EP0821134A1 - Agencement et procédé de réglage de diamètre d'anneau de stator - Google Patents
Agencement et procédé de réglage de diamètre d'anneau de stator Download PDFInfo
- Publication number
- EP0821134A1 EP0821134A1 EP97401775A EP97401775A EP0821134A1 EP 0821134 A1 EP0821134 A1 EP 0821134A1 EP 97401775 A EP97401775 A EP 97401775A EP 97401775 A EP97401775 A EP 97401775A EP 0821134 A1 EP0821134 A1 EP 0821134A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- stator ring
- conduits
- cavity
- gas
- adjustment arrangement
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
- F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
Definitions
- the invention relates to an arrangement and a stator ring diameter adjustment process so reduce the clearance with the rotor blade ends that this ring surrounds; it therefore applies to turbomachinery and was first designed for a turbine at high pressure of a two-stage turbine, without this application is exclusive.
- the adjustment arrangement in accordance with the invention is characterized in that it comprises a housing element hollowed out and occupied by a cavity communicating through conduits to rooms located in upstream and downstream of the ring and which surround a vein gas circulation delimited by the ring.
- This housing element is linked to the ring and located between the ring facing the rotor and the device surrounding gas blowing.
- the corresponding method of adjusting diameter of a stator ring linked to a periphery housing element internal consists, while blowing gas on an outer periphery of this element like previously to produce a gas flow essentially convective through the element of casing, away from the stator ring and between the outer and inner edges.
- FIG. 1 shows part of high-pressure turbine with an upstream stage 1 and a stage downstream 2.
- Each of stages 1 and 2 comprises, from of a rotor 3 and towards the outside, a group of blades mobile 4 linked to the rotor 3, a hoop 5 surrounding the movable blades 4, from which it is separated by a small play 6, a casing element 7 to which the hoop 5 is fixed by circular 8 and 9 adjustments on its sides upstream and downstream, and the blowing distributor 10, called shower collar as already mentioned, and which consists of a circular tube with holes 11 opening towards the casing element 7 a little distance from him.
- the blowing distributor 10 is supplied with air by a duct not shown leading to the compressor.
- the essential element of the invention is located on a part outer 15 of the casing element 7, which is hollowed out a cavity 16 divided into two halves, a groove upstream 17 and a downstream groove 18, by a partition 19 transverse, planar and circular.
- Upstream conduits 20 leading to an upstream chamber 21 open into the upstream groove 17, and likewise downstream conduits 22 leading downstream chamber 23 open into the downstream groove 18.
- the upstream 21 and downstream 23 chambers are located around bladed distributors 33 and 34 preceding each of the movable blade stages 4.
- Blade rings 35 and 36 intended to support the vanes of the distributors 33 and 34 isolate the chambers 21 and 23 from the vein 31 of gas flow in which the vanes and movable extend, so that the air which occupies them rooms 21 and 23 is not very agitated and remains even little near stagnant in their bottoms, where the ducts 20 and 22 open.
- a rollover 40 which isolates a chamber background 41 from the rest of the chamber 21 and into which the upstream conduits 20 open.
- the draft that can pass through chamber 21 runs along the cowling 40 and can only cross it by holes 42 perpendicular to its flow for enter the chamber bottom 41
- the flow towards downstream through cavity 16 and conduits 20 and 22 is therefore of low flow, which favors convection movements and heat exchanges obtained by this means, in particular in the cavity 16.
- the temperature of the casing element 7 thus tends to equalize without a significant air intake being product.
- the flow is further slowed by the eccentric position of 24 days piercing the partition 19 to communicate the gorges 17 and 18.
- These days 24 are in the form of axially offset lunules and radially of conduits 20 and 22: while these emerge at the bottom of gorges 17 and 18, days 24 are operated against their edge, near the distributor 10, from which they are only separated by a hoop 25 integrated into the casing element 7 and used to close the cavity 16 once it has been dug.
- the air travels the upstream gorge 17 outwards and turn back in the downstream groove 18 by crossing the cavity 16.
- the Figure 3 also shows that the days 24 extend, in angular direction in the cavity 16, halfway pairs of upstream 20 or downstream 22 conduits, which produces air circulation in the cavity 16. All of these provisions further increase convection.
