EP2179222B1 - Brûleur pour une chambre de combustion d'un turbogroupe - Google Patents

Brûleur pour une chambre de combustion d'un turbogroupe Download PDF

Info

Publication number
EP2179222B1
EP2179222B1 EP08775142.6A EP08775142A EP2179222B1 EP 2179222 B1 EP2179222 B1 EP 2179222B1 EP 08775142 A EP08775142 A EP 08775142A EP 2179222 B1 EP2179222 B1 EP 2179222B1
Authority
EP
European Patent Office
Prior art keywords
burner
lance
interior
outlet opening
passage
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.)
Active
Application number
EP08775142.6A
Other languages
German (de)
English (en)
Other versions
EP2179222A2 (fr
EP2179222B2 (fr
Inventor
Jaan Hellat
Adnan Eroglu
Jan Cerny
Douglas Anthony Pennell
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Alstom Technology 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
Family has litigation
First worldwide family litigation filed litigation Critical https://patents.darts-ip.com/?family=39865130&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP2179222(B1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2179222A2 publication Critical patent/EP2179222A2/fr
Publication of EP2179222B1 publication Critical patent/EP2179222B1/fr
Application granted granted Critical
Publication of EP2179222B2 publication Critical patent/EP2179222B2/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/00015—Pilot burners specially adapted for low load or transient conditions, e.g. for increasing stability

