EP2040001B1 - Chambre de combustion annulaire de moteur à turbine à gaz - Google Patents

Chambre de combustion annulaire de moteur à turbine à gaz Download PDF

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Publication number
EP2040001B1
EP2040001B1 EP08164751.3A EP08164751A EP2040001B1 EP 2040001 B1 EP2040001 B1 EP 2040001B1 EP 08164751 A EP08164751 A EP 08164751A EP 2040001 B1 EP2040001 B1 EP 2040001B1
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EP
European Patent Office
Prior art keywords
wall
chamber
combustion chamber
openings
combustion
Prior art date
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Application number
EP08164751.3A
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German (de)
English (en)
French (fr)
Other versions
EP2040001A3 (fr
EP2040001A2 (fr
Inventor
Didier Hippolyte Hernandez
Thomas Olivier Marie Noel
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
Safran Aircraft Engines SAS
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Publication date
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Publication of EP2040001A2 publication Critical patent/EP2040001A2/fr
Publication of EP2040001A3 publication Critical patent/EP2040001A3/fr
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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
    • F23R3/50—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
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00012—Details of sealing devices

Definitions

  • the present invention relates to the field of gas turbine engines, aims the annular combustion chambers of these engines and more particularly the combustion chamber bottoms.
  • Combustion chambers according to the relevant prior art are disclosed in the documents EP 1818615 A1 , and EP 1731839 .
  • a conventional annular combustion chamber is illustrated on the figure 1 . It is an axial half-section with respect to the axis of the engine of such a chamber the other half being deduced by symmetry with respect to this axis.
  • the combustion chamber 110 is housed in a diffusion chamber 130 which is an annular space defined between an outer casing 132 and an inner casing 134, in which compressed air is introduced from an upstream compressor not shown through An annular diffusion duct 136.
  • This conventional combustion chamber 110 has an outer wall 112 and an inner wall 114 which are coaxial and substantially conical to make the connection between the compressor duct and the turbine duct.
  • the outer 112 and inner 114 walls are interconnected upstream by a wall forming the chamber bottom 116.
  • the chamber bottom is an annular frustoconical piece which extends between two substantially transverse planes flaring from downstream to upstream.
  • the bottom chamber is connected to each of the two walls 112 and 114 by annular flanges 116 e and 116 i.
  • the chamber bottom is pierced with orifices 118 through which the injection systems 120 of fuel premixed with the combustion air pass. These orifices are angularly distributed around the motor axis. fireplaces are produced downstream of the injection systems.
  • the plane of the orifices is perpendicular to the axis of the combustion foci.
  • the axis combustion burners 200 are divergent, of angle ⁇ with respect to the axis of the motor.
  • thermal protection screens designated deflectors 122.
  • deflectors 122 are plates substantially refractory refractory material with an opening corresponding to that of the orifices of the injection systems.
  • the baffles are centered on the latter and fixed by brazing on the chamber bottom. They are cooled by cooling air jets entering the chamber through cooling bores 124 in the wall of the chamber bottom. These jets of air flowing from upstream to downstream are guided by chamber fairings 126, pass through the bottom chamber 116 and come to cool by impact the upstream face of the deflectors 122.
  • the invention therefore aims to allow the attachment of the deflectors on the wall of the chamber bottom despite the small space between two adjacent holes.
  • the invention relates to an annular combustion chamber of a gas turbine engine having an outer wall and an inner wall connected by a wall forming a chamber bottom, the walls delimiting combustion zones of axes inclined with respect to the axis. of the chamber, the chamber bottom wall, of frustoconical shape, being pierced with orifices for the fuel injection systems, the plane of the orifices being perpendicular to the axes of the combustion foci, thermal protection baffles centered on each orifices having a shoulder by which they bear against a flat surface portion along the periphery of the orifices.
  • the combustion chamber is characterized in that the chamber bottom wall is shaped in a succession of adjacent flat facets having a common edge, with a facet by injection system orifice, the shoulder of the deflectors bearing against the facet plane.
  • intersection of the planes of two adjacent facets forms a straight line passing through the axis of the combustion chamber.
  • the facets are then made by simply folding sheet.
  • This type of bottom wall construction advantageously applies when the minimum distance between two adjacent orifices is less than a value E which corresponds to the minimum sheet width in order to be able to produce flat surfaces with a transition zone according to FIG. prior art. Indeed, beyond this value, there are two solutions for producing the chamber bottom. The solution according to the prior art and the solution according to the invention. Below this value only the solution of the invention remains possible.
  • An evaluation of this value E is equal to the formula 9 * e + 2 * p + 5 in millimeters, in which "e” corresponds to the thickness of the sheet forming the bottom of the chamber and p the width of the shoulder or the bearing surface of the shoulder of the deflector.