- Air from the upstream chamber 21 can also be taken and directed directly to the turbine ring hoop 5 to adjust the diameter of this one directly.
- a distributor 30 in the form of an openwork plate divides and equalizes the air flow in front of the surface internal hoop 5. It is actually a known system used concurrently with the invention and which is only recalled here to better distinguish this last. In particular, a relatively important gas is directly blown on the hoop 5.
- the convection circuit is here placed closer to the stator ring 5 and is split into two elements each of which is located in an annular rib 43 or 44 for connecting a casing outside 45 to a spacer 46 carrying the ring stator 5.
- the ribs 43 and 44 are provided with spoilers 47 engaged under retaining edges 48 of the spacer 46 to constitute this connection, and we finds a spoiler 49 on the spacer 46, which is engaged under an edge 50 of the stator ring 5; all these borders 48 and 50 are retained in circular grooves drawn by the spoilers 47 and 49.
- a jumper 51 connects two flanges circulars 52 and 53 of the spacer 30 and the ring stator 5 to prevent it from moving axial.
- the two elements of the convection circuit here also include a cavity 16 divided in two parallel circular grooves 17 and 18 by a partition 19.
- the communication channels of the grooves outside extend around the cavities 16, and the days (54 here) drilled through the partitions 19 are located at their inner circumferences to be offset radially of the conduits, as in the embodiment former. They can also be offset angularly from these conduits.
- the upstream conduits 55 of the cavity 16 in the rib 43 open into a circular collecting chamber 56 substantially closed by a cover 57 and which communicates with conduits gas supply 65 by as many holes 58.
- the downstream conduits 59 of this same cavity 16 open out in an intermediate chamber 60 in which still open the upstream conduits 61 on the other cavity 16, located in the rib 14; the conduits downstream 62 from this other cavity 16 open into a other chamber 66.
- a deflector cover 67 is arranged in room 56, in front of the outlet of the conduits gas supply 65, to reverse the flow of it and make it gradually take a angular direction.
- An upstream conduit 55 is sheltered from the gas inlet through the deflector cowling 67 and is So found in the bottom of room 56 where the gas is pretty much stagnant.
- FIG. 5 finally shows the application of this system to an embodiment without the spacer 30: the fastening elements 49 to 53 defined above then directly connect the stator ring 5 to the ribs 13 and 14. All the other provisions of the Figure 4 are unchanged.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Control Of Turbines (AREA)
Abstract
Description
- la figure 1 est une vue générale de l'agencement et des pièces environnantes de la turbomachine,
- la figure 2 représente plus précisément les parties caractéristiques de l'invention,
- la figure 3 est une coupe de l'anneau de carter à travers la cavité,
- la figure 4 illustre un autre mode de réalisation de l'invention,
- et la figure 5 est une variante de cet autre mode de réalisation.
Claims (10)
- Agencement de réglage de diamètre d'un anneau de stator (5) au moyen d'un dispositif environnant (10,56,65) de soufflage de gaz, caractérisé en ce qu'il comprend, lié à l'anneau (5) et situé entre l'anneau et le dispositif de soufflage de gaz (10,56, 65), un élément de carter (7,43,44,45) évidé et occupé par une cavité (16) communiquant par des conduits (20, 22,55,59,61,62) à des chambres (21,23,56,60,663) en amont et en aval de l'anneau qui entourent une veine de circulation de gaz délimitée par l'anneau,et qui sont occupées par du gaz à peu près stagnant devant les conduits (20,22,55,61,62), la cavité (16) et les conduits (20,22,55,59,61,62) s'étendant à l'écart de l'anneau de stator.
- Agencement de réglage de diamètre d'anneau de stator suivant la revendication 1, caractérisé en ce que la cavité est divisée par une cloison (19) ajourée une moitié amont (17) dans laquelle débouchent les conduits (20,55,61) communiquant à la chambre amont (21,56,60) et une moitié aval (18) dans laquelle débouchent les conduits (22,59,62) communiquant à la chambre aval (23,60,66).
- Agencement de réglage de diamètre d'anneau de stator suivant la revendication 2, caractérisé en ce que la cloison (19) est pourvue de jours (24,54) décalés radialement des conduits.