Definitions

  • the present invention relates to a burner for a combustion chamber of a turbo group, in particular in a power plant, according to the preamble of claim 1.
  • the DE 103 45 137 A1 shows an intended for gas turbines injection device, which is designed in the manner of a lance and cantilevered into a burner. At the free end of the lance axial discharge openings for fuel and air are provided, such that a sheathed by a Ableluftstrom fuel jet is generated. To control the quantity ratio between fuel and shielding air is provided to exploit the temperature changes occurring at the injector. In this way, an automatic adaptation to different operating states is to be achieved in such a way that an optimal operation is maintained all the time.
  • this document can be taken from the reference that it is known to provide aerodynamic methods for flame stabilization, reference being made to swirl flows. It is emphasized that the entire flow in spin-stabilized burners is extremely sensitive to changes in the flow field.
  • a gas turbine fuel injector is known.
  • the injector has a rod-like end piece, which is arranged at the head of a vortex chamber substantially coaxially to the longitudinal axis of this chamber.
  • This vortex chamber opens on the output side into a combustion chamber.
  • the aforementioned end piece of the injector on the one hand has axial outlet openings through which fuel can be ejected as a liquid jet, on the other hand discharge openings are provided, via which the fuel can be ejected as a vaporising liquid jet.
  • the EP 0 704 657 A2 relates to a burner for gas turbines or the like.
  • This burner consists upstream of a swirl generator and an axially subsequent mixing section, wherein at the beginning of a mixing tube, a special transition geometry is provided, such that the mixing tube is penetrated by a swirl flow.
  • On the outflow side of the transition geometry are placed in the wall of the mixing section filing holes, which cause an increase in the flow velocity along the pipe wall.
  • the mixing section opens into a combustion chamber in which a backflow zone is formed in the region of a cross-sectional jump between the mixing section and the combustion chamber, which zone is intended to act as a flame holder.
  • a central fuel nozzle for injecting a particular liquid fuel is arranged in the swirl generator.
  • the DE 10 2005 015 152 A1 relates to a premix burner for a gas turbine combustor.
  • This burner comprises an oxidizer feed device for feeding a gaseous oxidizer into a mixing space to which gaseous fuel is fed by means of a gas fuel feed device and liquid fuel is fed by means of a liquid fuel feed device.
  • the liquid fuel supply device has a plurality of injection holes communicating with a main supply line, which are configured so that the spray jet generated has a component radially to a main outflow direction of the burner.
  • the invention as characterized in the claims deals with the problem for a burner of in EP 704657 mentioned type to provide an improved embodiment, which is characterized in particular by an increased stability of the combustion process in the combustion chamber.
  • the invention is based on the general idea to design the lance much longer, so that it can protrude deeper in the direction of the outlet opening into the burner interior.
  • the knowledge is used that a velocity profile is formed in the mixer for the mixture flow, which has significantly higher velocities in the center than in the edge region.
  • the speed in the center can be reduced, while at the same time the flow velocity in the edge regions increases.
  • the increased flow velocity in the edge region effectively counteracts flashback.
  • the targeted, in the direction of the outlet opening displaced positioning of the lance can also be achieved that a flame front, which arises during operation of the combustion chamber by the combustion reaction, at least partially into the burner interior protrudes.
  • the stationary flame front can partially extend within the burner interior.
  • the targeted introduction of fuel into the flame front can be improved with the help of the lance, since the distance between the free-standing lance end and the flame front is reduced.
  • the interaction between a plurality of burners of the combustion chamber is reduced via the combustion chamber, since the part of the flame front projecting into the respective burner interior is comparatively independent of the other burners with respect to the respective burner and thus stable.
  • the proposed construction thus makes it possible, in particular, to transfer results from test bench installations which only work with one burner to industrial installations in which the combustion chamber has a plurality of burners.
  • the lance has a plurality of concentrically arranged tubes, for example a central inner tube, which contains a central channel for liquid fuel and at least one axial outlet opening at the end of the lance.
  • a hollow-walled outer tube may be provided, which encloses the inner tube to form an inner annular channel and contains in its hollow wall at least one outer channel for gaseous fuel.
  • the inner ring channel ends axially open at the end of the lance and serves to guide air. Due to the proposed construction with concentric pipes, on the one hand, liquid fuel and, on the other hand, gaseous fuel can be supplied alternately or simultaneously via the lance. At the same time allows the air flow through the annular channel cooling the lance.
  • the air duct through the inner annular channel rinses the central channel or the at least one outer channel dispensable if only gaseous or only liquid fuel is supplied via the lance.
