EP0807211B1 - Ring-shaped diffuser for a gas turbine combustion chambers - Google Patents

Ring-shaped diffuser for a gas turbine combustion chambers Download PDF

Info

Publication number
EP0807211B1
EP0807211B1 EP96902919A EP96902919A EP0807211B1 EP 0807211 B1 EP0807211 B1 EP 0807211B1 EP 96902919 A EP96902919 A EP 96902919A EP 96902919 A EP96902919 A EP 96902919A EP 0807211 B1 EP0807211 B1 EP 0807211B1
Authority
EP
European Patent Office
Prior art keywords
diffuser
ring
gas turbine
struts
turbine combustion
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP96902919A
Other languages
German (de)
French (fr)
Other versions
EP0807211A1 (en
Inventor
William Kwan
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
BMW Rolls Royce GmbH
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 BMW Rolls Royce GmbH filed Critical BMW Rolls Royce GmbH
Publication of EP0807211A1 publication Critical patent/EP0807211A1/en
Application granted granted Critical
Publication of EP0807211B1 publication Critical patent/EP0807211B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/10—Air inlet arrangements for primary air

Definitions

  • the invention relates to a ring diffuser for a gas turbine combustion chamber with at least two lying essentially next to each other in the radial direction annular diffuser channels that viewed in the circumferential direction Have a plurality of air outlets separated from one another by struts.
  • Such a ring diffuser for supplying in particular stepped is known Gas turbine combustors, d. H. such combustion chambers, which next to Main burners also have pilot burners, from US Pat. No. 5,077,967 is used, for example, for the internal diffuser channel in the radial direction Supply of the individual pilot burners, while in the radial direction external diffuser channel, especially the main burner, is supplied with air.
  • the two are ring-shaped Diffuser channels viewed in the circumferential direction as usual through a variety divided by struts. These struts extend between the Inner and outer walls of the respective diffuser channel and serve on the one hand to support these channel walls, on the other hand also for improved Air routing or distribution of the air flow on the also arranged in a ring several burners.
  • the struts in the radial In the direction of adjacent diffuser channels offset from each other are.
  • FIG. 1 shows a partial section through a ring diffuser, and Fig. 2, the partial view X from Fig. 1.
  • annular gas turbine combustor supplied.
  • the inner wall 2a and the outer wall 2b of the ring diffuser 1 are in the air flow direction (Arrow direction 3) initially several guide blades 4 are provided, downstream of which the ring diffuser 1 extends in two in the radial direction R substantially adjacent annular diffuser channels 5a, 5b branches.
  • the radially inner diffuser channel can be, for example supply the pilot burners of the stepped combustion chamber, not shown, while the outer diffuser channel 5b the respective main burner can be assigned.
  • the diffuser channels 5a, 5b a plurality of adjacent air outlets 6a and 6b on the are separated from each other by struts 7. These struts extend between the respective diffuser channels 5a, 5b in the radial direction delimiting walls 2a, 2a 'and 2b, 2b'.
  • each strut 7 of the diffuser channel 5a is viewed in the circumferential direction U in FIG essentially between two struts 7 of the diffuser channel 5b and vice versa.
  • Another advantage of the strut arrangement shown is that the caused by temperature peaks or an uneven temperature distribution Stresses in the component can be reduced. In particular until The walls of the outer are reaching a steady temperature distribution Diffuser channel 5b is still relatively cold, while the walls of the interior Diffuser channel 5a through the hot according to arrow direction 3 from the compressor part the air flow delivered to the gas turbine is already heated.
  • This different temperature distribution can be particularly in the range Merging the walls 2a 'and 2b' lead to stress cracks, in particular if this merging or the two walls 2a ', 2b' themselves are designed to be relatively rigid.
  • the same inventive effects can also be achieved, if, for example, the struts 7 of the inner diffuser channel 5a are not lie exactly between the two struts 7 of the outer diffuser channel 5b, but more or less off-center with respect to each other Air outlet 6b.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Description

Die Erfindung betrifft einen Ringdiffusor für eine Gasturbinen-Brennkammer mit zumindest zwei in radialer Richtung im wesentlichen nebeneinanderliegenden ringförmigen Diffusorkanälen, die in Umfangsrichtung betrachtet eine Vielzahl von durch Streben voneinander getrennte Luftaustritte aufweisen.The invention relates to a ring diffuser for a gas turbine combustion chamber with at least two lying essentially next to each other in the radial direction annular diffuser channels that viewed in the circumferential direction Have a plurality of air outlets separated from one another by struts.

