EP1767858A1 - Brennkammer mit Verkleidung für eine Gasturbine - Google Patents

Brennkammer mit Verkleidung für eine Gasturbine Download PDF

Info

Publication number
EP1767858A1
EP1767858A1 EP06121135A EP06121135A EP1767858A1 EP 1767858 A1 EP1767858 A1 EP 1767858A1 EP 06121135 A EP06121135 A EP 06121135A EP 06121135 A EP06121135 A EP 06121135A EP 1767858 A1 EP1767858 A1 EP 1767858A1
Authority
EP
European Patent Office
Prior art keywords
wall
downstream
combustion chamber
chamber
cap
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
EP06121135A
Other languages
English (en)
French (fr)
Other versions
EP1767858B1 (de
Inventor
Romain Biebel
Didier Hippolyte Hernandez
Denis Gabriel Trahot
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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=36218594&utm_source=google_patent&utm_medium=platform_link&utm_campaign=public_patent_search&patent=EP1767858(A1) "Global patent litigation dataset” by Darts-ip is licensed under a Creative Commons Attribution 4.0 International License.
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1767858A1 publication Critical patent/EP1767858A1/de
Application granted granted Critical
Publication of EP1767858B1 publication Critical patent/EP1767858B1/de
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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23R3/002—Wall structures
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators

Definitions

  • the invention relates to a combustion chamber for a gas turbine engine, with an upstream fairing for separating the gas flow, an annular wall forming a cap of the upstream fairing of the chamber and a gas turbine engine with the chamber.
  • a turbojet comprises, from upstream to downstream in the direction of the gas flow, a fan, one or more stages of compressors, a combustion chamber, one or more turbine stages and a gas exhaust nozzle.
  • the combustion chamber 1 is generally annular about the axis of the turbojet engine. It comprises, in its upstream portion, a chamber bottom 2 with injection systems fueled by injectors 3, connected to a supply line 4. The injection systems are distributed along the bottom of the chamber 2.
  • the primary flow gas opens upstream of the chamber 1 by a diffuser 5, from which the flow of gas separates into a flow 6 passing through the combustion chamber. 1 to allow the combustion of the fuel injected by the injector 3, called the combustion stream 6, into an external bypass flow 7 of the inlet of the chamber 1 and a flow 8 of internal bypass of the chamber inlet 1.
  • the flows 7, 8 bypassing the entrance of the chamber are used for cooling the chamber 1, in particular.
  • This fairing 9 comprises two parts, called outer cap 10 and cap 11.
  • the outer cap 10 is in the form of a curved annular sheet towards the upstream side, fixed to the combustion chamber 1 at an outer downstream surface portion 15, and whose inner upstream edge 12 forms a flap downstream, thus forming an aerodynamic surface for separating external flow bypass 7 and combustion flow 6.
  • the inner cap 11 is in the form of a curved annular sheet towards the upstream side, fixed at the combustion chamber 1 at an outer downstream surface portion 16, and whose inner upstream edge 13 forms a flap downstream, forming an aerodynamic surface separation of the internal bypass flow 8 and the combustion stream 6.
  • the outer cap 10 and inner cap 11 are fixed on the outer side of the outer wall 31 and inner 32, respectively, of the combustion chamber 1, at their outer downstream surface portion 15, 16, respectively, by bolts 14.
  • the outer cap 10 and inner 11 are mounted cantilever on the combustion chamber 1.
  • the combustion chamber is subjected to vibratory stresses, particularly due to combustion and engine speed.
  • the caps 10, 11 are therefore subjected to these vibrations, in particular the outer cap 10.
  • the caps 10, 11 are also subjected to other dynamic excitation frequencies, in particular certain harmonic frequencies of the rotational speed of the rotary members of the turbojet engine. .
  • the caps 10, 11, mounted cantilevered may have resonance modes close to the frequencies and are therefore subject to high mechanical dynamic stresses. It follows risks of rupture or crack caps 10, 11.
  • a first solution consists in providing an annular damping ring, housed in the flap 12, 13 of the caps 10, 11 (or only the outer cap which is the most subject to vibratory stresses); the flap 12, 13 is for this purpose wrapped around the ring to maintain it.
  • the friction generated by the presence of the ring provides a damping effect and thus a displacement of the frequencies of the resonance modes of the caps 10, 11, which allows them to be removed from the vibratory frequencies to which the caps 10, 11 are subjected.
  • Such a device however has the disadvantage of a low mechanical strength. There is a risk of loosening the ring, or even rupture (due to the vibrations to which it is subjected), which decreases or cancels its effectiveness.
  • a second solution is to provide a fairing 9 monobloc, which is called rollover.
  • the outer cap 10 and inner 11 are then formed in one piece, with connecting tabs between them, at their inner upstream edges 12, 13.
  • Such a device has two disadvantages. First, because of the connecting lugs between the caps 10, 11, the flow section of the combustion stream 6 is reduced; however, it is common ground that this section must be as large as possible, in order to promote the passage of this flow, for a better combustion efficiency. Then, it is necessary to form the recesses between the tabs by laser cutting, these recesses having to present on their contour the equivalent of the flaps 12, 13. The realization of such a single-piece cowling is very difficult and therefore expensive.
  • the aim of the invention is to overcome these drawbacks and to propose a shroud sufficiently resistant to vibratory stresses, respecting the aerodynamic criteria for separating the flow while having a maximum cross-section for the passage of the combustion stream 6, and which can be realized simply, at low price.
  • the invention relates to an annular combustion chamber of a gas turbine engine, with an outer annular wall and an inner annular wall, comprising an upstream fairing for separating the gas flow entering the chamber into a flow of gas. combustion and a bypass flow of the inlet of the chamber, the fairing comprising an annular wall forming a cap, which comprises a downstream portion of attachment to a wall of the chamber and an upstream portion forming an edge of the flow passage section characterized in that the upstream portion is extended into at least one additional downstream fixing portion to the wall of the chamber.