  • the baffles comprise a flat surface portion lined with two radial sealing walls with the chamber bottom.
  • the invention also relates to a gas turbine engine comprising such a combustion chamber.
  • FIG. 2 a part of the chamber wall 116 seen from the side of the interior of the chamber without the annular walls is seen.
  • the two visible holes for the injection systems are circular and planar. They are bordered by a flat bearing surface 116a. These surfaces 116a form a flat support for the shoulders of the baffles, and are obtained by deformation by stamping the sheet forming the bottom chamber. Since the surface 116 is conical and has the same axis as the motor axis, the deformation is minimal along the generatrix G1 of the cone which passes through the diameter of the orifice and the deformation is maximum along the generatrix G2 which is tangent at the orifices, that is to say in the narrowest zone between two adjacent apertures.
  • the figure 3 shows, in section along the III - III direction, the shape of the wall in this zone.
  • the figure 4 shows the assembly of a deflector, in section along a generatrix G1.
  • This deflector 122 comprises a cylindrical flange 122a adapted to be housed in the opening of the chamber bottom.
  • the outer surface of this flange comprises a shoulder 122b which abuts on the bearing surface 116a.
  • a sleeve 123 holds the deflector against the bearing surface 116a. Everything is properly brazed.
  • the figure 5 shows the mounting of the deflector seen in the area of the figure 3 .
  • the shoulder 122b of the two deflectors 122 bears against the bearing surface 116a of the wall 116.
  • Walls 122c extending along the lateral edges and oriented radially with respect to the axis of the chamber, ensure sealing and prevent gases from the combustion chamber from circulating in the space between the bottom of the chamber and the baffle. These walls are perpendicular to the plane of the deflector
  • This zone is suitably cooled by unrepresented holes for the impact cooling air jets.
  • this minimum value below which the deformation of the sheet is mechanically no longer possible by means of industrial metal working, is substantially equal in millimeters to the value expressed by the following formula: 9 * e + 2 * p + 5 where "e” is the thickness of the sheet forming the bottom wall of the chamber and "p" the width of the shoulder 122b corresponding to the width that must be provided for the bearing surface 116a.
  • the figure 6 shows such a case of chamber bottom wall 116 'where the orifices are too close together for the sinking between the bearing surface 116'a is still possible.
  • the minimum value of the space separating two through-holes of the fuel injectors is 21.5 mm.
  • This wall geometry thus limits the possibilities of evolution of the chambers using more elaborate injection systems.
  • the annular chamber bottom wall 16 extends between two flanges, a radially inner flange 16i and a radially outer flange 16e through which the wall is fixed to the inner and outer walls of the annular combustion chamber, not shown because not concerned by the invention.
  • the wall comprises the orifices 16s for the injection systems.
  • the generally frustoconical wall consists of plane facets 16f surrounding each of the orifices 16s. These facets are thus delimited by four sides two sides in an arc 16f1 and 16f2.
  • the radially inner side 16f1 is bordered by the flange 16i for attachment to the inner wall of the combustion chamber.
  • the radially outer side 16f2 is bordered by the attachment flange 16e to the outer wall of the combustion chamber.
  • the other two sides 16f3 and 16f4 are rectilinear and are common to two adjacent facets. They are oriented in a radial direction passing through the axis of the engine. These sides are obtained by simply folding sheet.
  • the deflector 22 comprises a flat wall 22p which is positioned parallel to the flat facet of the chamber bottom.
  • a circular flange 22a borders the orifice corresponding to that of the chamber bottom.
  • This flange externally comprises a shoulder 22b which bears on the flat surface of the facet 16f.
  • Two side walls 22m seal between two adjacent baffles.
  • the deflector optionally has an excess thickness 22c.
  • this zone is shown in section on the chamber bottom between two adjacent orifices.
  • Two deflectors 22 are supported, by their shoulder 22b, on their respective facet 16f bordering the orifices of the injection systems.
  • the baffles are each held by a sheath, not shown here, slid around the circular flange on the other side with respect to the shoulder 22b and clasped together with the shoulder 22b the chamber bottom wall 16f.
  • the transition zones between flat surface portions and conical surface portions are dispensed with, and the number of fuel injectors can be increased. / or injection systems of larger diameter for better combustion.
  • the baffles being planar, the space between the bottom wall of the chamber and the baffles are flat, ensuring a flow of the cooling air homogeneous in this space.
  • the chamber is of divergent type, that is to say that the apex of the cone formed by the wall of the chamber bottom is downstream with respect to it and the axes of the combustion zones associated with the injectors deviate from the motor shaft downstream.
  • the invention also applies to a combustion chamber of convergent type, that is to say whose apex of the cone formed by the chamber bottom wall is located upstream with respect to itself and the axes of the Combustion points associated with the injectors are approaching the axis of the engine downstream.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP08164751.3A 2007-09-21 2008-09-19 Chambre de combustion annulaire de moteur à turbine à gaz Active EP2040001B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0706644A FR2921462B1 (fr) 2007-09-21 2007-09-21 Chambre de combustion annulaire de moteur a turbine a gaz