Bekannt ist ein derartiger Ringdiffusor zur Versorgung insbesondere gestufter Gasturbinen-Brennkammern, d. h. solcher Brennkammern, die neben Hauptbrennern auch Pilot-Brenner aufweisen, aus der US 5 077 967. Dabei dient beispielsweise der in radialer Richtung innenliegende Diffusorkanal zur Versorgung der einzelnen Pilotbrenner, während der in radialer Richtung außenliegende Diffusorkanal insbesondere die Hauptbrenner mit Luft versorgt. Im bekannten Stand der Technik sind dabei die beiden ringförmigen Diffusorkanäle in Umfangsrichtung betrachtet wie üblich durch eine Vielzahl von Streben unterteilt. Diese Streben erstrecken sich dabei zwischen den Innen- und Außenwänden des jeweiligen Diffusorkanales und dienen einerseits zur Abstützung dieser Kanalwände, andererseits auch zur verbesserten Luftführung bzw. Aufteilung des Luftstromes auf die ebenfalls ringförmig angeordneten mehreren Brenner.Such a ring diffuser for supplying in particular stepped is known Gas turbine combustors, d. H. such combustion chambers, which next to Main burners also have pilot burners, from US Pat. No. 5,077,967 is used, for example, for the internal diffuser channel in the radial direction Supply of the individual pilot burners, while in the radial direction external diffuser channel, especially the main burner, is supplied with air. In the known prior art, the two are ring-shaped Diffuser channels viewed in the circumferential direction as usual through a variety divided by struts. These struts extend between the Inner and outer walls of the respective diffuser channel and serve on the one hand to support these channel walls, on the other hand also for improved Air routing or distribution of the air flow on the also arranged in a ring several burners.

Wenngleich sich die bekannte Anordnung technisch grundsätzlich bewährt, so sind doch Verbesserungen wünschenswert, die aufzuzeigen sich die vorliegende Erfindung zur Aufgabe gestellt hat. Although the known arrangement has proven itself technically in principle, So improvements are desirable, which they show has given the present invention to the task.

Zur Lösung dieser Aufgabe ist vorgesehen, daß die Streben der in radialer Richtung nebeneinanderliegenden Diffusorkanäle zueinander versetzt angeordnet sind.To solve this problem it is provided that the struts in the radial In the direction of adjacent diffuser channels offset from each other are.

Näher erläutert wird die Erfindung anhand eines lediglich in zwei Prinzipskizzen dargestellten bevorzugten Ausführungsbeispieles. Dabei zeigt Fig. 1 einen Teilschnitt durch einen Ringdiffusor, sowie Fig. 2 die Teilansicht X aus Fig. 1.The invention is explained in more detail with reference to only two basic sketches illustrated preferred embodiment. 1 shows a partial section through a ring diffuser, and Fig. 2, the partial view X from Fig. 1.

Wie üblich und bekannt wird die von einem nicht gezeigten Axialverdichter geförderte Verbrennungsluft über einen Ringdiffusor 1 einer ebenfalls nicht gezeigten ringförmigen Gasturbinen-Brennkammer zugeführt. Zwischen der Innenwand 2a sowie der Außenwand 2b des Ringdiffusors 1 sind in Luft-Strömungsrichtung (Pfeilrichtung 3) zunächst mehrere Leitschaufeln 4 vorgesehen, stromab derer sich der Ringdiffusor 1 in zwei in radialer Richtung R im wesentlichen nebeneinanderliegende ringförmige Diffusorkanäle 5a, 5b verzweigt. Dabei kann der radial innenliegende Diffusorkanal beispielsweise die Pilotbrenner der nicht gezeigten, gestuften Brennkammer versorgen, während der außenliegende Diffusorkanal 5b den jeweiligen Hauptbrennem zugeordnet sein kann.As usual and known, that of an axial compressor, not shown also delivered combustion air via a ring diffuser 1 shown annular gas turbine combustor supplied. Between the The inner wall 2a and the outer wall 2b of the ring diffuser 1 are in the air flow direction (Arrow direction 3) initially several guide blades 4 are provided, downstream of which the ring diffuser 1 extends in two in the radial direction R substantially adjacent annular diffuser channels 5a, 5b branches. The radially inner diffuser channel can be, for example supply the pilot burners of the stepped combustion chamber, not shown, while the outer diffuser channel 5b the respective main burner can be assigned.