  • the annular wall forming a cap which is fixed, on the one hand, at its downstream fixing portion, on the other hand, at the additional downstream fastening portion secured to its upstream portion, is stiffened, which increases the frequency of its resonance modes, which do not overlap with the vibration frequencies to which the flange is subjected.
  • the effect of cantilever is attenuated.
  • such a cap is mechanically strong, which avoids the disadvantages associated with the presence of a rod, while it allows the formation of the fairing, separation of the air flow upstream of the chamber, in a cap external and an inner cap, thus providing an optimal section of flow of the combustion stream.
  • downstream fixing portion of the cap is fixed on the outside of the wall of the chamber and the additional downstream fixing portion of the cap is fixed on the inside of the wall of the chamber.
  • the combustion chamber having a chamber bottom the additional downstream fixing portion is attached to a bottom flange of the chamber, which is fixed to the wall of the chamber on its inner side.
  • the attachment of the downstream fixing portion of the cap, the combustion chamber and the additional downstream fixing portion of the cap is implemented by fixing bolts.
  • the fixing of the flange of the chamber bottom is also implemented by the fixing bolts.
  • the additional downstream fixing portion comprises a downstream wall with a downstream fixing portion to the wall of the chamber.
  • this downstream wall has recesses.
  • the additional downstream fixing portion comprises fixing lugs, extending from the upstream edge, comprising a downstream fixing portion to the wall of the chamber.
  • the additional downstream fixing portion comprises reinforcing tabs, connected by a downstream flange which supports fastening tabs to the wall of the chamber.
  • the invention also relates to an annular wall forming a cap of the upstream fairing of the combustion chamber presented above.
  • the invention further relates to a gas turbine engine, comprising the combustion chamber shown above.
  • annular wall forming the outer cap of the upstream fairing of the combustion chamber which is in accordance with the invention, because it is the one that is the most subject to vibratory stresses.
  • the invention also applies to the inner cap.
  • the invention is here described in connection with a turbojet, but it goes without saying that it applies to any gas turbine engine having a combustion chamber.
  • annular wall forming the outer cap 9 of the fairing of the combustion chamber is in accordance with the invention, the annular wall forming an inner cap being in accordance with the caps of the art. previous, because it is the outer cap that is most subject to vibration constraints. It goes without saying that the inner cap can also be provided according to the invention, by simple transposition to the inner cap, characteristics of the outer cap.
  • the elements of the similar turbojet engine will be designated by the same references as in FIG. 1.
  • the upstream fairing 9 of the combustion chamber 1, comprising an external cap and an internal cap. is always designated by the reference “9".
  • the outer cap 20, 20 ', 20 is in the form of a shaped sheet of constant thickness (it is thus less expensive and This sheet may be in any suitable material, for example the same material as the walls of the combustion chamber, in this case an alloy based on nickel or cobalt.
  • the outer cap 20, 20 ', 20 “comprises an upstream annular wall 21 for separating the primary gas flow into a combustion stream 6 and a bypass flow 7, here external, from the inlet of the combustion chamber 1.
  • This upstream wall 21 has a surface similar to that of the caps of the prior art, shaped for a good separation of the primary gas flow.
  • the upstream wall 21 On its downstream and outer side, the upstream wall 21 has a downstream portion 22 for attachment to the outer wall 31 of the combustion chamber 1, here on its outer side.
  • This downstream portion 22 is here planar and obtained by folding the sheet on the downstream side, in the same way as in the prior art. It comprises holes 23 for passing a bolt, not shown, for its attachment to the outer wall 31 of the combustion chamber 1, which has corresponding holes 33 for the passage of the fixing bolts.
  • the upstream wall 21 of the outer cap 20, 20 ', 20 "comprises an upstream portion 24 folded downstream, called upstream edge 24, forming an edge of the passage section of the combustion stream. 6, in this case the outer edge of this section.
  • This upstream portion 24 extends, on the downstream side, into an additional portion 25 of attachment to a wall of the combustion chamber 1, in this case the outer wall 31, which will be called additional downstream fixing portion 25.
  • the additional downstream fixing portion 25 comprises a downstream annular wall 26, which extends downstream of the upstream wall 21.
  • This downstream wall 26 extends from the upstream edge 24, severally with it, in this case in one piece with him. More specifically, from the upstream edge 24 folded downstream, extends a flat portion 27, then a second edge 28 folded outwardly, from which extends outwardly and downstream the downstream wall 26, downstream of the upstream wall 21.