  • air inside the burner media separation between liquid fuel and gaseous fuel can be achieved at least to the flame front. This can be advantageous for realizing a stable combustion reaction.
  • a burner 1 comprises a swirl generator 2, a mixer 3 and a lance 4.
  • the burner 1 forms in the assembled state a component of a combustion chamber of a turbo group, not shown here otherwise, which is arranged in particular in a power plant.
  • the swirl generator 2 encloses an input-side section of a burner interior 5 and has at least one air inlet 6, which extends tangentially with respect to a longitudinal central axis 7 of the burner 1.
  • the swirl generator 2 is configured conical.
  • the respective air inlet 6 forms a longitudinal slot along the cone sheath.
  • a plurality of such air inlets 6 are arranged distributed in the circumferential direction. As a result, the air can penetrate tangentially into the burner interior 5, whereby it is acted upon by a twist.
  • the swirl generator 2 also has a fuel inlet 8, via which gaseous fuel can be introduced into the burner interior 5.
  • this fuel inlet 8 consists of several, along the generatrix of the conical swirl generator 2 extending rows of individual inlet openings through which the fuel gas can enter the burner interior 5.
  • the fuel inlet 8 may be aligned tangentially to increase the swirl effect.
  • the fuel inlet 8 may generate some radial component to enhance mixing with the air.
  • the mixer 3 encloses an output-side section of the burner interior 5 and has an outlet opening 9, which is open to a combustion chamber 10 of the combustion chamber.
  • the mixer 3 comprises, for example, a tubular body 11, which is connected via a tubular transition piece 12 to the swirl generator 2 and which carries an outlet flange 13 with the outlet opening 9.
  • the burner 1 can be connected to the combustion chamber.
  • the mixer 3 is cylindrically shaped.
  • the lance 4 is used for introducing pilot fuel into the combustion chamber 10.
  • the lance 4 is arranged coaxially to the longitudinal central axis 7.
  • the lance 4 extends into the burner interior 5 from a burner head 14, which essentially forms the tip of the conical swirl generator 2.
  • the lance 4 thus starts from the burner head 14 and ends with a lance end 15 freestanding in a portion of the burner interior 5 enclosed by the mixer 3 at a distance 17 from the outlet opening 9 which is greater than 25% and less than 50% of the distance 18, has an outlet-side end 19 of the swirl generator 2 from the outlet opening 9.
  • a portion of a flame front 16 is shown, which forms during operation of the combustion chamber through the running in the combustion chamber 10 combustion reaction.
  • part of this flame front 16 projects into the burner interior 5, specifically into an end section of the burner interior 5, which is enclosed by an outlet-side end region of the mixer 3.
  • the flame front 16 remains within the section of the burner interior 5 enclosed by the outlet flange 13.
  • Such a course of the flame front 16, in which a part of the flame front 16 passes through the outlet opening 9 into the interior Burner interior 5 projects, is achieved by a special configuration and / or arrangement of the lance 4.
  • the lance 4 extends with its free-standing end 15 comparatively far into the burner interior 5, namely to the extent that a part of the flame front 16 extends into the burner interior 5 inside.
  • the lance 4 can protrude so deep into the burner interior 5 in the direction of the outlet opening 9, the lance 4 must be designed accordingly so that it has the necessary axial length for this purpose.
  • the lance 4 is positioned in the burner 1 so that its free-standing end 15 is located in a section of the burner interior 5 enclosed by the mixer 3. In other words, the lance 4 extends into the mixer 3.
  • the lance 4 extends with its free-standing end 15 in the axial direction to about half of the mixer 3 or even beyond in the mixer 3 into it.
  • Fig. 2 is the registered distance 17, which has the free-standing lance end 15 of the outlet opening 9, greater than 25% and less than 50% of the distance 18, the outlet-side end 19 of the swirl generator 2 from the outlet opening 9 has.
  • Fig. 2 can be arranged on the burner head 14, an inlet tube 20 which extends coaxially with the lance 4.
  • This inlet tube 20 protrudes in the axial direction into a section of the burner interior 5 enclosed by the swirl generator 2.
  • This inlet pipe 20 may form an annular inlet channel 21 for liquid fuel.
  • the inlet channel 21 has at least one axially oriented outlet opening 22.
  • the liquid fuel can enter the burner interior 5 substantially in the axial direction, as indicated by arrows 48.
  • the burner 1 can thus be operated with fuel gas and / or with liquid fuel.
  • a plurality of such axial outlet openings 22 are arranged at the end of the inlet tube 20 ending in the burner interior 5.
  • the lance 4 may be arranged in the axial direction adjustable on the burner head 14.
  • the axial position of the free-standing lance end 15 within the burner interior 5 is adjustable.
  • this allows the position of the part of the flame front 16 projecting into the burner interior 5 to be adjusted.
  • the burner 1 can be adapted to operating parameters of the combustion chamber, which allows stabilization of the combustion process.
  • the lance 4 can thus be retracted more or less deep into the burner interior 5, depending on demand, or extend more or less far out of the burner interior 5.
  • Fig. 3 shows a situation in which the lance 4 is largely extended from the burner interior 5.