- Agencement de réglage de diamètre d'anneau de stator suivant la revendication 2, caractérisé en ce que la cloison est pourvue de jours (24,54) décalés angulairement des conduits.
- Agencement de réglage de diamètre d'anneau de stator suivant l'une quelconque des revendications 1 à 4, caractérisé en ce qu'une des chambres (21) appartient à un circuit de soufflage de gaz sur l'anneau de stator (5).
- Agencement de réglage de diamètre d'anneau de stator suivant l'une quelconque des revendications 1 à 4, caractérisé en ce qu'une des chambres (56) appartient au dispositif environnant de soufflage de gaz.
- Agencement de réglage de diamètre d'anneau de stator suivant l'une quelconque des revendications 1 à 6, caractérisé en ce que la cavité est disposée sur une nervure (13,14) de soutien de l'anneau de stator.
- Agencement de réglage de diamètre d'anneau de stator suivant la revendication 7, caractérisé en ce qu'il comprend deux cavités disposées dans deux nervures (13,14) parallèles de soutien de l'anneau de stator, les cavités (16) communiquant entre elles par des conduits (59,61) et une chambre intermédiaire (60).
- Agencement de réglage de diamètre d'anneau de stator suivant l'une quelconque des revendications 1 à 8, caractérisé en ce qu'une des chambres (21,56) est siège d'un écoulement de gaz et en ce qu'un capotage (40,67) situé dans ladite chambre y délimite un fond de chambre (41) sensiblement dépourvu d'écoulement dans lequel débouchent les conduits (20,55) de la cavité communiquant à ladite chambre.
- Procédé de réglage de diamètre d'un anneau de stator (5) lié à un pourtour interne d'un élément de carter (7), consistant à souffler du gaz sur un pourtour externe de l'élément de carter, caractérisé en ce qu'il consiste à produire un écoulement de gaz essentiellement convectif à travers l'élément de carter, à l'écart de l'anneau de stator et entre les pourtours interne et externe.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9609364 | 1996-07-25 | ||
FR9609364A FR2751694B1 (fr) | 1996-07-25 | 1996-07-25 | Agencement et procede de reglage de diametre d'anneau de stator |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0821134A1 true EP0821134A1 (fr) | 1998-01-28 |
EP0821134B1 EP0821134B1 (fr) | 2004-03-24 |
Family
ID=9494470
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP97401775A Expired - Lifetime EP0821134B1 (fr) | 1996-07-25 | 1997-07-24 | Agencement et procédé de réglage de diamètre d'anneau de stator |
Country Status (5)
Country | Link |
---|---|
US (1) | US5915919A (fr) |
EP (1) | EP0821134B1 (fr) |
CA (1) | CA2211428C (fr) |
DE (1) | DE69728222T2 (fr) |
FR (1) | FR2751694B1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1914392A2 (fr) * | 2006-10-12 | 2008-04-23 | General Electric Company | Refroidissement par contact de carter de turbine pour turbines à gaz |
EP1923538A2 (fr) * | 2006-11-15 | 2008-05-21 | General Electric Company | Turbine avec réglage du jeu des extrémités des aubes par transpiration |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2780443B1 (fr) * | 1998-06-25 | 2000-08-04 | Snecma | Anneau de stator de turbine haute pression d'une turbomachine |
DE10019437A1 (de) * | 2000-04-19 | 2001-12-20 | Rolls Royce Deutschland | Verfahren und Vorrichtung zum Kühlen der Gehäuse von Turbinen von Strahltriebwerken |
FR3002971B1 (fr) * | 2013-03-06 | 2015-04-17 | Snecma | Dispositif de ventilation d'un carter de stator d'une turbomachine, comprenant un ajustement sur des circonferences |
FR3002972B1 (fr) * | 2013-03-06 | 2015-04-17 | Snecma | Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale |
DE102018203442A1 (de) | 2018-03-07 | 2019-09-12 | MTU Aero Engines AG | Innenring für eine Turbomaschine, Leitschaufelkranz mit einem Innenring, Turbomaschine und Verfahren zur Herstellung eines Innenrings |