In Umfangsrichtung U betrachtet (vgl. Fig. 2) weisen die Diffusorkanäle 5a, 5b eine Vielzahl nebeneinanderliegender Luftaustritte 6a bzw. 6b auf, die durch Streben 7 voneinander getrennt sind. Diese Streben erstrecken sich dabei zwischen den die jeweiligen Diffusorkanäle 5a, 5b in radialer Richtung begrenzenden Wänden 2a, 2a' bzw. 2b, 2b'.Viewed in the circumferential direction U (see FIG. 2), the diffuser channels 5a, 5b a plurality of adjacent air outlets 6a and 6b on the are separated from each other by struts 7. These struts extend between the respective diffuser channels 5a, 5b in the radial direction delimiting walls 2a, 2a 'and 2b, 2b'.

Um die Ausströmverhältnisse dieses Ringdiffusors 1 zu optimieren, d. h. um einerseits die Anströmung der nicht gezeigten ringförmig angeordneten Pilot- und Hauptbrenner möglichst günstig zu gestalten und andererseits Verwirbelungsverluste im Austrittsbereich des Ringdiffusors, d. h. zwischen den einzelnen Luftaustritten 6a, 6b gering zu halten, sind die Streben 7 der beiden Diffusorkanäle 5a, 5b versetzt zueinander angeordnet. Dies bedeutet, daß sich in Umfangsrichtung U betrachtet jede Strebe 7 des Diffusorkanals 5a im wesentlichen zwischen zwei Streben 7 des Diffusorkanals 5b befindet und umgekehrt. Die nicht nur im Hinblick auf die Stabilität der einzelnen Wände 2a, 2a', 2b, 2b' benötigten Streben 7, die nämlich zusätzlich eine gewünschte weitere Luftaufteilung auf die einzelnen Brenner der Brennkammer vornehmen, verursachen nämlich auch geringfügige ungünstige Strömungswirbel. Ungünstige Auswirkungen dieser Wirbel werden mit der gezeigten Streben-Anordnung so gering als möglich gehalten. Würden hingegen die Streben 7 der beiden Diffusorkanäle 5a, 5b jeweils direkt übereinanderliegen, so würden sich die Wirbelstörungen, die an den einzelnen übereinanderliegenden Streben 7 hervorgerufen werden, nicht nur aufsummieren, sondern sogar vervielfachen. Dieser Effekt wird dadurch vermieden, daß die Streben 7 der in radialer Richtung nebeneinanderliegenden Diffusorkanäle 5a, 5b wie gezeigt zueinander versetzt angeordnet sind.In order to optimize the outflow conditions of this ring diffuser 1, i. H. around on the one hand, the inflow of the pilot pilot, not shown, arranged in a ring and make the main burner as cheap as possible and, on the other hand, swirl losses in the exit area of the ring diffuser, d. H. between the individual To keep air outlets 6a, 6b low, the struts 7 of the two Diffuser channels 5a, 5b arranged offset to one another. This means that each strut 7 of the diffuser channel 5a is viewed in the circumferential direction U in FIG essentially between two struts 7 of the diffuser channel 5b and vice versa. Not only in terms of the stability of the individual walls 2a, 2a ', 2b, 2b' required struts 7, namely namely a desired one further air distribution to the individual burners of the combustion chamber make, cause even minor unfavorable flow vortices. Adverse effects of these vertebrae are shown with the Strut arrangement kept as low as possible. Would, however the struts 7 of the two diffuser channels 5a, 5b each lie directly one above the other, so would the vertebral disorders that lie on top of each other Struts 7 are caused, not just add up, but even multiply. This effect is avoided by the fact that the struts 7 of the diffuser channels lying side by side in the radial direction 5a, 5b are arranged offset from one another as shown.