  • the lance end 15 expediently ends at the inside of the burner head 14 facing the burner interior 5 Fig. 3
  • the lance 4 is fully extended. It can be retracted according to an arrow 23 back into the burner interior 5.
  • the flame front 16 is arranged completely outside the burner interior 5 and is located downstream of the outlet opening 9 with respect to the flow direction of the burner 1.
  • a velocity profile 24 is shown, which represents the distribution of the flow velocity along the cross section of the burner 1 within the mixer 3. Visible, the flow has a significant maximum in the absence of lance 4 in the center.
  • the flow velocity in the center of the cross section of the mixer 3 is inevitably reduced.
  • the speed is correspondingly increased outside the lance 4, ie in the edge region of the cross section, in order to ensure a constant volume flow.
  • the reduction of central flow velocity allows the flame front 16 to travel upstream. With appropriate positioning and design of the lance 4, the flame front 16 protrudes partially into the burner interior 5, as in Fig. 1 is shown.
  • the lance 4 is also shown cut.
  • the following detailed description of the lance 4 applies in particular to the embodiments of the Fig. 1 to 3 ,
  • the lance 4 has a plurality of concentrically arranged tubes, namely a central inner tube 25 and an outer tube 26.
  • the inner tube 25 includes a central channel 27 and has at least the free-standing lance end 15 arranged axially oriented outlet opening 28.
  • the central channel 27 is used to supply liquid fuel to at least one outlet opening 28.
  • the inner tube 25 is provided in the region of the outlet opening 28 with a nozzle-shaped cross-sectional constriction 29, which allows the formation of an intense liquid jet.
  • This liquid fuel jet is in the Fig. 4 and 5 indicated by an arrow 32.
  • the outer tube 26 is sized so that it surrounds the inner tube 25 to form an inner annular channel 30.
  • This inner annular channel 30 is axially open at the end of the lance 15 and thus opens into the burner interior 5.
  • the inner annular channel 30 serves to guide air, which can emerge from the inner annular channel 30 in the axial direction according to an arrow 31.
  • the outer tube 26 is hollow-walled, that is, the outer tube 26 has a hollow wall 33 with an inner wall 34 and a radially spaced outer wall 35.
  • the outer tube 26 includes at least one outer channel 36 (FIGS. Fig. 4 ) or 37 ( Fig. 5 ).
  • This at least one outer channel 36, 37 serves to supply gaseous fuel.
  • the outer channel 36, 37 may be configured as an annular channel, which is simply formed between the two walls 34, 35 of the wall 33.
  • This outer annular channel 36 or 37 can according to Fig. 4 have at least one axially oriented outlet opening 38 at the lance end 15, whereby a substantially axially oriented injection of fuel gas according to an arrow 39 can be achieved.
  • a lance end portion 40, having a brace, having the free-standing lance end 15, may be an array of a plurality of radial exit openings 41. These radial outlet openings 41 are preferably formed in the outer wall 35 of the hollow wall 33 of the outer tube 26.
  • a corresponding control may be provided which, for example, operates with a sleeve-shaped control element which lies in a first position in front of the radial outlet openings 41. while it locks in a second position, the at least one axial outlet opening 38.
  • a plurality of circumferentially distributed axial outlet openings 38 are arranged at the axial end of the outer tube 26.
  • first outer channel 36 may be formed, which at the lance end 15 to the at least one axial outlet opening 38 leads.
  • at least one second outer channel 37 may be formed in the hollow wall 33, which leads to at least one of the radial outlet openings 41 formed in the lance end section 40.
  • Fig. 4 shows, for example, a section through the first outer channels 36, while Fig. 5 a section through the second outer channels 37 shows.
  • the first and second outer channels 36, 37 may be connected on the input side to various, independently operable supply devices or control devices.
  • the inner tube 25 projects axially beyond the outer tube 26. In this way, a certain separation of media during operation of the lance 4 for injecting the liquid fuel and for injecting the fuel gas can be achieved. This media separation can also be assisted by the injected air 31.
  • the inlet pipe 20 arranged at the burner head 14 is hollow-walled, so that it has a hollow wall 43 with an inner wall 44 and an outer wall 45.
  • the hollow-walled inlet tube 20 is here also dimensioned so that it encloses the lance 4 and the outer tube 26 to form an axially open annular channel 46. Through this annular channel 46 47 air can be injected into the burner interior according to an arrow. In this way, an effective cooling of the lance in the region of the burner head 14 can be achieved.
  • the inlet channel 21 corresponding to the introduction of the liquid fuel Arrows 48 is used, is formed in the hollow wall 43 and may also be configured in particular ring-shaped.
  • a wall 49 of the mixer 3 is provided with a film cooling 50.
  • a film cooling 50 is realized for example by means of a plurality of cooling holes 51 which pass through the corresponding wall 49 and can be flowed through by coolant, which applies to the side of the wall 49 facing the burner interior 5 and thereby generates a cooling film protecting the wall 49.
  • coolant is usually air.
  • the cooling holes 51 may be set in the main flow direction of the burner 1 as shown here to enhance the formation of a cooling film.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)

