EP2025945A3 - Flow working machine with ring canal wall fitting - Google Patents

Flow working machine with ring canal wall fitting Download PDF

Info

Publication number
EP2025945A3
EP2025945A3 EP08013782.1A EP08013782A EP2025945A3 EP 2025945 A3 EP2025945 A3 EP 2025945A3 EP 08013782 A EP08013782 A EP 08013782A EP 2025945 A3 EP2025945 A3 EP 2025945A3
Authority
EP
European Patent Office
Prior art keywords
point
recess
blade tip
points
wall
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08013782.1A
Other languages
German (de)
French (fr)
Other versions
EP2025945B1 (en
EP2025945A2 (en
Inventor
Volker Gümmer
Marius Swoboda
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2025945A2 publication Critical patent/EP2025945A2/en
Publication of EP2025945A3 publication Critical patent/EP2025945A3/en
Application granted granted Critical
Publication of EP2025945B1 publication Critical patent/EP2025945B1/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
    • F04D29/526—Details of the casing section radially opposing blade tips
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/685—Inducing localised fluid recirculation in the stator-rotor interface

Landscapes

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

Abstract

Die Erfindung bezieht sich auf eine Strömungsarbeitsmaschine mit einem von einem Gehäuse (1) und einer rotierenden Welle (2) gebildeten Strömungspfad, in welchem Reihen von Rotorschaufeln (3) und Statorschaufeln (4) angeordnet sind, wobei in einem Spitzenbereich der Schaufeln (3, 4) in einer Ringkanalwandung des Gehäuses (1) und/oder der Welle (2) zumindest eine ringnutartige Ausnehmung (5) angeordnet ist, dadurch gekennzeichnet, dass der Querschnitt und die Lage der Ausnehmung (5) wie folgt definiert sind:
ein in Strömungsrichtung stromauf angeordneter Begrenzungspunkt (E) der Ausnehmung (5) weist einen Abstand e > 0 vor dem vorderen Schaufelspitzenpunkt (A) auf,
ein in Strömungsrichtung stromab angeordneter Begrenzungspunkt (F) der Ausnehmung (5) weist einen Abstand (f) zu dem vorderen Schaufelspitzenpunkt (A) auf,

wobei folgendes gilt: 0,5 L > f > 0,
wobei L als Abstand der Schaufelspitzenpunkte (A und B) definiert ist;
wobei die Wandung der Ausnehmung (5) einen Punkt (S) einschließt, welcher auf einer orthogonalen auf der Linie (AB) durch den Punkt (S) angeordnet ist,
wobei eine Gerade durch die Schaufelspitzenpunkte (A und B) und eine Tangente an die Wandung der Ausnehmung (5) mindestens in einem Punkt der in einem Meridianschnitt gegebenen Wandung der Ausnehmung (5) zwischen den Punkten (S) und (F) einen Winkel (beta) einschließen, der 15° ≤ beta ≤ 70° beträgt,
wobei alle Punkte in einer Meridianebene liegen, die durch eine Achsrichtung (x) der Achse (6) der Strömungsarbeitsmaschine und eine Radialrichtung (r) gebildet wird, und
wobei alle Abstände parallel zu einer einen vorderen Schaufelspitzenpunkt (A) und einen hinteren Schaufelspitzenpunkt (B) verbindenden Linie gemessen sind.

Figure imgaf001
The invention relates to a fluid flow machine with a flow path formed by a housing (1) and a rotating shaft (2), in which rows of rotor blades (3) and stator blades (4) are arranged, wherein in a tip region of the blades (3, 4) in an annular channel wall of the housing (1) and / or the shaft (2) at least one annular groove-like recess (5) is arranged, characterized in that the cross section and the position of the recess (5) are defined as follows:
a boundary point (E) of the recess (5) arranged upstream in the flow direction has a distance e> 0 in front of the front blade tip point (A),
a boundary point (F) of the recess (5) arranged downstream in the direction of flow has a distance (f) from the front blade tip point (A),

where: 0.5 L>f> 0,
where L is defined as the distance of the blade tip points (A and B);
the wall of the recess (5) enclosing a point (S) disposed on an orthogonal line (AB) through the point (S),
wherein a straight line through the blade tip points (A and B) and a tangent to the wall of the recess (5) at least at one point of the given in a meridian section wall of the recess (5) between the points (S) and (F) an angle ( beta) which is 15 ° ≤ beta ≤ 70 °,
wherein all points lie in a meridian plane formed by an axial direction (x) of the axis (6) of the fluid flow machine and a radial direction (r), and
wherein all distances are measured parallel to a line connecting a front blade tip point (A) and a rear blade tip point (B).
Figure imgaf001
EP08013782.1A 2007-08-10 2008-07-31 Flow working machine with ring canal wall fitting Expired - Fee Related EP2025945B1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007037924A DE102007037924A1 (en) 2007-08-10 2007-08-10 Turbomachine with Ringkanalwandausnehmung

