ( 30 ) projetée de l'autre surface ( 21 ) de joint a des dimensions au moins aussi grandes que la partie ( 29 ) en saillie de la couche ( 23 ) en nid d'abeilles de manière à ce que, lorsque le fond ( 13, 14 ) intermédiaire de carcasse est à l'état monté, la couche ( 23 ) en nid d'abeilles soit imprimé dans la couche ( 30 ) projetée.
  8. Fond intermédiaire de carcasse suivant l'une des revendications 1 à 7, dans lequel le fond ( 13, 14 ) intermédiaire de carcasse est formé d'une moitié ( 17 ) inférieure et d'une moitié ( 18 ) supérieure qui forment, à l'état de montage, le joint ( 19 ) dans un plan dans lequel se trouve l'axe ( 24 ) de rotation de la turbomachine ( 1 ).
  9. Fond intermédiaire de carcasse suivant la revendication 8, dans lequel il est prévu, sur la moitié ( 17 ) inférieure, la une surface ( 20 ) de joint ayant la couche ( 23 ) en nid d'abeilles, et, sur la moitié ( 18 ) supérieure, l'autre surface ( 21 ) de joint ayant la couche ( 31 ) projetée.
  10. Turbomachine ayant un fond ( 13, 14 ) intermédiaire de carcasse suivant l'une des revendications 1 à 9.
  11. Turbomachine suivant la revendication 10, la turbomachine étant un turbocompresseur ( 1 ) radial qui a un étage ( 8 ) de turbocompresseur radial ayant un diffuseur ( 10 ) annulaire, un conduit ( 11 ) de déviation et un conduit ( 12 ) de retour, qui sont formés par au moins deux fonds ( 13, 14 ) intermédiaires de carcasse.
EP09782156.5A 2008-09-03 2009-08-25 Fond intermédiaire de carter pour une turbomachine Not-in-force EP2321534B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102008045669 2008-09-03
PCT/EP2009/060922 WO2010026077A1 (fr) 2008-09-03 2009-08-25 Fond intermédiaire de carter pour une turbomachine

Publications (2)

Publication Number Publication Date
EP2321534A1 EP2321534A1 (fr) 2011-05-18
EP2321534B1 true EP2321534B1 (fr) 2016-11-16

Family

ID=41165166

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09782156.5A Not-in-force EP2321534B1 (fr) 2008-09-03 2009-08-25 Fond intermédiaire de carter pour une turbomachine

Country Status (4)

Country Link
US (1) US8142151B2 (fr)
EP (1) EP2321534B1 (fr)
CN (1) CN102144098B (fr)
WO (1) WO2010026077A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2623730A1 (fr) 2012-02-02 2013-08-07 Siemens Aktiengesellschaft Composant de turbomachine doté d'un joint de séparation et turbine à vapeur dotée du composant de turbomachine
JP6963471B2 (ja) * 2017-11-09 2021-11-10 三菱重工コンプレッサ株式会社 回転機械
FR3096728B1 (fr) * 2019-05-29 2022-01-28 Thermodyn Cartouche de compresseur, motocompresseur et procédé d’assemblage d’un tel motocompresseur

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB168772A (en) 1920-08-19 1921-09-15 Gen Electric Improvements in and relating to centrifugal compressors and the like
US3390830A (en) 1967-04-14 1968-07-02 Kahane Wilhelm Sealing of horizontally-split centrifugal compressors
DE2542336C3 (de) 1975-09-23 1978-06-15 Igor Martynovitsch Kalnin Mehrstufiger Radialverdichter
SU732556A1 (ru) * 1978-07-18 1980-05-05 Ордена Ленина И Ордена Трудового Красного Знамени Производственное Объединение "Невский Завод" Им. В.И.Ленина Статор турбомашины с горизонтальным разъемом
CH676487A5 (fr) * 1988-10-19 1991-01-31 Proizv Ob Nevsky Z Im V I
CN1042758A (zh) * 1988-11-18 1990-06-06 列宁联合企业涅弗斯克工厂 具有水平拆装面的离心式压缩机
CN2075700U (zh) * 1989-07-14 1991-04-24 徐晓强 一种高效燃气轮机
JP3294491B2 (ja) 1995-12-20 2002-06-24 株式会社日立製作所 内燃機関の過給機
ITMI20011348A1 (it) * 2001-06-27 2002-12-27 Nuovo Pignone Spa Pistone di bilanciamento per compressori centrifughi con tenuta a cellette a gioco divergente
ITMI20032149A1 (it) * 2003-11-07 2005-05-08 Nuovo Pignone Spa Compressore centrifugo multistadio con cassa apribile orizzontalmente

Also Published As

Publication number Publication date
US20110158794A1 (en) 2011-06-30
CN102144098A (zh) 2011-08-03
EP2321534A1 (fr) 2011-05-18
WO2010026077A1 (fr) 2010-03-11
US8142151B2 (en) 2012-03-27
CN102144098B (zh) 2013-08-28