  • This downstream wall 26 has a downstream fixing portion 29, flat, folded downstream, here parallel to the downstream fixing portion 22 of the cap 20 integral with the upstream wall 21 and located therein relative thereto.
  • the downstream fixing portion 29 of the downstream wall 26 has holes 30 for passing a bolt, not shown, for its attachment to the outer wall 31 of the chamber 1, each hole being coaxial with a corresponding hole 23 of the downstream fixing portion 22 of the upstream wall 21.
  • the downstream fixing portion 29 of the downstream wall 26 is fixed to the outer wall 31 of the combustion chamber 1, on its inner side. More specifically, it is attached to a flange 34 of the chamber bottom 2, on its inner side, itself directly attached to the inner surface of the outer wall 31 of the combustion chamber 1.
  • This flange 34 has corresponding holes 35 for the passage of the fixing bolts.
  • Each fastening bolt passes from the outside to the inside, and thus participates in fixing the downstream fixing portion 22 of the upstream wall 21 of the cap 20, of the outer wall 31 of the combustion chamber 1, the flange 34 of the chamber bottom 2 and the downstream fixing portion 29 of the downstream wall 26 of the cap 20.
  • the fixing of the outer cap 20 is here provided, on the one hand, on the outer side of the outer wall 31 of the combustion chamber 1, as regards the downstream fixing portion 22 of the upstream wall 21, on the other hand on the inner side of the outer wall 31 of the combustion chamber 1, with regard to the downstream fixing portion 29 of the downstream wall 26.
  • any other arrangement may be provided, in which the outer cap 20 is fixed to the outer wall 31 of the chamber 1, on the one hand, at the downstream fixing portion 22 of its upstream wall 21, on the other hand, at its further downstream fixing portion 25 extending its upstream edge 24.
  • the fixing of these parts also contributes to the fixing of the flange 34 of the chamber bottom 2.
  • the fixing is done here with the help of bolts, but any other method of fixing can be provided, for example by welding, riveting, ...
  • the downstream wall 26 has recesses 36, distributed along its circumference, in order to reduce its mass. But the downstream wall 26 can also be full. In this case, the rigidity and the mechanical strength of the outer cap 20 are increased, whereas in the event of ingestion of a foreign body that would hit the upstream wall 21 and cause a break, the downstream wall 26 can fill a emergency wall function.
  • the rigidity of the outer cap 20 is increased, which implies the displacement of the frequency values of its resonance modes. , which are thus remote from the vibratory frequencies to which the outer cap 20 is subjected.
  • the outer cap 20 is therefore subjected to lower vibratory forces and has, moreover, a greater overall strength. His dynamic behavior is greater. Cantilever effects are mitigated.
  • the aerodynamic function of separation of the primary gas flow is also preserved, since the surface that it encounters - the upstream surface of the upstream wall 21 - is the same as for the outer caps 20 of the prior art.
  • the shroud 9 is also formed of two caps 20, 11, which allows an optimal passage section for the combustion stream 6.
  • the additional downstream fixing portion 25 comprises a plurality of fastening tabs 37, also forming reinforcements, which extend from the upstream edge 24 of the outer cap 20 ', jointly and severally. with it, in this case in one piece with him. More precisely, from the upstream edge 24 folded downstream, extends a flat portion 27, then a second edge 28 folded symmetrically to the upstream edge 24, from which extend outwardly and downstream the tabs 37, downstream of the upstream wall 21 of the outer cap 20 '.
  • the tabs 37 are distributed regularly angularly along the circumference of the second edge 28, or downstream inner edge 28, to the right of the holes 23 of the downstream fixing portion 22 of the outer cap 20 'integral with its upstream wall 21.
  • Each leg fastening 37 comprises a downstream portion 38 for fastening, flat, folded upstream, here parallel to the downstream fastening portion 22 of the upstream wall 21 of the cap 20 ', and located on the inside with respect to this this.
  • the downstream fastening portion 38 of each fixing lug 37 has a hole 39 for the passage of a bolt, not shown, for fixing the lug 37 to the outer wall 31 of the combustion chamber 1, coaxial with a hole 23. corresponding to the downstream fixing portion 22 of the upstream wall 21.
  • the fixing lugs 37 are fixed at their downstream fixing portion 38 to the outer wall 31 of the combustion chamber 1, on its inner side. More specifically, they are fixed to the flange 34 of the chamber bottom 2, on its inner side, itself directly attached to the inner surface of the outer wall 31 of the combustion chamber 1.
  • This flange 34 has corresponding holes 35 for the passage of the fixing bolts.
  • Each fixing bolt passes from the outside to the inside, and thus participates in fixing the downstream fastening portion 22 of the upstream wall 21 of the cap 20 ', of the outer wall 31 of the combustion chamber 1, the flange 34 of the chamber bottom 2 and the downstream fixing portion 38 of the fixing lugs 37 of the cap 20 '.
