EP1840466A1 - Anordnung von Verdünnungsöffnungen in der Brennkammerwand einer Turbomaschine - Google Patents

Anordnung von Verdünnungsöffnungen in der Brennkammerwand einer Turbomaschine Download PDF

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Publication number
EP1840466A1
EP1840466A1 EP07075224A EP07075224A EP1840466A1 EP 1840466 A1 EP1840466 A1 EP 1840466A1 EP 07075224 A EP07075224 A EP 07075224A EP 07075224 A EP07075224 A EP 07075224A EP 1840466 A1 EP1840466 A1 EP 1840466A1
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EP
European Patent Office
Prior art keywords
combustion chamber
edge
downstream
opening
upstream
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
EP07075224A
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English (en)
French (fr)
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EP1840466B1 (de
Inventor
Romain Biebel
Luc Daguenet
Denis Sandelis
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication of EP1840466A1 publication Critical patent/EP1840466A1/de
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    • 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
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • the invention relates to the field of turbine engine combustion chambers and more specifically to the configuration of the dilution air intake openings and the cooling air passage perforations arranged in the walls of the flame tube or in any element of combustion chamber wall.
  • FIG. 1B shows an axial sectional view of a turbomachine combustion chamber 1 according to the state of the art, as described in the patent document.
  • EP-A-0 743 490 in the name of the plaintiff.
  • the combustion chamber 1 is formed of two concentric tubular side walls 3 constituting a flame tube (extending in the longitudinal direction L-L of the chamber, parallel here to the axis X-X of the turbomachine).
  • the chamber is closed at one end, upstream side M, by an annular bottom wall 4 where there are fuel injectors 6 and combustion air inlet 7, the combustion of which generates a flow of combustion gas.
  • the chamber is terminated at the other end, downstream side V, by an annular orifice 5 for exhausting the stream G of burnt gases to the rotary gas turbine of the turbomachine.
  • openings 8 or dilution holes are arranged in the side walls 3 of the chamber 1, to mix a complementary fresh air flow A in the flue gas stream G which is propagated towards the downstream V of the chamber 1.
  • This addition of fresh air A serves to dilute the hot gases G, reduce their temperature, cool the walls and increase the proportion of air in the gas mixture. This is to try to optimize the stoichiometry of the combustion air / fuel mixture, to burn the unburnt and to reduce the emissions of NOx-nitrogen oxides, with a view to improving the combustion of the gaseous mixture G (in particular by prolonging , sure the whole extent of the chamber, the combustion of the initially too rich mixture, on ignition).
  • the dilution air inlet openings 8 pierced in the side walls 3 are arranged along the circumference of the tubular walls at a central axial position between the bottom M and the orifice 5 of the chamber 1.
  • the opening 8 ' is obtained by simple normal drilling (with a forest or by punch cutting) of a cylindrical bore with straight edges, perpendicular to the wall 3 of the chamber 1.
  • the opening 8' can also be performed by laser.
  • the walls 3 of the chamber 1 comprise perforations 9, of tiny dimensions. These micro-perforations are distributed over the extent of these metal walls 3, with a preferential concentration around the dilution openings 8 '.
  • These perforations (in English “impingement holes”) are used for the injection of micro-air flow whose primary role is to cool the metal mass of the side walls 3 to enable them to withstand very high temperatures (over 1000 °) C) Hot gases G in the combustion chamber 1. It is appropriate here to distinguish these micro-cooling air injection perforations, referred to herein as cooling perforations, with respect to relatively large intake openings.
  • dilution air here called dilution openings.
  • the object of the invention is to overcome the disadvantages of current solutions and to make a combustion chamber with dilution openings to optimize the admission of the air flow while avoiding, as far as possible, the turbulence and the formation of hot spots, detrimental to the thermo-mechanical behavior of the combustion chamber and its service life.