Claims (9)

  1. Brûleur pour une chambre de combustion d'un turbogroupe, comprenant au moins un générateur de tourbillon (2), un mélangeur (3) et un dispositif d'injection de carburant sous la forme d'une lance (4), qui introduit de l'air et des carburants à l'intérieur (5) d'un brûleur en vue d'une réaction de combustion se produisant dans une chambre de combustion (10), dans lequel le générateur de tourbillon (2), qui entoure côté admission l'intérieur de brûleur (5), présente au moins une admission d'air (6) tangentielle par rapport à un axe central longitudinal (7), et le mélangeur (3), qui entoure côté sortie l'intérieur de brûleur (5), présente une ouverture de sortie ouverte vers la chambre de combustion (10), et la lance (4) disposée coaxialement à l'axe central longitudinal (7) s'étend à partir d'une tête de brûleur (14) dans l'intérieur de brûleur (5) pour l'introduction de carburant pilote pendant un fonctionnement pilote du brûleur (1), caractérisé en ce que la lance (4) s'étend, au moins pendant le fonctionnement pilote du brûleur (1), dans l'intérieur de brûleur (5) à un point tel qu'un front de flamme (16) de la réaction de combustion se produisant dans la chambre de combustion (10) s'étende au moins en partie jusque dans une partie d'extrémité de l'intérieur de brûleur (5) entourée par une zone d'extrémité côté sortie du mélangeur (3), du fait que la lance (4) est disposée avec son extrémité côté sortie (15), au moins pendant le fonctionnement pilote du brûleur (1), dans une partie de l'intérieur de brûleur (5) entourée par le mélangeur (3) et qu'une distance (17) de l'extrémité de la lance (15) à l'ouverture de sortie (9) est supérieure à 25 % et inférieure à 50 % de la distance (18), qu'une extrémité côté sortie (19) du générateur de tourbillon (2) présente par rapport à l'ouverture de sortie (9).
  2. Brûleur selon la revendication 1, caractérisé en ce que la lance (4) est disposée de façon réglable en longueur sur la tête de brûleur (14), de telle manière qu'elle puisse, en fonction des besoins, être introduite plus ou moins profondément dans l'intérieur de brûleur (5) ou retirée plus ou moins largement hors de celui-ci.
  3. Brûleur selon la revendication 1 ou 2, caractérisé en ce qu'un tube d'admission (20) est disposé sur la tête de brûleur (14), lequel pénètre coaxialement à la lance (4) dans la partie de l'intérieur de brûleur (5) entourée par le générateur de tourbillon (2) et forme un canal d'admission annulaire (21) pour un carburant liquide, qui présente au moins une ouverture de sortie axiale (22).
  4. Brûleur selon la revendication 3, caractérisé en ce que le tube d'admission (20) est réalisé à paroi creuse, en ce que le tube d'admission (20) entoure la lance (4) en formant un canal annulaire axialement ouvert (46) pour l'air, et en ce que le canal d'admission (21) est formé dans la paroi creuse (43) du tube d'admission (20).
  5. Brûleur selon l'une quelconque des revendications 1 à 4, caractérisé en ce que la lance (4) comprend plusieurs tubes (25, 26) disposés de façon concentrique, en ce qu'un tube intérieur central (25) comporte un canal central (27) pour un carburant liquide et présente au moins une ouverture de sortie axiale (28) à l'extrémité (15) de la lance, en ce qu'un tube extérieur à paroi creuse (26) entoure le tube intérieur (25) en formant un canal annulaire intérieur (30) et comporte dans sa paroi creuse (33) au moins un canal extérieur (36, 37) pour un carburant gazeux, et en ce que le canal annulaire intérieur (30) se termine sous forme axialement ouverte à l'extrémité (15) de la lance et sert pour le guidage de l'air.
  6. Brûleur selon la revendication 5, caractérisé en ce que le canal extérieur (36, 37) est configuré en un canal annulaire dans la paroi creuse (33) du tube extérieur (26), lequel présente à l'extrémité (15) de la lance au moins une ouverture de sortie axiale (28) et/ou la partie d'extrémité de la lance (40) présentant l'extrémité (15) de la lance comporte plusieurs ouvertures de sortie radiales (41).
  7. Brûleur selon la revendication 5, caractérisé en ce qu'au moins un (premier) canal extérieur (36) est formé dans la paroi creuse (33) du tube extérieur (26), lequel présente à l'extrémité (15) de la lance au moins une ouverture de sortie axiale (28), et/ou en ce qu'au moins un (deuxième) canal extérieur (37) est formé dans la paroi creuse (33) du tube extérieur (26), lequel présente dans une partie d'extrémité de la lance (40) présentant l'extrémité (15) de la lance plusieurs ouvertures de sortie radiales (41).
  8. Brûleur selon l'une quelconque des revendications 5 à 7, caractérisé en ce que le tube intérieur (25) est saillant axialement au-delà du tube extérieur (26).
  9. Brûleur selon l'une quelconque des revendications 1 à 8, caractérisé en ce qu'une paroi (49) du mélangeur (3) est équipée d'un refroidissement par film (50).
EP08775142.6A 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe Active EP2179222B2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102007037289 2007-08-07
PCT/EP2008/059321 WO2009019113A2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe

Publications (3)

Publication Number Publication Date
EP2179222A2 EP2179222A2 (fr) 2010-04-28
EP2179222B1 true EP2179222B1 (fr) 2014-10-22
EP2179222B2 EP2179222B2 (fr) 2021-12-01

Family

ID=39865130

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08775142.6A Active EP2179222B2 (fr) 2007-08-07 2008-07-16 Brûleur pour une chambre de combustion d'un turbogroupe

Country Status (3)

Country Link
US (1) US8069671B2 (fr)
EP (1) EP2179222B2 (fr)
WO (1) WO2009019113A2 (fr)

Families Citing this family (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2225488B1 (fr) * 2007-11-27 2013-07-17 Alstom Technology Ltd Brûleur à prémélange pour une turbine à gaz
US8413446B2 (en) * 2008-12-10 2013-04-09 Caterpillar Inc. Fuel injector arrangement having porous premixing chamber
ES2400247T3 (es) * 2008-12-19 2013-04-08 Alstom Technology Ltd Quemador de una turbina de gas que tiene una configuración de lanza especial
US20100175380A1 (en) * 2009-01-13 2010-07-15 General Electric Company Traversing fuel nozzles in cap-less combustor assembly
EP2496883B1 (fr) 2009-11-07 2016-08-10 Alstom Technology Ltd Brûleur à prémélange pour chambre de combustion de turbine à gaz
WO2011054760A1 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système de refroidissement permettant d'accroître le rendement d'une turbine à gaz
EP2496882B1 (fr) * 2009-11-07 2018-03-28 Ansaldo Energia Switzerland AG Système d'injection pour brûleur de réchauffage avec lances à combustible
WO2011054739A2 (fr) 2009-11-07 2011-05-12 Alstom Technology Ltd Système d'injection pour brûleur de réchauffage
WO2013085411A1 (fr) * 2011-12-05 2013-06-13 General Electric Company Chambre de combustion multizones
US9016039B2 (en) * 2012-04-05 2015-04-28 General Electric Company Combustor and method for supplying fuel to a combustor
EP2685160B1 (fr) 2012-07-10 2018-02-21 Ansaldo Energia Switzerland AG Brûleur de prémélange du type multi-cônes destiné à une turbine à gaz
US8943834B2 (en) * 2012-11-20 2015-02-03 Niigata Power Systems Co., Ltd. Pre-mixing injector with bladeless swirler
US9441543B2 (en) * 2012-11-20 2016-09-13 Niigata Power Systems Co., Ltd. Gas turbine combustor including a premixing chamber having an inner diameter enlarging portion
EP3133342A1 (fr) * 2015-08-20 2017-02-22 Siemens Aktiengesellschaft Brûleur à double carburant prémélangé avec un composant d'injection éfilé de carburant liquide principal
EP3299720B1 (fr) 2016-09-22 2020-11-04 Ansaldo Energia IP UK Limited Ensemble avant de chambre de combustion pour turbine à gaz
US11175035B2 (en) 2016-10-10 2021-11-16 King Abdullah University Of Science And Technology Burners for conversion of methane to olefins, aromatics, and nanoparticles
US10907832B2 (en) 2018-06-08 2021-02-02 General Electric Company Pilot nozzle tips for extended lance of combustor burner
GB2585025A (en) * 2019-06-25 2020-12-30 Siemens Ag Combustor for a gas turbine
US11774093B2 (en) 2020-04-08 2023-10-03 General Electric Company Burner cooling structures
US20230332544A1 (en) * 2020-10-14 2023-10-19 King Abdullah University Of Science And Technology Adjustable fuel injector for flame dynamics control
US11692711B2 (en) 2021-08-13 2023-07-04 General Electric Company Pilot burner for combustor

Family Cites Families (31)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH672541A5 (fr) * 1986-12-11 1989-11-30 Bbc Brown Boveri & Cie
CH674561A5 (fr) * 1987-12-21 1990-06-15 Bbc Brown Boveri & Cie
JP2713627B2 (ja) * 1989-03-20 1998-02-16 株式会社日立製作所 ガスタービン燃焼器、これを備えているガスタービン設備、及びこの燃焼方法
US5408825A (en) * 1993-12-03 1995-04-25 Westinghouse Electric Corporation Dual fuel gas turbine combustor
DE4435266A1 (de) * 1994-10-01 1996-04-04 Abb Management Ag Brenner
US5943866A (en) * 1994-10-03 1999-08-31 General Electric Company Dynamically uncoupled low NOx combustor having multiple premixers with axial staging
DE4446842B4 (de) * 1994-12-27 2006-08-10 Alstom Verfahren und Vorrichtung zum Zuleiten eines gasförmigen Brennstoffs in einen Vormischbrenner
DE19510744A1 (de) * 1995-03-24 1996-09-26 Abb Management Ag Brennkammer mit Zweistufenverbrennung
DE19520291A1 (de) * 1995-06-02 1996-12-05 Abb Management Ag Brennkammer
DE19527453B4 (de) † 1995-07-27 2009-05-07 Alstom Vormischbrenner
DE19545310B4 (de) † 1995-12-05 2008-06-26 Alstom Vormischbrenner
DE19545309A1 (de) * 1995-12-05 1997-06-12 Asea Brown Boveri Vormischbrenner
DE19547913A1 (de) † 1995-12-21 1997-06-26 Abb Research Ltd Brenner für einen Wärmeerzeuger
DE19640198A1 (de) † 1996-09-30 1998-04-02 Abb Research Ltd Vormischbrenner
US5735466A (en) * 1996-12-20 1998-04-07 United Technologies Corporation Two stream tangential entry nozzle
JP3448190B2 (ja) * 1997-08-29 2003-09-16 三菱重工業株式会社 ガスタービンの燃焼器
JP4625609B2 (ja) † 2000-06-15 2011-02-02 アルストム テクノロジー リミテッド バーナーの運転方法と段階的予混合ガス噴射バーナー
DE10050248A1 (de) † 2000-10-11 2002-04-18 Alstom Switzerland Ltd Brenner
DE10051221A1 (de) † 2000-10-16 2002-07-11 Alstom Switzerland Ltd Brenner mit gestufter Brennstoff-Eindüsung
DE10104695B4 (de) † 2001-02-02 2014-11-20 Alstom Technology Ltd. Vormischbrenner für eine Gasturbine
DE10164099A1 (de) * 2001-12-24 2003-07-03 Alstom Switzerland Ltd Brenner mit gestufter Brennstoffeinspritzung
DE10205839B4 (de) * 2002-02-13 2011-08-11 Alstom Technology Ltd. Vormischbrenner zur Verminderung verbrennungsgetriebener Schwingungen in Verbrennungssystemen
DE10334228A1 (de) * 2002-08-19 2004-03-04 Alstom (Switzerland) Ltd. Verfahren zum Betrieb eines Vormischbrenners sowie Vorrichtung zur Durchführung des Verfahrens
US6786046B2 (en) * 2002-09-11 2004-09-07 Siemens Westinghouse Power Corporation Dual-mode nozzle assembly with passive tip cooling
US7284378B2 (en) * 2004-06-04 2007-10-23 General Electric Company Methods and apparatus for low emission gas turbine energy generation
DE10345137B4 (de) * 2003-09-29 2014-02-13 Alstom Technology Ltd. Verfahren zum Betrieb einer Brennstoffeinspritzvorrichtung sowie eine Brennstoffeinspritzvorrichtung zur Durchführung des Verfahrens
US6935117B2 (en) * 2003-10-23 2005-08-30 United Technologies Corporation Turbine engine fuel injector
MX2007004119A (es) * 2004-10-18 2007-06-20 Alstom Technology Ltd Quemador para turbina de gas.
DE102005015152A1 (de) * 2005-03-31 2006-10-05 Alstom Technology Ltd. Vormischbrenner für eine Gasturbinenbrennkammer
CN101365913A (zh) † 2005-11-04 2009-02-11 阿尔斯托姆科技有限公司 燃料喷管
US8127546B2 (en) * 2007-05-31 2012-03-06 Solar Turbines Inc. Turbine engine fuel injector with helmholtz resonators