Publications (3)

Publication Number Publication Date
EP2025945A2 EP2025945A2 (en) 2009-02-18
EP2025945A3 true EP2025945A3 (en) 2014-06-25
EP2025945B1 EP2025945B1 (en) 2016-04-20

Family

ID=39869927

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08013782.1A Expired - Fee Related EP2025945B1 (en) 2007-08-10 2008-07-31 Flow working machine with ring canal wall fitting

Country Status (3)

Country Link
US (1) US8419355B2 (en)
EP (1) EP2025945B1 (en)
DE (1) DE102007037924A1 (en)

Families Citing this family (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007056953B4 (en) * 2007-11-27 2015-10-22 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with Ringkanalwandausnehmung
FR2940374B1 (en) 2008-12-23 2015-02-20 Snecma COMPRESSOR HOUSING WITH OPTIMIZED CAVITIES.
DE102011107523B4 (en) * 2011-07-15 2016-08-11 MTU Aero Engines AG System for injecting a fluid, compressor and turbomachine
FR2989744B1 (en) 2012-04-19 2014-06-13 Snecma CAVITY COMPRESSOR HOUSING WITH OPTIMIZED SHAFT
FR2989742B1 (en) * 2012-04-19 2014-05-09 Snecma UPRIGHT CAVITY COMPRESSOR HOUSING OPTIMIZED
FR2989743B1 (en) * 2012-04-19 2015-08-14 Snecma COMPRESSOR HOUSING WITH CAVITIES OF VARIED LENGTHS
US20140093355A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Extended indentation for a fastener within an air flow
WO2014116842A1 (en) 2013-01-23 2014-07-31 Concepts Eti, Inc. Structures and methods for forcing coupling of flow fields of adjacent bladed elements of turbomachines, and turbomachines incorporating the same
WO2014158236A1 (en) * 2013-03-12 2014-10-02 United Technologies Corporation Cantilever stator with vortex initiation feature
US9644639B2 (en) * 2014-01-27 2017-05-09 Pratt & Whitney Canada Corp. Shroud treatment for a centrifugal compressor
CN106574636B (en) 2014-06-24 2021-08-24 概创机械设计有限责任公司 Flow control structure for turbomachine and design method thereof
EP3177811B1 (en) * 2014-08-08 2021-07-21 Siemens Energy Global GmbH & Co. KG Gas turbine engine compressor
US20160153465A1 (en) * 2014-12-01 2016-06-02 General Electric Company Axial compressor endwall treatment for controlling leakage flow therein
US10047620B2 (en) * 2014-12-16 2018-08-14 General Electric Company Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein
EP3037674A1 (en) * 2014-12-22 2016-06-29 Alstom Technology Ltd Engine and method for operating said engine
JP2016118165A (en) * 2014-12-22 2016-06-30 株式会社Ihi Axial flow machine and jet engine
CN108506249B (en) * 2018-04-02 2020-03-10 华能国际电力股份有限公司 Groove end wall processing method for axial flow compressor
DE102018116062A1 (en) * 2018-07-03 2020-01-09 Rolls-Royce Deutschland Ltd & Co Kg Structure assembly for a compressor of a turbomachine
US10914318B2 (en) * 2019-01-10 2021-02-09 General Electric Company Engine casing treatment for reducing circumferentially variable distortion
EP3734081A1 (en) * 2019-04-30 2020-11-04 Borgwarner Inc. Flow modification device for compressor
EP4193035A1 (en) 2020-08-07 2023-06-14 Concepts NREC, LLC Flow control structures for enhanced performance and turbomachines incorporating the same
CN112832878B (en) * 2020-12-31 2022-10-25 南昌航空大学 Unsteady casing processing structure for turbine leakage flow control
US20230151825A1 (en) * 2021-11-17 2023-05-18 Pratt & Whitney Canada Corp. Compressor shroud with swept grooves
FR3137940A1 (en) * 2022-07-15 2024-01-19 Safran Treatment of variable timing casing by co-axial multi-discs
US11970985B1 (en) 2023-08-16 2024-04-30 Rolls-Royce North American Technologies Inc. Adjustable air flow plenum with pivoting vanes for a fan of a gas turbine engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3521798A1 (en) * 1984-06-19 1992-08-27 Rolls Royce Plc AXIAL COMPRESSOR WITH PUMP PREVENTION MEASURES
DE69402843T2 (en) * 1993-03-11 1997-09-04 Central Inst Of Aviat Motors C SHOVEL TIP DEVICE TO PROTECT AGAINST FLOW RETURN
DE10330084A1 (en) * 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Recirculation structure for turbocompressors
GB2408546A (en) * 2003-11-25 2005-06-01 Rolls Royce Plc Compressor casing treatment slots