  • the invention relates to a turbomachine annular combustion chamber having a bottom wall, extending transversely to a longitudinal axis of extension of the chamber, and side walls extending longitudinally from the bottom wall, located upstream of the chamber, up to a combustion gas flow ejection orifice, located downstream of the chamber, the side walls comprising at least one row of dilution air intake openings of the flow of combustion gas, with the particularity that at least one dilution opening has an upstream edge projecting towards the inside of the chamber and an asymmetrical downstream edge of the upstream edge with respect to a plane transverse to the wall, the light of the opening having an axis oriented in a direction oblique to the wall, facing inwards and downstream of the chamber.
  • the downstream edge protrudes towards the outside of the chamber.
  • the downstream edge is less salient than the upstream edge.
  • downstream edge is substantially rectilinear.
  • the upstream edge is folded in a direction oblique with respect to the side wall and facing inwards and downstream of the chamber.
  • downstream edge is folded in a direction oblique with respect to the side wall and oriented towards the outside and upstream of the chamber.
  • the bore of the opening may comprise substantially cylindrical walls.
  • the opening has an elliptical section at the surface of the side wall.
  • the elliptical section of the opening may have a major axis directed in a longitudinal direction of the chamber from upstream to downstream.
  • the major axis of the ellipse of the opening can be directed substantially transversely.
  • the projecting edge of the opening extends and is smoothed transversely and / or the protrusion of the upstream projecting edge decreases progressively from upstream to downstream.
  • At least one projecting edge has an arch form.
  • the upstream edge forms an arcade projecting inwards and downstream of the chamber and / or the downstream edge forms an arcade projecting outwards and upstream of the chamber.
  • the arc or openings of the opening are elongated transversely.
  • the side wall has a plurality of cooling air passage perforations.
  • cooling perforations are provided on at least one edge and / or in an area around the edge of the dilution opening.
  • cooling perforations may be provided on the downstream periphery of the dilution opening.
  • the periphery of the opening has a higher density of cooling perforations than the rest of the side wall of the chamber.
  • the cooling perforations are directed obliquely with respect to the surface of the side wall, in particular the cooling perforations are oriented obliquely in the direction going from upstream to downstream, following the passage of the air from the outside to the inside of the room.
  • the invention applies to a turbomachine provided with such a combustion chamber.
  • the invention also relates to a side wall element for forming such a combustion chamber, the wall element comprising at least one dilution opening having an upstream edge projecting towards the inner side of the wall and an asymmetrical downstream edge of the upstream edge. relative to a plane transverse to the wall, the aperture lumen having an axis oblique to the wall, facing inwards and downstream.
  • the invention may also relate to a turbomachine combustion chamber sidewall element having an upstream gas combustion zone and a downstream combustion gas ejection port, the sidewall having inlet openings of dilution air of the flue gas stream, the wall element having at least one dilution opening having an upstream edge projecting towards the inner side of the wall and an asymmetric downstream edge of the upstream edge with respect to a transverse plane at the wall, the opening lumen having an axis oblique to the wall, facing inwards and downstream.
  • FIGS. 2, 3 and 4 show three embodiments of dilution air intake openings 10, 20, 30 in a chamber side wall element 3. combustion 1 according to the invention, these three embodiments showing that the dilution opening has asymmetrical edges 11/12, 21/22 and 31/32. More precisely, contrary to the state of the art, the upstream edge 11/21/31 and the downstream edge 12/22/32 of the opening are not symmetrical with respect to a plane TT transverse to the side wall 3.
  • the combustion chamber side walls are made of metal materials, especially refractory metal alloys capable of withstanding creep and oxidation and this, at very high temperatures (especially higher than 1000 ° C) prevailing inside a combustion chamber.
  • the wall elements presented here can be made from rolled and pressed nickel-base metal sheets, in particular an alloy of nickel, chromium and iron in which nickel predominates, such as Hastelloy X, or a cobalt-based alloy, especially combining cobalt, chromium, nickel, tungsten and where cobalt is the majority, such as HA 188.
  • the dilution openings 10, 20, 30 made in a chamber wall 3 according to the invention comprise an upstream edge 11, 21 or 31 projecting towards an inner side of the chamber 1, and a downstream edge 12, 22 or 32 not prominent towards the interior of the chamber 1.