Also Published As

Publication number Publication date
WO2009019113A3 (fr) 2009-06-11
US8069671B2 (en) 2011-12-06
US20100146983A1 (en) 2010-06-17
EP2179222A2 (fr) 2010-04-28
EP2179222B2 (fr) 2021-12-01
WO2009019113A2 (fr) 2009-02-12

Similar Documents

Publication Publication Date Title
EP2179222B1 (fr) Brûleur pour une chambre de combustion d'un turbogroupe
EP2116766B1 (fr) Brûleur avec lance à combustible
EP1802915B1 (fr) Bruleur pour turbine a gaz
EP1864056B1 (fr) Bruleur de premelange destine a une chambre de combustion de turbine a gaz
DE2143012C3 (de) Brenneranordnung bei einer Gasturbinen-Brennkammer
DE60007946T2 (de) Eine Brennkammer
EP2225488B1 (fr) Brûleur à prémélange pour une turbine à gaz
EP1714081B1 (fr) Systeme de bruleur de premelange pour faire fonctionner une chambre de combustion, et procede pour faire fonctionner une chambre de combustion
EP1456583B1 (fr) Procédé d'injection d'un mélange air/carburant dans une chambre de combustion
EP2220433B1 (fr) Procédé et dispositif pour la combustion d'hydrogène dans un brûleur à prémélange
EP3559551B1 (fr) Dispositif de mélange et tête de brûleur pour un brûleur à émission de nox réduite
EP0548396B1 (fr) Dispositif servant à mélanger deux composants gazeux et brûleur dans lequel ce dispositif est appliqué
EP1754002B1 (fr) Brûleur étagé à prémélange comprenant in injecteur de carburant liquide
EP3087323B1 (fr) Injecteur de combustible, brûleur avec un tel injecteur de combustible, et turbine à gaz munie dudit brûleur
DE2538512A1 (de) Brennkammer mit abgestuften vormischungsrohren
EP3198199A1 (fr) Tête de brûleur et turbine à gaz pourvue d'un tel brûleur
WO2007051705A1 (fr) Lance à combustible
EP0483554B1 (fr) Procédé pour la réduction au minimum des émissions de NOx dans une combustion
WO2009019114A2 (fr) Combustible pour une chambre de combustion d'un turbogroupe
DE19507088B4 (de) Vormischbrenner
EP3301370B1 (fr) Tête de brûleur, système de brûleur et utilisation du système de brûleur dans la chambre de combustion d'une turbine à gaz
DE19733768C2 (de) Brenngas-Einleitungsvorrichtung für einen Gas-Vormischbrenner
EP3250857B1 (fr) Agencement de brûleur
EP3301371A1 (fr) Système de chambre de combustion, utilisation d'un système de chambre de combustion pourvu d'une turbine racoordée et procédé de mise en oeuvre d'un processus de combustion
EP0866268B1 (fr) Procédé de fonctionnement d'un brûleur stabilisé par vortex et brûleur mettant en oeuvre le procédé

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: 20100201

AK Designated contracting states

Kind code of ref document: A2

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 MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA MK RS

RIN1 Information on inventor provided before grant (corrected)