US11015475B2 (en) * | 2018-12-27 | 2021-05-25 | Rolls-Royce Corporation | Passive blade tip clearance control system for gas turbine engine |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2295239A1 (fr) * | 1974-12-19 | 1976-07-16 | Gen Electric | Turbine a gaz a vanne thermosensible pour le reglage du jeu entre le rotor et le stator |
GB2062117A (en) * | 1980-10-20 | 1981-05-20 | Gen Electric | Clearance Control for Turbine Blades |
US4337016A (en) * | 1979-12-13 | 1982-06-29 | United Technologies Corporation | Dual wall seal means |
EP0115984A1 (fr) * | 1983-02-03 | 1984-08-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Dispositif d'étanchéité d'aubages mobiles de turbomachine |
GB2217788A (en) * | 1988-03-31 | 1989-11-01 | Gen Electric | Gas turbine engine shroud clearance control |
GB2263138A (en) * | 1992-01-08 | 1993-07-14 | Snecma | Turbomachine compressor casing with clearance control means |
FR2688539A1 (fr) * | 1992-03-11 | 1993-09-17 | Snecma | Stator de turbomachine comprenant des dispositifs de reglage de jeu entre le stator et les aubes du rotor. |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2712727A (en) * | 1950-05-17 | 1955-07-12 | Rolls Royce | Gas turbine power plants with means for preventing or removing ice formation |
GB2047354B (en) * | 1979-04-26 | 1983-03-30 | Rolls Royce | Gas turbine engines |
GB2236147B (en) * | 1989-08-24 | 1993-05-12 | Rolls Royce Plc | Gas turbine engine with turbine tip clearance control device and method of operation |
GB9210642D0 (en) * | 1992-05-19 | 1992-07-08 | Rolls Royce Plc | Rotor shroud assembly |
JPH06173712A (ja) * | 1992-12-14 | 1994-06-21 | Toshiba Corp | ガスタービンケーシングの冷却装置 |
US5593277A (en) * | 1995-06-06 | 1997-01-14 | General Electric Company | Smart turbine shroud |
-
1996
- 1996-07-25 FR FR9609364A patent/FR2751694B1/fr not_active Expired - Fee Related
-
1997
- 1997-07-11 US US08/893,521 patent/US5915919A/en not_active Expired - Lifetime
- 1997-07-17 CA CA002211428A patent/CA2211428C/fr not_active Expired - Fee Related
- 1997-07-24 EP EP97401775A patent/EP0821134B1/fr not_active Expired - Lifetime
- 1997-07-24 DE DE69728222T patent/DE69728222T2/de not_active Expired - Lifetime
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2295239A1 (fr) * | 1974-12-19 | 1976-07-16 | Gen Electric | Turbine a gaz a vanne thermosensible pour le reglage du jeu entre le rotor et le stator |
US4337016A (en) * | 1979-12-13 | 1982-06-29 | United Technologies Corporation | Dual wall seal means |
GB2062117A (en) * | 1980-10-20 | 1981-05-20 | Gen Electric | Clearance Control for Turbine Blades |
EP0115984A1 (fr) * | 1983-02-03 | 1984-08-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Dispositif d'étanchéité d'aubages mobiles de turbomachine |
GB2217788A (en) * | 1988-03-31 | 1989-11-01 | Gen Electric | Gas turbine engine shroud clearance control |
GB2263138A (en) * | 1992-01-08 | 1993-07-14 | Snecma | Turbomachine compressor casing with clearance control means |
FR2688539A1 (fr) * | 1992-03-11 | 1993-09-17 | Snecma | Stator de turbomachine comprenant des dispositifs de reglage de jeu entre le stator et les aubes du rotor. |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1914392A2 (fr) * | 2006-10-12 | 2008-04-23 | General Electric Company | Refroidissement par contact de carter de turbine pour turbines à gaz |
EP1914392A3 (fr) * | 2006-10-12 | 2013-01-02 | General Electric Company | Refroidissement par contact de carter de turbine pour turbines à gaz |
US8801370B2 (en) | 2006-10-12 | 2014-08-12 | General Electric Company | Turbine case impingement cooling for heavy duty gas turbines |
EP1923538A2 (fr) * | 2006-11-15 | 2008-05-21 | General Electric Company | Turbine avec réglage du jeu des extrémités des aubes par transpiration |
EP1923538A3 (fr) * | 2006-11-15 | 2014-07-23 | General Electric Company | Turbine avec réglage du jeu des extrémités des aubes par transpiration |
Also Published As