  • the protrusion of the upstream edge 11, 21, 31 is preferably directed obliquely HH with respect to the wall 3, the upstream edge 11, 21, 31 being folded down according to a oblique direction HH oriented inwardly 1 and downstream V of the chamber, the direction HH being substantially inscribed in the longitudinal plane LL of the chamber 1.
  • the shape of the downstream edge 12, 22, 32 of the opening 10, 20, 30 may be the subject of several variant embodiments, as illustrated in the figures.
  • the downstream periphery 12 of the opening 10 has a straight edge, that is to say a straight edge 12 that does not project, inscribed in the extension of the side wall 3 (flat or rectilinear edge).
  • the opening 20 has a downstream edge 22 slightly projecting towards the outside of the chamber 1, the downstream edge 22 (facing outwards) being less protruding than the edge upstream 21 (turned inward).
  • the opening 30 has a downstream edge 32 projecting outwardly from the chamber 1, the downstream edge 32 being here substantially projecting outwards as the upstream edge 31 is projecting inwards 1.
  • the edges 31 and 32 of the opening may be symmetrical with respect to a central point O of the opening 30, without however being symmetrical with respect to a plane TT transverse to the wall 3.
  • An advantage of an opening according to the invention having a downstream edge 22 or 32 protruding outwards is to be able to capture and divert the flow A of fresh air that runs along the outside of the walls 3 of the chamber 1 and therefore d to accentuate the flow D of intake of fresh air into the chamber 1. Depending on the prominence of the downstream edge 22 or 32 towards the outside, this accentuation will be more or less marked.
  • the downstream edge may, however, be slightly protruding towards the inside of the chamber, the downstream edge being less protruding towards the inside than the upstream edge. Because the downstream edge is less protruding than the upstream edge, it no longer forms a prominent ridge inside the chamber and is no longer exposed to the incidence of hot gas flow.
  • the opening of the wall thus has an upstream edge directed obliquely in the direction of the hot gas flow.
  • the upstream edge is folded down and has a reduced prominence inside the chamber relative to a 'flanged' hole of the prior art.
  • the flow of gas arrives with a oblique incidence on the upstream edge of the dilution opening according to the invention.
  • the oblique orientation of the upstream edge protruding inside the chamber limits the turbulence of the hot gas flow in the wake downstream of the opening.
  • downstream edge does not protrude symmetrically to the upstream edge inside the chamber, which inhibits the formation of a vortex on the upstream and downstream edges of the opening.
  • the advantage of the opening 10, 20, 30 according to the invention is to reduce the possibility of turbulence formation on the downstream edge 12,22,32 and to inhibit the appearance of hot spots in the wake of the opening.
  • Another advantage of the invention is that it makes it possible to implant micro-perforations 19, 29, 39 for the injection of the flow R of cooling air into the zone immediately near the edge of the opening 10, 20, 30 .
  • Increasing the cooling efficiency R of the walls can make it possible to improve the service life of the combustion chamber 1 and reduce its maintenance frequency.
  • FIG. 5 illustrate, from different angles of view, the shape of a dilution opening 10 arranged according to the first embodiment of the invention, in which the dilution opening 10 comprises an upstream edge 11 projecting towards the interior of the chamber, while the downstream edge 12 does not protrude either inwardly or outwardly of the chamber.
  • the opening 10 From an internal point of view 5A of the chamber, the opening 10 has an upstream projecting edge and a straight downward or trailing edge, that is to say that the wall 12 downstream of the opening 10 is flat until 'at the edge of the latter.
  • the wall at the downstream edge 12 of the opening is preferably flat or more generally rectilinear.
  • the opening 10 From an outside point of view 5B, the opening 10 has an upstream rim 11 entering and a straight or smooth downstream edge 12.
  • downstream edge 12 is substantially non-prominent with respect to the adjacent areas of the wall 3 which immediately surround it and generally it is less prominent than the ridge of the upstream edge 11.
  • the upstream edge 11 of the opening 10 projects towards the inside of the chamber and forms a folded or curved wall portion of the inner side of the wall 3.
  • the wall portion of the upstream edge 12 is folded according to a oblique direction HH relative to the surface of the wall 3 of the chamber.