Family Cites Families (58)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE889506C (en) 1940-09-25 1953-09-10 Versuchsanstalt Fuer Luftfahrt Flow machine with boundary layer suction
GB619722A (en) 1946-12-20 1949-03-14 English Electric Co Ltd Improvements in and relating to boundary layer control in fluid conduits
US2933238A (en) * 1954-06-24 1960-04-19 Edward A Stalker Axial flow compressors incorporating boundary layer control
GB799675A (en) 1955-10-13 1958-08-13 Bristol Aeroengines Ltd Improvements in or relating to axial flow gas compressors and turbines
US3066912A (en) * 1961-03-28 1962-12-04 Gen Electric Turbine erosion protective device
CH437614A (en) 1963-07-02 1967-11-30 Moravec Zdenek Turbo machine with reduced noise generation
GB987625A (en) 1963-10-14 1965-03-31 Rolls Royce Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
US3572960A (en) * 1969-01-02 1971-03-30 Gen Electric Reduction of sound in gas turbine engines
DE1938132A1 (en) * 1969-07-26 1971-01-28 Daimler Benz Ag Guide vanes of axial compressors
FR2166494A5 (en) * 1971-12-27 1973-08-17 Onera (Off Nat Aerospatiale)
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
FR2248732A5 (en) * 1973-10-23 1975-05-16 Onera (Off Nat Aerospatiale)
US4155680A (en) * 1977-02-14 1979-05-22 General Electric Company Compressor protection means
GB2017228B (en) * 1977-07-14 1982-05-06 Pratt & Witney Aircraft Of Can Shroud for a turbine rotor
FR2491549B1 (en) * 1980-10-08 1985-07-05 Snecma DEVICE FOR COOLING A GAS TURBINE, BY TAKING AIR FROM THE COMPRESSOR
US4479755A (en) * 1982-04-22 1984-10-30 A/S Kongsberg Vapenfabrikk Compressor boundary layer bleeding system
DE3407945A1 (en) 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München METHOD AND MEANS FOR AVOIDING THE DEVELOPMENT OF TITANIUM FIRE
DE3407946A1 (en) * 1984-03-03 1985-09-05 MTU Motoren- und Turbinen-Union München GmbH, 8000 München DEVICE FOR PREVENTING THE SPREADING OF TITANIUM FIRE IN TURBO MACHINES, ESPECIALLY GAS TURBINE OR. GAS TURBINE JET ENGINES
GB2245312B (en) * 1984-06-19 1992-03-25 Rolls Royce Plc Axial flow compressor surge margin improvement
US5059093A (en) * 1990-06-07 1991-10-22 United Technologies Corporation Compressor bleed port
US5203162A (en) * 1990-09-12 1993-04-20 United Technologies Corporation Compressor bleed manifold for a gas turbine engine
JPH04132899A (en) * 1990-09-25 1992-05-07 Mitsubishi Heavy Ind Ltd Axial blower
EP0497574B1 (en) 1991-01-30 1995-09-20 United Technologies Corporation Fan case treatment
US5327716A (en) * 1992-06-10 1994-07-12 General Electric Company System and method for tailoring rotor tip bleed air
US5431533A (en) * 1993-10-15 1995-07-11 United Technologies Corporation Active vaned passage casing treatment
US5480284A (en) * 1993-12-20 1996-01-02 General Electric Company Self bleeding rotor blade
US5562404A (en) 1994-12-23 1996-10-08 United Technologies Corporation Vaned passage hub treatment for cantilever stator vanes
US5474417A (en) * 1994-12-29 1995-12-12 United Technologies Corporation Cast casing treatment for compressor blades
US5607284A (en) 1994-12-29 1997-03-04 United Technologies Corporation Baffled passage casing treatment for compressor blades