  • the fixing of the outer cap 20 ' is here provided, on the one hand, on the outer side of the outer wall 31 of the combustion chamber 1, as regards the downstream fixing portion 22 of the upstream wall 21, of on the other hand, on the inner side of the outer wall 31 of the combustion chamber 1, with regard to the downstream fixing portion 38 of the fixing lugs 37.
  • any other arrangement may be provided, in which the cap external 20 'is fixed to the outer wall 31 of the chamber 1, on the one hand, at the downstream fixing portion 22 of its upstream wall 21, on the other hand, at its further downstream fixing portion 25 extending its upstream edge 24.
  • the fixing of these parts also contributes to the fixing of the flange 34 of the chamber bottom 2.
  • the fixing is done here with the help of bolts, but any other mode fastening can be provided, for example by welding, riveting, ...
  • the rigidity of the outer cap 20' is increased and the cap 20 'is less subject to the constraints vibration. It is also more resistant and its dynamic behavior is greater. Cantilever effects are mitigated.
  • the aerodynamic separation function of the primary gas flow is also preserved, with an optimal passage section for the combustion flow 6. It is noted that the discrete distribution of the fixing lugs 37 allows a more simple implementation of the outer cap. 20 ', with respect to the first embodiment wherein the downstream fixing portion 29 is continuous.
  • the rigidity of the additional downstream fixing portion 25 is however less than in the first embodiment.
  • the additional downstream fastening portion 25 comprises a plurality of lugs 40, forming reinforcements, which extend from the upstream edge 24 of the outer cap 20 ", solidarily with this one. ci, in this case in one piece with him, and which are interconnected at their outer end downstream by an annular flange 41 supporting a plurality of tabs 42, or scallops, fastening extending upstream. precisely, from the upstream edge 24 folded downstream, extends a flat portion 27, then a second edge 28 folded symmetrically to the upstream edge 24, from which extend outwardly and downstream the tabs 40, downstream of the upstream wall 21 of the outer cap 20 ".
  • the tabs 40 support and are connected by an annular flange 41 folded upstream.
  • This annular rim 41 supports the plurality of fixing lugs 42, which are flat and extend upstream, here parallel to the downstream fixing portion 22 of the upstream wall 21 of the cap 20 ", and are located at interior with respect to it.
  • the reinforcing tabs 40 are distributed regularly angularly along the circumference of the second edge 28.
  • Each fastening tab 42 is located angularly between two reinforcing tabs 40, in this case equidistant from these reinforcing tabs 40, and is located to the right of a hole 23 of the downstream fixing portion 22 of the upstream wall 21.
  • Each fixing lug 42 has a hole 43 for passing a bolt, not shown, for fixing the lug 42 to the outer wall 31 of the combustion chamber 1, coaxial with a corresponding hole 23 of the downstream fixing portion 22 of the upstream wall 21.
  • the fastening tabs 42 are fixed to the outer wall 31 of the combustion chamber 1, on its inner side. More specifically, they are fixed to the flange 34 of the chamber bottom 2, on its inner side, itself directly attached to the inner surface of the outer wall 31 of the combustion chamber 1.
  • This flange 34 has corresponding holes 35 for the passage of the fixing bolts.
  • the fixing of the outer cap 20 " is here provided, on the one hand, on the outer side of the outer wall 31 of the combustion chamber 1, as regards the downstream fixing portion 22 of the upstream wall 21, of on the other hand, on the inner side of the outer wall 31 of the combustion chamber 1, as regards the fastening tabs 42.
  • any other arrangement may be provided, in which the outer cap 20 "is attached to the outer wall 31 of the chamber 1, on the one hand, at the downstream fixing portion 22 of its upstream wall 21, on the other hand, at its further downstream fixing portion 25 extending its upstream edge 24.
  • the fixing of these parts also contributes to the fixing of the flange 34 of the chamber bottom 2.
  • the fixing is done here with the help of bolts, but any other method of fixing can be provided, for example by welding, riveting, ...
  • this third embodiment is somehow intermediate between the first two embodiments, with a fixation by tabs distributed discretely, which facilitates the introduction of the cap 20 ", but a more rigid structure than in the case of the second embodiment, because of the flange 41 connecting the reinforcing tabs 40.
  • the angular alternation of the reinforcing tabs 40 and the attachment tabs 42 provides a better distribution of efforts.
  • the outer cap comprises a downstream portion 22, integral with its upstream wall 21, for attachment to the outer wall 31 of the combustion chamber 1, and an additional downstream fixing portion 25 , integrally extending the upstream edge 24 of its upstream wall 21, fixing to the same outer wall 31.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Superstructure Of Vehicle (AREA)
  • Cylinder Crankcases Of Internal Combustion Engines (AREA)
EP06121135.5A 2005-09-23 2006-09-22 Brennkammer mit Verkleidung für eine Gasturbine Active EP1767858B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0552847A FR2891351B1 (fr) 2005-09-23 2005-09-23 Chambre de combustion de moteur a turbine a gaz avec carenage