  • the folded wall portion of the upstream edge 12 preferably extends obliquely at an acute angle ( ⁇ less than 90 °) facing inwards and downstream of the chamber.
  • the dilution aperture 10 has an upstream edge 11 in the form of an arcade 13 or skylight 13 of the "play skylight” type.
  • curved that is to say in the form of a curved arch arch 13 whose lateral flanges 15 are progressively softened to melt in the plane of the wall 3.
  • the arched arch 13 formed by the upstream edge 11 relies on generators HH oblique with respect to the wall 3 and oriented towards the inside and the downstream side of the chamber
  • the light of the opening 10 is oriented obliquely inwards and downstream by relative to the wall 3 of the chamber
  • the downstream edge 12 of the opening 10, i.e., about half the circumference of the downstream side of the opening 10, has no prominence, either on the inside or outer side.
  • such a form of dilution opening 10 makes it possible to implant micro-perforations 19 for the passage of cooling air around the opening 10 and as close as possible to the edge 12 of the opening 10.
  • the bore of the hole of the dilution opening itself has an elliptical cross section, in particular with a large axis directed transversely.
  • the orifice of the opening may have a transverse dimension that is as wide as, or even wider than, its longitudinal dimension at the surface of the wall 3.
  • FIG. 6 illustrate, from different angles of view, the shape of a dilution opening 30 arranged according to the third embodiment of the invention.
  • the dilution opening 30 has an upstream edge 31 in the form of an arcade or skylight of the type "curved skylight”, folded obliquely inwardly 1 of the chamber, to which is added a downstream edge 32 in the form of arcade or “window with curved plays", but folded obliquely towards the outside of the chamber 1.
  • the downstream edge 32 like the upstream edge 31, has a curved arc shape whose lateral edges 34 are progressively softened until they melt in the plane of the wall 3.
  • the inwardly oriented arch 31 formed by the upstream edge and the outwardly oriented arch 32 formed by the downstream edge may abut generatrices parallel to the H-H axis as shown in views 6A and 6C.
  • the vaults may follow non-parallel generatrices (not shown).
  • an opening having an upstream edge 31 projecting internally 1 towards downstream V according to the pivot angle (angle ⁇ less than 90 ° preferably) and a downstream edge 32 protruding outwardly upstream M also follows the pivot angle ⁇ .
  • the opening 30 then has a center of symmetry O although the upstream 31 and downstream edges 32 are antisymmetric with respect to a transverse plane T-T perpendicular to the wall 3.
  • the angle ⁇ is an acute angle. It can be of the order of 20 ° to 60 °, preferably chosen between 30 ° and 50 °, typically about 40 ° -45 °.
  • such forms of openings are obtained by matrix stamping.
  • the orifice formed on the surface of the wall 3 has an elliptical cross section whose major axis is oriented longitudinally in the direction LL
  • the bore of the hole of the opening 30 has an elliptical cross-section with a major axis E arranged in the transverse direction. This makes it possible to obtain an orifice 30 presenting, on the surface of the wall 3, a transverse dimension E as wide, or even much wider than its longitudinal dimension LL.
  • the arched arcade 32 formed by the downstream edge projecting outwards and upstream M with respect to the chamber 1, advantageously makes it possible to capture, in the manner of a scoop or a trough, the flow A fresh air circulates outside, along the wall 3.
  • the flow A of fresh air circulating around the chamber 1 from upstream to downstream can thus be deflected easily and almost without loss of pressure (no loss of load) to the interior of the chamber 1, which facilitates its admission.
  • the flow D of fresh air admitted can go along the wall 3 by forming a laminar flow which cools the wall 3 and advantageously isolates this wall. ci of the flow G of hot gases.
  • the flow D of fresh air admitted is advantageously folded by the roof of the upstream edge 31 and is further plated under the influence of the flow G of hot gases.
  • such a dilution opening 30 provided with an upstream edge 31 protruding internally and a downstream edge 32 protruding outwardly, makes it possible to drill micro-perforations 39 for injecting air from cooling (English “impingement holes”) closer to the edge of the dilution opening 30.
  • Cooling perforations 35 and 36 can be drilled particularly closer to the periphery of the downstream edge 32 or closer to the periphery of the upstream edge 31.