JP3816150B2 (en) * 1995-07-18 2006-08-30 株式会社荏原製作所 Centrifugal fluid machinery
US5762034A (en) * 1996-01-16 1998-06-09 Board Of Trustees Operating Michigan State University Cooling fan shroud
DE19632207A1 (en) * 1996-08-09 1998-02-12 Bmw Rolls Royce Gmbh Process for preventing laminar boundary layer separation on turbomachine blades
US6109868A (en) * 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction
US6231301B1 (en) * 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
US6574965B1 (en) 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
US6290458B1 (en) * 1999-09-20 2001-09-18 Hitachi, Ltd. Turbo machines
US6234747B1 (en) * 1999-11-15 2001-05-22 General Electric Company Rub resistant compressor stage
DE10135003C1 (en) * 2001-07-18 2002-10-02 Mtu Aero Engines Gmbh Compressor housing structure in axially, through-flowing moving blade ring for use in pumps
US6585479B2 (en) 2001-08-14 2003-07-01 United Technologies Corporation Casing treatment for compressors
US6663346B2 (en) * 2002-01-17 2003-12-16 United Technologies Corporation Compressor stator inner diameter platform bleed system
AU2003207365A1 (en) * 2002-02-28 2003-09-09 Daimlerchrysler Ag Anti-stall tip treatment means for turbo-compressors
GB0216952D0 (en) * 2002-07-20 2002-08-28 Rolls Royce Plc Gas turbine engine casing and rotor blade arrangement
DE10233032A1 (en) 2002-07-20 2004-01-29 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with integrated fluid circulation system
WO2004018844A1 (en) * 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Recirculation structure for a turbocompressor
FR2846034B1 (en) * 2002-10-22 2006-06-23 Snecma Moteurs CARTER, COMPRESSOR, TURBINE AND COMBUSTION TURBOMOTOR COMPRISING SUCH A CARTER
DE10355240A1 (en) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with fluid removal
DE10355241A1 (en) * 2003-11-26 2005-06-30 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with fluid supply
US7097414B2 (en) * 2003-12-16 2006-08-29 Pratt & Whitney Rocketdyne, Inc. Inducer tip vortex suppressor
GB2413158B (en) * 2004-04-13 2006-08-16 Rolls Royce Plc Flow control arrangement
DE102004030597A1 (en) * 2004-06-24 2006-01-26 Rolls-Royce Deutschland Ltd & Co Kg Turbomachine with external wheel jet generation at the stator
DE102004043036A1 (en) * 2004-09-06 2006-03-09 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with fluid removal
DE102004055439A1 (en) * 2004-11-17 2006-05-24 Rolls-Royce Deutschland Ltd & Co Kg Fluid flow machine with dynamic flow control
US7861823B2 (en) * 2005-11-04 2011-01-04 United Technologies Corporation Duct for reducing shock related noise
GB0600532D0 (en) * 2006-01-12 2006-02-22 Rolls Royce Plc A blade and rotor arrangement
EP1862641A1 (en) * 2006-06-02 2007-12-05 Siemens Aktiengesellschaft Annular flow channel for axial flow turbomachine
US20080044273A1 (en) * 2006-08-15 2008-02-21 Syed Arif Khalid Turbomachine with reduced leakage penalties in pressure change and efficiency
FR2912789B1 (en) * 2007-02-21 2009-10-02 Snecma Sa CARTER WITH CARTER TREATMENT, COMPRESSOR AND TURBOMACHINE COMPRISING SUCH A CARTER.
US20090160135A1 (en) * 2007-12-20 2009-06-25 Gabriele Turini Labyrinth seal with reduced leakage flow by grooves and teeth synergistic action