Similar Documents

Publication Publication Date Title
EP2886961B1 (fr) Rondelle de bardeaux de chambre de combustion d'une turbine à gaz
EP2414641B1 (fr) Rotor de turbomachine axiale doté d'un disque d'étanchéité
EP2647795B1 (fr) Système d'étanchéité pour turbomachine
EP3369996B1 (fr) Dispositif formant bardeau de la chambre de combustion d'une turbine à gaz
EP2478186B1 (fr) Rotor de turbomachine
EP2808559B1 (fr) Ensemble structurel pour une turbomachine
EP3273001B1 (fr) Procédé de fabrication d'un élément d'aube en tandem
EP2993356A1 (fr) Étage de compresseur radial
EP2321534B1 (fr) Fond intermédiaire de carter pour une turbomachine
EP2411631B1 (fr) Plaque d'étanchéité et système d'aube tournante
DE102019210699A1 (de) Zwischenelement für eine Schaufel-Rotorscheiben-Verbindung bei einem Rotor einer Strömungsmaschine und Rotor für eine Strömungsmaschine
EP1995413B1 (fr) Joint d'étanchéité pour le jeu d'aubes d'une turbomachine
EP2232080B1 (fr) Rotor de pompe
EP2218918A1 (fr) Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites
EP2526263B1 (fr) Système de boîtier pour une turbomachine axiale
EP3236011A1 (fr) Rotor comprenant un porte à faux sur les pales pour un élément de sécurité
EP2808557A1 (fr) Ensemble structurel pour une turbomachine
DE102018210600A1 (de) Mantelringanordnung für eine strömungsmaschine
EP3159487B1 (fr) Stator d'une turbine à gaz ayant un guidage d'air de refroidissement amélioré
EP2871418B1 (fr) Chambre de combustion d'une turbine à gaz et son procédé de fabrication
WO2019137804A1 (fr) Carter intérieur de turboréacteur
EP2980481A1 (fr) Turbine à gaz d'avion avec un joint d'étanchéité pour l'étanchéificiation d'une bougie d'allumage au niveau de la paroi de la chambre de combustion d'une turbine à gaz
EP3935283B1 (fr) Soufflante de canal latéral
EP2811117A2 (fr) Anneau de renforcement pour une turbomachine
EP3536913B1 (fr) Bague intérieure pour une turbomachine et procédé de fabrication de cette bague intérieure

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: 20110216

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): 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 SE SI SK SM TR

AX Request for extension of the european patent

Extension state: AL BA RS

DAX Request for extension of the european patent (deleted)
RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/08 20060101ALI20160512BHEP

Ipc: F04D 29/62 20060101ALI20160512BHEP

Ipc: F04D 29/42 20060101ALI20160512BHEP

Ipc: F04D 17/12 20060101ALI20160512BHEP

Ipc: F04D 29/44 20060101ALI20160512BHEP

Ipc: F04D 29/16 20060101ALI20160512BHEP

Ipc: F04D 1/06 20060101AFI20160512BHEP

INTG Intention to grant announced

Effective date: 20160608

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): 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 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: 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: 846221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20161215

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 502009013383

Country of ref document: DE

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: 20161116

REG Reference to a national code

Ref country code: NL

Ref legal event code: MP

Effective date: 20161116

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: 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: 20161116

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: 20170216

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: 20170217

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: 20161116

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: 20161116

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

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: 20170316

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: 20161116

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: 20161116

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: 20161116

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: 20161116

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: 20161116

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: 20161116

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: 20161116

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: 20161116

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: 20161116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502009013383

Country of ref document: DE

RAP2 Party data changed (patent owner data changed or rights of a patent transferred)

Owner name: SIEMENS AKTIENGESELLSCHAFT

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: 20161116

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: 20161116

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: 20170216

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

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG, CH

Ref country code: CH

Ref legal event code: PCOW

Free format text: NEW ADDRESS: WERNER-VON-SIEMENS-STRASSE 1, 80333 MUENCHEN (DE)

26N No opposition filed

Effective date: 20170817

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

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: 20161116

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502009013383

Country of ref document: DE

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

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: 20161116

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20170825

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

Ref country code: CH

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

Effective date: 20170831

Ref country code: LI

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

Effective date: 20170831

REG Reference to a national code

Ref country code: BE

Ref legal event code: MM

Effective date: 20170831

REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20180430

REG Reference to a national code

Ref country code: IE

Ref legal event code: MM4A

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: 20170825

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

Ref country code: GB

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

Effective date: 20170825

Ref country code: IE

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

Effective date: 20170825

Ref country code: DE

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

Effective date: 20180301

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

Ref country code: FR

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

Effective date: 20170831

Ref country code: BE

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

Effective date: 20170831

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: 20161116

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 846221

Country of ref document: AT

Kind code of ref document: T

Effective date: 20170825

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: 20170825

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: 20090825

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 NON-PAYMENT OF DUE FEES

Effective date: 20161116

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: 20161116

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: 20161116

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

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: 20170316