Ein weiterer Vorteil der gezeigten Streben-Anordnung besteht darin, daß die durch Temperaturspitzen bzw. eine ungleiche Temperaturverteilung hervorgerufenen Spannungen im Bauteil reduziert werden. Insbesondere bis zum Erreichen einer stationären Temperaturverteilung sind die Wände des äußeren Diffusorkanales 5b noch relativ kalt, während die Wände des inneren Diffusorkanales 5a durch die heiße gemäß Pfeilrichtung 3 vom Kompressorteil der Gasturbine herangeförderte Luftströmung bereits erwärmt sind. Diese unterschiedliche Temperaturverteilung kann insbesondere im Bereich der Zusammenführung der Wände 2a' und 2b' zu Spannungsrissen führen, insbesondere wenn diese Zusammenführung bzw. die beiden Wände 2a', 2b' selbst relativ steif gestaltet sind. Sind nun die Streben 7 - wie gezeigt - zwischen den Wänden 2b und 2b' bzw. 2a und 2a' in Umfangsrichtung versetzt zueinander angeordnet, so wird hierdurch dieser gesamten Bauteilstruktur eine gewisse Weichheit verliehen, die den Abbau von Spannungsspitzen förderlich ist. Mögliche Spannungen, resultierend aus Temperaturspitzen bzw. einer ungleichen Temperaturverteilung können hiermit abgeleitet werden, so daß die Wahrscheinlichkeit für Risse im Bauteil aufgrund der versetzten Anordnung der Streben 7 deutlich herabgesetzt wird.Another advantage of the strut arrangement shown is that the caused by temperature peaks or an uneven temperature distribution Stresses in the component can be reduced. In particular until The walls of the outer are reaching a steady temperature distribution Diffuser channel 5b is still relatively cold, while the walls of the interior Diffuser channel 5a through the hot according to arrow direction 3 from the compressor part the air flow delivered to the gas turbine is already heated. This different temperature distribution can be particularly in the range Merging the walls 2a 'and 2b' lead to stress cracks, in particular if this merging or the two walls 2a ', 2b' themselves are designed to be relatively rigid. Are the struts 7 - as shown - between the walls 2b and 2b 'or 2a and 2a' offset in the circumferential direction arranged with respect to one another, so this entire component structure given a certain softness that the breakdown of voltage spikes is beneficial. Possible tensions resulting from temperature peaks or an uneven temperature distribution can be derived with this, so that the probability of cracks in the component due to the staggered arrangement of the struts 7 is significantly reduced.

Noch ein weiterer Vorteil dieser Strebenanordnung liegt in der vereinfachten Herstellbarkeit, insbesondere beim Gießen. Aufgrund der gleichmäßigeren Materialverteilung, hervorgerufen durch die versetzte Streben-Anordnung, läuft der Erstarrungsprozeß des flüssigen Gießmateriales gleichmäßiger und besser ab, so daß die Ausschußquote wesentlich geringer ist. Auch können die nötigen Toleranzen mit der beschriebenen Strebenanordnung besser eingehalten werden.Yet another advantage of this strut arrangement is that it is simplified Producibility, especially when casting. Because of the more even Material distribution, caused by the offset strut arrangement, the solidification process of the liquid casting material runs more evenly and better, so that the reject rate is much lower. Can too the necessary tolerances better with the strut arrangement described be respected.

Selbstverständlich sind die gleichen erfinderischen Effekte auch erzielbar, wenn beispielsweise die Streben 7 des inneren Diffusorkanales 5a nicht exakt zwischen den beiden Streben 7 des äußeren Diffusorkanales 5b liegen, sondern mehr oder minder außermittig bezüglich des jeweiligen anderen Luftaustrittes 6b.Of course, the same inventive effects can also be achieved, if, for example, the struts 7 of the inner diffuser channel 5a are not lie exactly between the two struts 7 of the outer diffuser channel 5b, but more or less off-center with respect to each other Air outlet 6b.

Claims (1)

  1. A ring diffuser for a gas turbine combustion chamber with at least two ring shaped diffuser channels (5a, 5b) lying essentially adjacent to each other in the radial direction (R), which observed in the peripheral direction (U) have a multiplicity of air outlets (6a, 6b) separated from each other by webs (7),
    characterised in that the webs (7) of the diffuser channels (5a, 5b) adjacent to each other in the radial direction (R) are arranged to be offset with respect to each other.
EP96902919A 1995-02-03 1996-01-25 Ring-shaped diffuser for a gas turbine combustion chambers Expired - Lifetime EP0807211B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19503567 1995-02-03
DE19503567A DE19503567A1 (en) 1995-02-03 1995-02-03 Ring diffuser for a gas turbine combustion chamber
PCT/EP1996/000299 WO1996023978A1 (en) 1995-02-03 1996-01-25 Ring-shaped diffuser for a gas turbine combustion chambers

Publications (2)

Publication Number Publication Date
EP0807211A1 EP0807211A1 (en) 1997-11-19
EP0807211B1 true EP0807211B1 (en) 1999-05-19

Family

ID=7753124

Family Applications (1)

Application Number Title Priority Date Filing Date
EP96902919A Expired - Lifetime EP0807211B1 (en) 1995-02-03 1996-01-25 Ring-shaped diffuser for a gas turbine combustion chambers

Country Status (4)

Country Link
EP (1) EP0807211B1 (en)
CA (1) CA2208843A1 (en)
DE (2) DE19503567A1 (en)
WO (1) WO1996023978A1 (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2241840C2 (en) * 2002-11-12 2004-12-10 Открытое акционерное общество "Авиадвигатель" Gas-turbine engine
FR2880391A1 (en) * 2005-01-06 2006-07-07 Snecma Moteurs Sa DIFFUSER FOR AN ANNULAR COMBUSTION CHAMBER, IN PARTICULAR FOR AN AIRCRAFT TURBOMOTOR