  • the perforations 35,36,39 of cooling air passage have dimensions of millimeter or sub-millimeter order (in particular of the order of a tenth of a millimeter to a few millimeters, typically 1 ⁇ 2 mm to 2 mm).
  • the cooling perforations are preferably drilled in an oblique direction 1-1 oriented towards the inside 1 and downstream V of the chamber 1.
  • the oblique angle ⁇ of the microphones -perforations R can be different or of the same order of magnitude as the oblique angle ⁇ of the dilution openings D.
  • the angle ⁇ of the cooling perforations may be of the order of a few degrees to several tens of degrees, the angle ⁇ being generally less than 60 ° relative to the normal T-T at the wall.
  • the holes 19,29,35,36,39 of cooling are advantageously pierced by means of laser beam tooling, of wavelength, of energy and of adequate section, according to the usual techniques.
  • the primary role of these perforations is to make the wall permeable to the air so as to remove calories by convection.
  • the dilution apertures 10, 20, 30 having upstanding edges 11, 21, 31 in the form of a softened arch projecting internally and upstanding edges 12, 22, 32 protruding externally can thus be surrounded by multiple micro-cooling perforations 35. 36 disposed closer to the edge of the opening 10 / 20,30 in the area that was likely to present localized hot spots or burns.
  • the invention applies to a turbomachine comprising a combustion chamber 1 according to the invention.
EP07075224.1A 2006-03-30 2007-03-23 Anordnung von Verdünnungsöffnungen in der Brennkammerwand einer Turbomaschine Active EP1840466B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0602744A FR2899315B1 (fr) 2006-03-30 2006-03-30 Configuration d'ouvertures de dilution dans une paroi de chambre de combustion de turbomachine

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EP1840466A1 true EP1840466A1 (de) 2007-10-03
EP1840466B1 EP1840466B1 (de) 2018-10-24

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US (1) US7891194B2 (de)
EP (1) EP1840466B1 (de)
JP (1) JP2007271256A (de)
CN (1) CN101046299A (de)
CA (1) CA2582634C (de)
FR (1) FR2899315B1 (de)
RU (1) RU2354889C2 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013050105A1 (de) * 2011-10-06 2013-04-11 Lufthansa Technik Ag Brennkammer für eine gasturbine
FR3055950A1 (fr) * 2016-09-14 2018-03-16 Safran Helicopter Engines Chambre de combustion pour turbomachine comprenant des moyens pour ameliorer le refroidissement d'une paroi annulaire dans le sillage d'un obstacle
FR3098569A1 (fr) * 2019-07-10 2021-01-15 Safran Aircraft Engines Paroi annulaire pour chambre de combustion de turbomachine comprenant des trous primaires, des trous de dilution et des orifices de refroidissement inclines
EP3475614B1 (de) * 2016-06-22 2023-08-02 General Electric Company Brennkammerbaugruppe für einen turbinenmotor

Families Citing this family (39)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8387397B2 (en) * 2009-01-27 2013-03-05 General Electric Company Flow conditioner for use in gas turbine component in which combustion occurs
US8438856B2 (en) * 2009-03-02 2013-05-14 General Electric Company Effusion cooled one-piece can combustor
ATE554346T1 (de) * 2009-03-16 2012-05-15 Alstom Technology Ltd BRENNER FÜR EINE GASTURBINE UND VERFAHREN ZUR LOKALEN KÜHLUNG VON HEIßEN GASSTRÖMEN, DIE EINEN BRENNER DURCHLAUFEN
US20100269513A1 (en) * 2009-04-23 2010-10-28 General Electric Company Thimble Fan for a Combustion System
US9897320B2 (en) * 2009-07-30 2018-02-20 Honeywell International Inc. Effusion cooled dual wall gas turbine combustors
FR2948988B1 (fr) 2009-08-04 2011-12-09 Snecma Chambre de combustion de turbomachine comprenant des orifices d'entree d'air ameliores
CH703657A1 (de) * 2010-08-27 2012-02-29 Alstom Technology Ltd Verfahren zum betrieb einer brenneranordnung sowie brenneranordnung zur durchführung des verfahrens.