Publications (2)

Publication Number Publication Date
EP1767858A1 true EP1767858A1 (de) 2007-03-28
EP1767858B1 EP1767858B1 (de) 2017-07-26

Family

ID=36218594

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06121135.5A Active EP1767858B1 (de) 2005-09-23 2006-09-22 Brennkammer mit Verkleidung für eine Gasturbine

Country Status (4)

Country Link
US (1) US7617688B2 (de)
EP (1) EP1767858B1 (de)
FR (1) FR2891351B1 (de)
RU (1) RU2382946C2 (de)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8973365B2 (en) * 2010-10-29 2015-03-10 Solar Turbines Incorporated Gas turbine combustor with mounting for Helmholtz resonators
US9976746B2 (en) * 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
DE102015224990A1 (de) * 2015-12-11 2017-06-14 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zur Montage einer Brennkammer eines Gasturbinentriebwerks
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
RU204676U1 (ru) * 2020-12-10 2021-06-04 Публичное Акционерное Общество "Одк-Сатурн" Кольцеобразный конический элемент воздушного завихрителя камеры сгорания

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564171A1 (de) * 1992-03-30 1993-10-06 General Electric Company Einteiliger Aufsatz für eine Dualringbrennkammer
EP1251312A2 (de) * 2001-04-17 2002-10-23 General Electric Company Zerlegbarer Aufsatz für eine Gasturbinenbrennkammer
EP1265031A1 (de) * 2001-06-06 2002-12-11 Snecma Moteurs Befestigung von metallischen Aufsätzen auf CMC-Turbomachinenbrennkammerwänden
EP1398571A2 (de) * 2002-09-10 2004-03-17 General Electric Company Hergestellter Aufsatz für eine Dualringbrennkammer einer Gastubine und Verfahren zu seiner Herstellung

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0564171A1 (de) * 1992-03-30 1993-10-06 General Electric Company Einteiliger Aufsatz für eine Dualringbrennkammer
EP1251312A2 (de) * 2001-04-17 2002-10-23 General Electric Company Zerlegbarer Aufsatz für eine Gasturbinenbrennkammer
EP1265031A1 (de) * 2001-06-06 2002-12-11 Snecma Moteurs Befestigung von metallischen Aufsätzen auf CMC-Turbomachinenbrennkammerwänden
EP1398571A2 (de) * 2002-09-10 2004-03-17 General Electric Company Hergestellter Aufsatz für eine Dualringbrennkammer einer Gastubine und Verfahren zu seiner Herstellung

Also Published As

Publication number Publication date
US20070074520A1 (en) 2007-04-05
EP1767858B1 (de) 2017-07-26
US7617688B2 (en) 2009-11-17
RU2382946C2 (ru) 2010-02-27
FR2891351B1 (fr) 2007-12-07
FR2891351A1 (fr) 2007-03-30
RU2006133868A (ru) 2008-03-27