Publications (3)

Publication Number Publication Date
EP2040001A2 EP2040001A2 (fr) 2009-03-25
EP2040001A3 EP2040001A3 (fr) 2010-02-17
EP2040001B1 true EP2040001B1 (fr) 2018-04-18

Family

ID=39327017

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08164751.3A Active EP2040001B1 (fr) 2007-09-21 2008-09-19 Chambre de combustion annulaire de moteur à turbine à gaz

Country Status (5)

Country Link
US (1) US8156744B2 (ru)
EP (1) EP2040001B1 (ru)
CA (1) CA2639588C (ru)
FR (1) FR2921462B1 (ru)
RU (1) RU2485405C2 (ru)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH704185A1 (de) * 2010-12-06 2012-06-15 Alstom Technology Ltd Gasturbine sowie verfahren zum rekonditionieren einer solchen gasturbine.
FR2970666B1 (fr) * 2011-01-24 2013-01-18 Snecma Procede de perforation d'au moins une paroi d'une chambre de combustion
GB2491580A (en) * 2011-06-06 2012-12-12 Rolls Royce Plc A method of manufacturing a sheet metal annular combustion chamber
US10260748B2 (en) 2012-12-21 2019-04-16 United Technologies Corporation Gas turbine engine combustor with tailored temperature profile
US10816201B2 (en) 2013-09-13 2020-10-27 Raytheon Technologies Corporation Sealed combustor liner panel for a gas turbine engine
DE102015202570A1 (de) * 2015-02-12 2016-08-18 Rolls-Royce Deutschland Ltd & Co Kg Abdichtung eines Randspalts zwischen Effusionsschindeln einer Gasturbinenbrennkammer
US10816213B2 (en) 2018-03-01 2020-10-27 General Electric Company Combustor assembly with structural cowl and decoupled chamber

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US4222230A (en) * 1978-08-14 1980-09-16 General Electric Company Combustor dome assembly
US4843825A (en) * 1988-05-16 1989-07-04 United Technologies Corporation Combustor dome heat shield
FR2673454B1 (fr) * 1991-02-28 1995-01-13 Snecma Chambre de combustion comportant une paroi de fond comprenant une pluralite de troncs de cones partiels.
US5463864A (en) * 1993-12-27 1995-11-07 United Technologies Corporation Fuel nozzle guide for a gas turbine engine combustor
US5419115A (en) * 1994-04-29 1995-05-30 United Technologies Corporation Bulkhead and fuel nozzle guide assembly for an annular combustion chamber
US5974805A (en) * 1997-10-28 1999-11-02 Rolls-Royce Plc Heat shielding for a turbine combustor
US6164074A (en) * 1997-12-12 2000-12-26 United Technologies Corporation Combustor bulkhead with improved cooling and air recirculation zone
US6550251B1 (en) * 1997-12-18 2003-04-22 General Electric Company Venturiless swirl cup
US6212870B1 (en) * 1998-09-22 2001-04-10 General Electric Company Self fixturing combustor dome assembly
US6279323B1 (en) * 1999-11-01 2001-08-28 General Electric Company Low emissions combustor
RU2225575C2 (ru) * 2001-12-06 2004-03-10 Межрегиональная общественная организация "Поволжское отделение Российской инженерной академии" Устройство для подвода топлива в камеру сгорания
RU2223488C1 (ru) * 2002-10-25 2004-02-10 Красноярский государственный университет Индикаторный состав для определения меди (ii) в водных растворах
US7121095B2 (en) * 2003-08-11 2006-10-17 General Electric Company Combustor dome assembly of a gas turbine engine having improved deflector plates
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base
US7415826B2 (en) * 2005-07-25 2008-08-26 General Electric Company Free floating mixer assembly for combustor of a gas turbine engine
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2897922B1 (fr) * 2006-02-27 2008-10-10 Snecma Sa Agencement pour une chambre de combustion de turboreacteur
FR2903171B1 (fr) * 2006-06-29 2008-10-17 Snecma Sa Agencement a liaison par crabot pour chambre de combustion de turbomachine
FR2909748B1 (fr) * 2006-12-07 2009-07-10 Snecma Sa Fond de chambre, procede de realisation de celui-ci, chambre de combustion le comportant et turboreacteur en etant equipe
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.

Non-Patent Citations (1)

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Title
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Also Published As

Publication number Publication date
EP2040001A3 (fr) 2010-02-17
EP2040001A2 (fr) 2009-03-25
RU2008137660A (ru) 2010-03-27
CA2639588C (fr) 2016-03-29
FR2921462B1 (fr) 2012-08-24
US20090077976A1 (en) 2009-03-26
FR2921462A1 (fr) 2009-03-27
CA2639588A1 (fr) 2009-03-21
US8156744B2 (en) 2012-04-17
RU2485405C2 (ru) 2013-06-20

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