US8590864B2 (en) * 2010-10-21 2013-11-26 Woodward Fst, Inc. Semi-tubular vane air swirler
FR2972027B1 (fr) * 2011-02-25 2013-03-29 Snecma Chambre annulaire de combustion de turbomachine comprenant des orifices de dilution ameliores
US9127551B2 (en) * 2011-03-29 2015-09-08 Siemens Energy, Inc. Turbine combustion system cooling scoop
FR2979416B1 (fr) * 2011-08-26 2013-09-20 Turbomeca Paroi de chambre de combustion
FR2991028B1 (fr) * 2012-05-25 2014-07-04 Snecma Virole de chambre de combustion de turbomachine
US9377199B2 (en) * 2012-12-28 2016-06-28 General Electric Company Methods of reinforcing combustor aperture and related combustor
US9541292B2 (en) 2013-03-12 2017-01-10 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9958161B2 (en) 2013-03-12 2018-05-01 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9127843B2 (en) 2013-03-12 2015-09-08 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US9366187B2 (en) 2013-03-12 2016-06-14 Pratt & Whitney Canada Corp. Slinger combustor
US9228747B2 (en) * 2013-03-12 2016-01-05 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
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WO2015047509A2 (en) * 2013-08-30 2015-04-02 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
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GB201417429D0 (en) 2014-10-02 2014-11-19 Rolls Royce Plc A cooled component
CA2933884A1 (en) * 2015-06-30 2016-12-30 Rolls-Royce Corporation Combustor tile
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US11965653B2 (en) * 2021-06-23 2024-04-23 General Electric Company Dilution air inlets with notched tip and slotted tail for combustor
US11920790B2 (en) 2021-11-03 2024-03-05 General Electric Company Wavy annular dilution slots for lower emissions
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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE488448A (de) *
FR1052475A (fr) * 1952-03-15 1954-01-25 Snecma Chambres de combustion convenant en particulier aux turbines à gaz
FR2081220A1 (de) * 1970-03-19 1971-12-03 Hertel Heinrich
US5528903A (en) * 1992-03-20 1996-06-25 Schneider-Sanchez Ges.M.B.H. Small gas turbine
EP0743490A1 (de) * 1995-04-26 1996-11-20 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind
US5727378A (en) * 1995-08-25 1998-03-17 Great Lakes Helicopters Inc. Gas turbine engine

Family Cites Families (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US2625792A (en) * 1947-09-10 1953-01-20 Rolls Royce Flame tube having telescoping walls with fluted ends to admit air
DE1066385B (de) * 1956-11-21 1959-10-01 Rolls-Royce Limited, Derby (Großbritannien) Brennanlage von Gastufbmenaggregaten
US3134229A (en) * 1961-10-02 1964-05-26 Gen Electric Combustion chamber
US4244178A (en) * 1978-03-20 1981-01-13 General Motors Corporation Porous laminated combustor structure
US4301657A (en) * 1978-05-04 1981-11-24 Caterpillar Tractor Co. Gas turbine combustion chamber
US4527397A (en) * 1981-03-27 1985-07-09 Westinghouse Electric Corp. Turbine combustor having enhanced wall cooling for longer combustor life at high combustor outlet gas temperatures
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
US4944152A (en) * 1988-10-11 1990-07-31 Sundstrand Corporation Augmented turbine combustor cooling
US5220794A (en) * 1988-12-12 1993-06-22 Sundstrand Corporation Improved fuel injector for a gas turbine engine
US5241818A (en) * 1989-07-13 1993-09-07 Sundstrand Corporation Fuel injector for a gas turbine engine
US5174108A (en) * 1989-12-11 1992-12-29 Sundstrand Corporation Turbine engine combustor without air film cooling
US5363644A (en) * 1989-12-21 1994-11-15 Sundstrand Corporation Annular combustor
US5263316A (en) * 1989-12-21 1993-11-23 Sundstrand Corporation Turbine engine with airblast injection