Similar Documents

Publication Publication Date Title
EP1881179B1 (de) Wandbelüftungssystem für die Brennkammer einer Strömungsmaschine
CA2535304C (fr) Carenage de chambre de combustion de turbomachine
EP1767858B1 (de) Brennkammer mit Verkleidung für eine Gasturbine
FR2961251A1 (fr) Moyeu de carter intermediaire pour turboreacteur d'aeronef comprenant des moyens d'evacuation de debris ameliores
FR3040076A1 (fr) Ensemble moteur pour aeronef comprenant une structure primaire de mat d'accrochage equipee d'une extension de caisson comprenant deux parties en forme globale d'arceau
EP2234886B1 (de) Gondel für ein turbojet-triebwerk
EP2048324B1 (de) Turbinenstator für Turbotriebwerk eines Luftfahrzeugs, der mit einer Schwingungsdämpfungsvorrichtung ausgestattet ist
EP2022973A1 (de) Äußeres Gehäuse eines Fan-Laufrades in einer Strömungsmaschine
FR2992353A1 (fr) Ensemble forme d'un cone d'echappement et d'un carter d'echappement dans un moteur a turbine a gaz
FR3027340B1 (fr) Disque aubage monobloc comportant un moyeu pourvu de fentes radiales delimitant des embases de pales
EP2247503B1 (de) Struktur zur anbringung eines turbostrahlmotors
CA2842871A1 (fr) Cone d'ejection pour turboreacteur d'aeronef
FR2948635A1 (fr) Assemblage pour aeronef comprenant un mat d'accrochage de turbomachine dont les moyens d'attache sur la voilure sont agences en t
CA2619422C (fr) Chambre de combustion d'une turbomachine
FR3005693A1 (fr) Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie
EP3587274A1 (de) Gondel einer antriebseinheit eines luftfahrzeugs, die eine vielzahl von dämpfungselementen zwischen einem vorderteil und einem hauptteil umfasst, und entsprechende antriebseinhait eines luftfahrzeugs
EP3772458B1 (de) Vorderer teil der gondel einer flugzeug-antriebsgruppe mit einem schutzschild vor seinen versteifungsrahmen
WO2022096825A1 (fr) Fixation d'un cône d'éjection au carter d'échappement d'une turbomachine
FR3097903A1 (fr) Carter pour une turbomachine d’aeronef
CA2780548C (fr) Structure annulaire metallique de raccord pour turbomachine d'aeronef
FR2910597A1 (fr) Carenage pour fond de chambre de combustion
FR3054527B1 (fr) Ensemble pour aeronef comprenant un bouclier de protection contre un eclatement moteur, monte sur le carter d'un module de turbomachine
WO2022096832A1 (fr) Fixation d'un cône d'éjection dans une turbine de turbomachine
FR2887615A1 (fr) Carenage circulaire de chambre de combustion de turbomachine
WO2018130765A1 (fr) Chambre de combustion pour 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: 20060922

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

AKX Designation fees paid

Designated state(s): DE FR GB IT

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SAFRAN AIRCRAFT ENGINES

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

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

Free format text: STATUS: GRANT OF PATENT IS INTENDED

INTG Intention to grant announced

Effective date: 20170410

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): DE FR GB IT

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: 602006053112

Country of ref document: DE

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: DE

Ref legal event code: R026

Ref document number: 602006053112

Country of ref document: DE

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

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

Free format text: ORIGINAL CODE: 0009299OPPO

26 Opposition filed

Opponent name: UNITED TECHNOLOGIES CORPORATION

Effective date: 20180426

R26 Opposition filed (corrected)

Opponent name: UNITED TECHNOLOGIES CORPORATION

Effective date: 20180426

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

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

Free format text: ORIGINAL CODE: EPIDOSNOBS3

PLCK Communication despatched that opposition was rejected

Free format text: ORIGINAL CODE: EPIDOSNREJ1

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

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: RAYTHEON TECHNOLOGIES CORPORATION

Effective date: 20180426

APBQ Date of receipt of statement of grounds of appeal recorded

Free format text: ORIGINAL CODE: EPIDOSNNOA3O

APBY Invitation to file observations in appeal sent

Free format text: ORIGINAL CODE: EPIDOSNOBA2O

REG Reference to a national code

Ref country code: DE

Ref legal event code: R100

Ref document number: 602006053112

Country of ref document: DE

APBU Appeal procedure closed

Free format text: ORIGINAL CODE: EPIDOSNNOA9O

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

Ref country code: IT

Payment date: 20230822

Year of fee payment: 18

PLBN Opposition rejected

Free format text: ORIGINAL CODE: 0009273

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

Free format text: STATUS: OPPOSITION REJECTED

27O Opposition rejected

Effective date: 20230907

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

Ref country code: DE

Payment date: 20240820

Year of fee payment: 19

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

Ref country code: GB

Payment date: 20240821

Year of fee payment: 19

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

Ref country code: FR

Payment date: 20240820

Year of fee payment: 19