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2704089A (en) * 1952-06-09 1955-03-15 Lee R Woodworth Gas turbine diffuser
DE1092159B (en) * 1956-12-20 1960-11-03 Messerschmitt Boelkow Blohm Axial compressor with relative supersonic speed
GB1315856A (en) * 1970-03-20 1973-05-02 Secr Defence Flow restrictors
US5077967A (en) * 1990-11-09 1992-01-07 General Electric Company Profile matched diffuser
US5165850A (en) * 1991-07-15 1992-11-24 General Electric Company Compressor discharge flowpath
US5323604A (en) * 1992-11-16 1994-06-28 General Electric Company Triple annular combustor for gas turbine engine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11732892B2 (en) 2013-08-14 2023-08-22 General Electric Company Gas turbomachine diffuser assembly with radial flow splitters
US12044408B2 (en) 2013-08-14 2024-07-23 Ge Infrastructure Technology Llc Gas turbomachine diffuser assembly with radial flow splitters

Also Published As

Publication number Publication date
DE19503567A1 (en) 1996-08-08
WO1996023978A1 (en) 1996-08-08
EP0807211A1 (en) 1997-11-19
CA2208843A1 (en) 1996-08-08
DE59601944D1 (en) 1999-06-24

Similar Documents

Publication Publication Date Title
DE69412484T2 (en) COMBUSTION CHAMBER OF A GAS TURBINE ENGINE
DE3873130T2 (en) FORCED COOLING FOR A GAS TURBINE INLET CHANNEL.
DE3007763C2 (en) Annular combustion chamber for gas turbine engines
DE69726626T2 (en) Three-channel diffuser for a gas turbine engine
EP2154431B1 (en) Thermal machine
EP1389690B1 (en) Screw interiorly cooled
DE19538746B4 (en) Segmented centerbody for a double ring combustor
DE69819260T2 (en) Gas turbine combustor
EP1111189B1 (en) Cooling air path for the rotor of a gas turbine engine
DE69209634T2 (en) Dual fuel nozzle for gas turbine
DE3309268C2 (en)
CH698347B1 (en) Fuel nozzle for a gas turbine, gas turbine and process for operating a gas turbine.
CH701144A2 (en) Fuel nozzle support system with many premix fuel nozzles.
DE19520291A1 (en) Combustion chamber
DE102015112767A1 (en) Fuel injector assemblies in combustion turbines
EP2470834B1 (en) Burner, in particular for gas turbines
DE102007007090A1 (en) Gas turbine has cooling air transfer system with several tubular nozzles which are independently arranged in a circle inside a chamber, encompass the rotor and can discharge cooling air
DE1108516B (en) Burning device
DE60216366T2 (en) Gas turbine combustor
EP2275743A2 (en) Gas turbine combustion chamber with starter film for cooling the combustion chamber wall
WO2011023648A2 (en) Swirl blade, burner and gas turbine
EP0636764A1 (en) Gasturbine with cooled rotor
EP0122872A1 (en) Medium pressure steam turbine for a high temperature steam plant with intermediate reheating
DE3317722A1 (en) RING DIFFUSER FOR A GAS TURBINE ENGINE
DE1751838A1 (en) Burner arrangement, especially for gas turbine systems

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: 19970424

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB SE

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

17Q First examination report despatched

Effective date: 19980828

GRAG Despatch of communication of intention to grant

Free format text: ORIGINAL CODE: EPIDOS AGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

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 SE

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 19990519

REF Corresponds to:

Ref document number: 59601944

Country of ref document: DE

Date of ref document: 19990624

ET Fr: translation filed
PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

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

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

26N No opposition filed
REG Reference to a national code

Ref country code: FR

Ref legal event code: CJ

Ref country code: FR

Ref legal event code: CA

REG Reference to a national code

Ref country code: GB

Ref legal event code: IF02

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

Ref country code: DE

Payment date: 20090302

Year of fee payment: 14

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

Ref country code: GB

Payment date: 20090129

Year of fee payment: 14

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

Ref country code: SE

Payment date: 20090128

Year of fee payment: 14

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

Ref country code: FR

Payment date: 20090119

Year of fee payment: 14

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

Effective date: 20100125

EUG Se: european patent has lapsed
REG Reference to a national code

Ref country code: FR

Ref legal event code: ST

Effective date: 20100930

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: 20100201

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: 20100803

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: 20100125

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

Ref country code: SE

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

Effective date: 20100126