US5261224A (en) * 1989-12-21 1993-11-16 Sundstrand Corporation High altitude starting two-stage fuel injection apparatus
US5150570A (en) * 1989-12-21 1992-09-29 Sundstrand Corporation Unitized fuel manifold and injector for a turbine engine
US5205117A (en) * 1989-12-21 1993-04-27 Sundstrand Corporation High altitude starting two-stage fuel injection
US5277022A (en) * 1990-06-22 1994-01-11 Sundstrand Corporation Air blast fuel injecton system
US5172546A (en) * 1990-11-19 1992-12-22 Sundstrand Corporation Volume enhanced turbine engine combustion zone
US5167122A (en) * 1991-04-30 1992-12-01 Sundstrand Corporation Fuel system for a turbo machine
US5277021A (en) * 1991-05-13 1994-01-11 Sundstrand Corporation Very high altitude turbine combustor
US5317864A (en) * 1992-09-30 1994-06-07 Sundstrand Corporation Tangentially directed air assisted fuel injection and small annular combustors for turbines
US5488829A (en) * 1994-05-25 1996-02-06 Westinghouse Electric Corporation Method and apparatus for reducing noise generated by combustion
US6351949B1 (en) * 1999-09-03 2002-03-05 Allison Advanced Development Company Interchangeable combustor chute
US6494044B1 (en) * 1999-11-19 2002-12-17 General Electric Company Aerodynamic devices for enhancing sidepanel cooling on an impingement cooled transition duct and related method
US6681578B1 (en) * 2002-11-22 2004-01-27 General Electric Company Combustor liner with ring turbulators and related method
US6931862B2 (en) * 2003-04-30 2005-08-23 Hamilton Sundstrand Corporation Combustor system for an expendable gas turbine engine
US8151570B2 (en) * 2007-12-06 2012-04-10 Alstom Technology Ltd Transition duct cooling feed tubes

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE488448A (de) *
FR1052475A (fr) * 1952-03-15 1954-01-25 Snecma Chambres de combustion convenant en particulier aux turbines à gaz
FR2081220A1 (de) * 1970-03-19 1971-12-03 Hertel Heinrich
US5528903A (en) * 1992-03-20 1996-06-25 Schneider-Sanchez Ges.M.B.H. Small gas turbine
EP0743490A1 (de) * 1995-04-26 1996-11-20 SOCIETE NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION -Snecma Brennkammer mit einer Vielzahl von Filmkühlungsbohrungen die in verschiedene axiale und tangentiale Richtungen geneigt sind
US5727378A (en) * 1995-08-25 1998-03-17 Great Lakes Helicopters Inc. Gas turbine engine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013050105A1 (de) * 2011-10-06 2013-04-11 Lufthansa Technik Ag Brennkammer für eine gasturbine
EP3475614B1 (de) * 2016-06-22 2023-08-02 General Electric Company Brennkammerbaugruppe für einen turbinenmotor
FR3055950A1 (fr) * 2016-09-14 2018-03-16 Safran Helicopter Engines Chambre de combustion pour turbomachine comprenant des moyens pour ameliorer le refroidissement d'une paroi annulaire dans le sillage d'un obstacle
WO2018050999A1 (fr) * 2016-09-14 2018-03-22 Safran Helicopter Engines Chambre de combustion pour turbomachine comprenant des moyens pour améliorer le refroidissement d'une paroi annulaire dans le sillage d'un obstacle
FR3098569A1 (fr) * 2019-07-10 2021-01-15 Safran Aircraft Engines Paroi annulaire pour chambre de combustion de turbomachine comprenant des trous primaires, des trous de dilution et des orifices de refroidissement inclines

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CA2582634C (fr) 2015-12-01
FR2899315B1 (fr) 2012-09-28
RU2354889C2 (ru) 2009-05-10
JP2007271256A (ja) 2007-10-18
CA2582634A1 (fr) 2007-09-30
RU2007111388A (ru) 2008-10-10
EP1840466B1 (de) 2018-10-24
US20070227149A1 (en) 2007-10-04
CN101046299A (zh) 2007-10-03
FR2899315A1 (fr) 2007-10-05
US7891194B2 (en) 2011-02-22

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