Inventor name: HELLAT, JAAN

Inventor name: CERNY, JAN

Inventor name: PENNELL, DOUGLAS ANTHONY

Inventor name: EROGLU, ADNAN

DAX Request for extension of the european patent (deleted)
17Q First examination report despatched

Effective date: 20120926

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20140522

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 MT NL NO PL PT RO SE SI SK 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: AT

Ref legal event code: REF

Ref document number: 692841

Country of ref document: AT

Kind code of ref document: T

Effective date: 20141115

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: DE

Ref legal event code: R096

Ref document number: 502008012336

Country of ref document: DE

Effective date: 20141204

REG Reference to a national code

Ref country code: NL

Ref legal event code: VDEP

Effective date: 20141022

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: 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: 20150223

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: 20150222

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: 20150122

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: 20141022

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: 20141022

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: 20141022

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: 20141022

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

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: 20141022

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: 20141022

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: 20141022

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: 20150123

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: 20141022

Ref country code: CY

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

Effective date: 20141022

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 502008012336

Country of ref document: DE

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

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: 20141022

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: 20141022

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: 20141022

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: 20141022

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: 20141022

PLBI Opposition filed

Free format text: ORIGINAL CODE: 0009260

PLAX Notice of opposition and request to file observation + time limit sent

Free format text: ORIGINAL CODE: EPIDOSNOBS2

26 Opposition filed

Opponent name: SIEMENS AKTIENGESELLSCHAFT

Effective date: 20150721

PLAF Information modified related to communication of a notice of opposition and request to file observations + time limit

Free format text: ORIGINAL CODE: EPIDOSCOBS2

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: 20141022

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: 20141022

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

PLAF Information modified related to communication of a notice of opposition and request to file observations + time limit

Free format text: ORIGINAL CODE: EPIDOSCOBS2

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 FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20150716

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: CH

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

Effective date: 20150731

Ref country code: LI

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

Effective date: 20150731

PLBB Reply of patent proprietor to notice(s) of opposition received

Free format text: ORIGINAL CODE: EPIDOSNOBS3

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

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

Ref country code: IE

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

Effective date: 20150716

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008012336

Country of ref document: DE

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH, CH

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008012336

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: ALSTOM TECHNOLOGY LTD., BADEN, CH

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

Owner name: GENERAL ELECTRIC TECHNOLOGY GMBH

REG Reference to a national code

Ref country code: AT

Ref legal event code: MM01

Ref document number: 692841

Country of ref document: AT

Kind code of ref document: T

Effective date: 20150716

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: 20150716

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: 20141022

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

Owner name: ANSALDO ENERGIA IP UK LIMITED

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: 20080716

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: 20141022

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

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

Ref country code: BE

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

Effective date: 20150731

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: 20141022

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

REG Reference to a national code

Ref country code: DE

Ref legal event code: R081

Ref document number: 502008012336

Country of ref document: DE

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Free format text: FORMER OWNER: GENERAL ELECTRIC TECHNOLOGY GMBH, BADEN, CH

REG Reference to a national code

Ref country code: GB

Ref legal event code: 732E

Free format text: REGISTERED BETWEEN 20170824 AND 20170830

R26 Opposition filed (corrected)

Opponent name: SIEMENS AKTIENGESELLSCHAFT

Effective date: 20150721

REG Reference to a national code

Ref country code: FR

Ref legal event code: TP

Owner name: ANSALDO ENERGIA IP UK LIMITED, GB

Effective date: 20171221

APBM Appeal reference recorded

Free format text: ORIGINAL CODE: EPIDOSNREFNO

APBP Date of receipt of notice of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA2O

APAH Appeal reference modified

Free format text: ORIGINAL CODE: EPIDOSCREFNO

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

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

Effective date: 20180716

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: 20180716

Ref country code: FR

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

Effective date: 20180731

PLAB Opposition data, opponent's data or that of the opponent's representative modified

Free format text: ORIGINAL CODE: 0009299OPPO

R26 Opposition filed (corrected)

Opponent name: SIEMENS AKTIENGESELLSCHAFT

Effective date: 20150721

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

PUAH Patent maintained in amended form

Free format text: ORIGINAL CODE: 0009272

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

Free format text: STATUS: PATENT MAINTAINED AS AMENDED

27A Patent maintained in amended form

Effective date: 20211201

AK Designated contracting states

Kind code of ref document: B2

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 MT NL NO PL PT RO SE SI SK TR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R102

Ref document number: 502008012336

Country of ref document: DE

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

Ref country code: IT

Payment date: 20231228

Year of fee payment: 16

Ref country code: DE

Payment date: 20231214

Year of fee payment: 16

P01 Opt-out of the competence of the unified patent court (upc) registered

Effective date: 20240430