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3521798A1 (en) * 1984-06-19 1992-08-27 Rolls Royce Plc AXIAL COMPRESSOR WITH PUMP PREVENTION MEASURES
DE69402843T2 (en) * 1993-03-11 1997-09-04 Central Inst Of Aviat Motors C SHOVEL TIP DEVICE TO PROTECT AGAINST FLOW RETURN
DE10330084A1 (en) * 2002-08-23 2004-03-04 Mtu Aero Engines Gmbh Recirculation structure for turbocompressors
GB2408546A (en) * 2003-11-25 2005-06-01 Rolls Royce Plc Compressor casing treatment slots

Also Published As

Publication number Publication date
DE102007037924A1 (en) 2009-02-12
US20090041576A1 (en) 2009-02-12
EP2025945B1 (en) 2016-04-20
EP2025945A2 (en) 2009-02-18
US8419355B2 (en) 2013-04-16

Similar Documents

Publication Publication Date Title
EP2025945A3 (en) Flow working machine with ring canal wall fitting
EP2696029B1 (en) Blade row with side wall contours and fluid flow engine
EP2249043B1 (en) Compressor or pump with fluid extraction
EP3408503B1 (en) Turbomachinery with bladed diffuser
EP1710395A3 (en) Axial turbine
EP2226509B1 (en) Turbo compressor or pump with fluid injection to influence the boundary layer
EP2711505B1 (en) Auxiliary transmission device
EP2101040A3 (en) Turbomachine with multi-flow rotor assembly
DE102006044781A1 (en) Centrifugal compressor
DE10013908A1 (en) Fuel or washing fluid supply pump for vehicle has angles of blades in their radial extend increasing proportionally from center point with decrease in spacing
EP3225781A2 (en) Blade channel, blade row and turbomachine
EP3473848A1 (en) Flow energy installation, in particular a wind turbine with a jacket
DE102014106440A1 (en) Impeller, in particular for a side channel machine
EP3179036A1 (en) Ring area contouring of a gas turbine
DE102011052418A1 (en) Hub flow path profile
EP1637697A3 (en) Fluid machine flow path with axial gap concentration smaller than 1
DE102011052672A1 (en) Peak flow path profile
CN107178457B (en) The guide vane and hydraulic of hydraulic
DE102005042146A1 (en) Rotor with low input torque for a vane pump
EP2251091A3 (en) Rotor nozzle
DE102015223543A1 (en) Planetary gear, in particular for a wind turbine, with oil supply means for pressure oil lubrication planetary gear teeth
EP3580527B1 (en) Turbine wheel counter
DE112009002266B4 (en) Blade row for the final stage of a steam turbine
DE102012220249B4 (en) Guide vane, turbomachine and inner ring
DE102013224081A1 (en) compressor

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

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

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

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

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/66 20060101ALI20140520BHEP

Ipc: F04D 29/16 20060101ALI20140520BHEP

Ipc: F04D 27/02 20060101AFI20140520BHEP

Ipc: F04D 29/52 20060101ALI20140520BHEP

17P Request for examination filed

Effective date: 20140716

RBV Designated contracting states (corrected)

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

AKX Designation fees paid

Designated state(s): DE FR GB

AXX Extension fees paid

Extension state: AL

Extension state: RS

Extension state: MK

Extension state: BA

17Q First examination report despatched

Effective date: 20150216

REG Reference to a national code

Ref country code: DE

Ref legal event code: R079

Ref document number: 502008014108

Country of ref document: DE

Free format text: PREVIOUS MAIN CLASS: F04D0027020000

Ipc: F04D0029520000

RIC1 Information provided on ipc code assigned before grant

Ipc: F04D 29/52 20060101AFI20150929BHEP

Ipc: F04D 29/68 20060101ALI20150929BHEP

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20151113

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

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: DE

Ref legal event code: R096

Ref document number: 502008014108

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 9

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 502008014108

Country of ref document: DE

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

26N No opposition filed

Effective date: 20170123

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

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

Ref country code: DE

Payment date: 20190729

Year of fee payment: 12

Ref country code: FR

Payment date: 20190725

Year of fee payment: 12

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

Ref country code: GB

Payment date: 20190729

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R082

Ref document number: 502008014108

Country of ref document: DE

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502008014108

Country of ref document: DE

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

Effective date: 20200731

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: 20200731

Ref country code: GB

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

Effective date: 20200731

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

Ref country code: DE

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

Effective date: 20210202