Publication number | Publication date |
---|---|
DE69728222D1 (de) | 2004-04-29 |
FR2751694A1 (fr) | 1998-01-30 |
US5915919A (en) | 1999-06-29 |
FR2751694B1 (fr) | 1998-09-04 |
DE69728222T2 (de) | 2005-03-10 |
EP0821134B1 (fr) | 2004-03-24 |
CA2211428C (fr) | 2006-03-14 |
CA2211428A1 (fr) | 1998-01-25 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CA2366363C (fr) | Agencement de reglage de diametre d'un stator de turbine a gaz | |
US6390771B1 (en) | High-pressure compressor stator | |
JP5111975B2 (ja) | タービンエンジンで使用するノズルセグメントを製作するためのノズルシングレット及びガスタービンエンジン | |
EP0816639B1 (fr) | Dispositif de souflage de gaz de réglage de jeux dans une turbomachine | |
US8764385B2 (en) | Axial-centrifugal compressor having system for controlling play | |
EP2732145B1 (fr) | Système de mise sous pression de carter de moteur à turbine à gaz | |
EP0821134B1 (fr) | Agencement et procédé de réglage de diamètre d'anneau de stator | |
JPH0689653B2 (ja) | ガスタービンエンジンの圧縮機用の羽根及びパツキングの隙間最適化装置 | |
RU2003128565A (ru) | Газотурбинный двигатель с вращающимися в противоположных направлениях вентиляторами и с задним нагнетателем | |
JP4060279B2 (ja) | ターボ機械の高圧タービンロータ用の通気装置 | |
EP2948642A1 (fr) | Aube de stator réglable à segment multiple pour un ensemble d'aube à section variable | |
CN107023391B (zh) | 用于燃气涡轮发动机的压缩机 | |
JPH03137423A (ja) | 前方抽気開口を有する燃焼器内側通路 | |
EP1188901A2 (fr) | Ouvertures de transfert pour le refroidissement d'un rotor | |
CN109958478A (zh) | 翼型件及其制造方法 | |
EP1508670B1 (fr) | Aube refroidie de moteur à turbine à gaz | |
CA3020423A1 (fr) | Refroidissement de carenage de turbine | |
CN107084002A (zh) | 一种组件的热应力释放 | |
EP3412868B1 (fr) | Aube statorique avec refroidissement fendu à débit réglable de plate-forme pour turbine à gaz | |
US20180038236A1 (en) | Gas turbine engine stator vane baffle arrangement | |
JP2005009410A (ja) | ガスタービン及びロータシール空気導入方法 | |
FR3002972A1 (fr) | Dispositif de ventilation d'un carter de stator d'une turbomachine comprenant un ajustement en direction axiale | |
FR3055355A1 (fr) | Dispositif et procede de reglage de jeux entre un rotor et un stator concentrique d'une turbomachine | |
US10495107B2 (en) | Guide vane assembly with compensation device | |
FR3115562A1 (fr) | Injecteur d’air de refroidissement pour turbine de turbomachine |
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: 19970812 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE |
|
RBV | Designated contracting states (corrected) |
Designated state(s): DE FR GB |
|
17Q | First examination report despatched |
Effective date: 20020221 |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
RAP1 | Party data changed (applicant data changed or rights of an application transferred) |
Owner name: SNECMA MOTEURS |
|
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 |
|
REF | Corresponds to: |
Ref document number: 69728222 Country of ref document: DE Date of ref document: 20040429 Kind code of ref document: P |
|
GBT | Gb: translation of ep patent filed (gb section 77(6)(a)/1977) |
Effective date: 20040419 |
|
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: 20041228 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20150626 Year of fee payment: 19 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 19 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20150623 Year of fee payment: 19 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20160720 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R119 Ref document number: 69728222 Country of ref document: DE |
|
GBPC | Gb: european patent ceased through non-payment of renewal fee |
Effective date: 20160724 |
|
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: 20170201 |
|
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: 20160724 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: CD Owner name: SAFRAN AIRCRAFT ENGINES Effective date: 20170719 |