EP2040000A1 - Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef - Google Patents

Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef Download PDF

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Publication number
EP2040000A1
EP2040000A1 EP08164788A EP08164788A EP2040000A1 EP 2040000 A1 EP2040000 A1 EP 2040000A1 EP 08164788 A EP08164788 A EP 08164788A EP 08164788 A EP08164788 A EP 08164788A EP 2040000 A1 EP2040000 A1 EP 2040000A1
Authority
EP
European Patent Office
Prior art keywords
hole
injection
shape
injection systems
module according
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.)
Withdrawn
Application number
EP08164788A
Other languages
German (de)
English (en)
French (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
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
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP2040000A1 publication Critical patent/EP2040000A1/fr
Withdrawn legal-status Critical Current

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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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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

Definitions

  • the invention relates to the arrangement of injection systems in a combustion chamber bottom of an aircraft engine, such as a turbomachine or a turboprop.
  • the combustion chambers of the turbomachines comprise a bottom of combustion chamber at the periphery of which are mounted injection systems being regularly distributed.
  • the injection systems in each of which fuel injectors are mounted have the function of delivering a mixture of air and fuel which is ignited to provide the combustion gases.
  • the injection systems used deliver a quantity ranging from 10 to 25% of the air flowing through the combustion chamber.
  • the size of each injection system is reduced compared to that of the chamber.
  • the regular distribution of the injection systems at the periphery of the chamber bottom is provided in such a way that two adjacent injection systems are always separated from each other.
  • the differential expansions that occur during a combustion between the combustion chamber and its surrounding housing can be so high that it is necessary to provide a large operating clearance at the mounting link of each injector with its injection system, to compensate for said differential expansions.
  • the expected operating clearance may be of the order of 3 mm.
  • New generation injection systems introduce up to 70% of the air flowing through the combustion chamber.
  • the size of each multipoint injection system is larger than that of the current injection systems.
  • the multipoint fuel is delivered to the periphery of the multipoint injector. It is therefore necessary to have effective mixing of the multipoint fuel with the air injected by the injection system not to have the operating clearance of the injection system at its portion directly in contact with the injector. In other words, it is necessary to move the above-mentioned operating clearance at the level of the connection between the injection system and the bottom of the chamber.
  • the chamber bottom diameter is imposed and limited by design. So, in some case keeping all the other design parameters, it can lead to cases of geometric interference between consecutive attachment zones of injection systems.
  • an object of the invention is to propose a solution that makes it possible to have no geometric interference between consecutive attachment zones of new generation injection systems while maintaining the performance of the latter.
  • each protruding part of the peripheral injection systems at the hole and each protruding part of the peripheral fastening devices at the hole on the injection system side has a cylindrical external shape truncated by a flat part, so that the fastening devices and systems adjacent injectors are joined together with their flats parallel to each other.
  • each projecting part of the injection systems comprises an injection bowl flange truncated externally by a flat part.
  • each projecting part of the fixing devices comprises a ring and a sheath, each of cylindrical outer shape truncated by a flat and between which the truncated injection bowl flange is kept sliding.
  • tangential right tangent shape is meant here and in the context of the invention, a shape that has a cross section to the injection axis whose connection of the straight portions with a curve is tangent.
  • it may be two semicircles of the same diameter interconnected by two segments of straight lines parallel to the radial direction of the chamber bottom.
  • the known injection systems are slidably mounted in their fixing device to compensate for the relative radial displacements between chamber and combustion casing which are due to the differential expansion differences between these two parts during a combustion.
  • An operating clearance, the value of the displacements, is integrated in the sliding zone defined between the outside part of the injection system and the inside of the fixing device passing through the hole.
  • the chamber bottom holes, the parts of the injection systems and their associated fastening devices are always provided in cylindrical form. So, by construction, the operating clearance necessary to compensate radial displacements is the same in the tangential direction. The inventors have established that the operating clearance is not necessary in this tangential direction. According to the second embodiment of the invention, by assigning an oblong shape to straight tangents to the chamber bottom hole, to the fixing device and to the sliding zone of the injection system, the value of the operating clearance is recovered. tangential and thus gaining space for the injection systems.
  • the tangential operating clearance may be zero.
  • the part of the injection system such as a bowl, and that of fixing at the bottom hole of the chamber.
  • each fastening device may comprise a non-projecting part which extends at the periphery of the hole on the injection system side and of homothetic shape to that of the hole making it possible to maintain the mechanical system of the device. injection at the bottom of the chamber in the event of weld failure and / or brazing of the parts of the fastening device between them and / or at the bottom of the chamber.
  • the non-protruding part which makes it possible to ensure the mechanical support preferably comprises an elastically deformable ring arranged in contact with the hole and housed inside a groove in the sheath.
  • Each portion of the injection systems passing through the hole may include a cylindrical injection bowl portion.
  • the injection bowl may further comprise an oblong straight tangent outer flange homothetic to that of the inner part of the fasteners passing through the hole.
  • the invention finally relates to a turbomachine comprising a combustion module defined above.
  • FIG. 1 there is shown a peripheral zone of the chamber bottom 1 of a turbomachine as it currently exists.
  • two injection systems 2 are each attached to each other in a hole 10 in the chamber bottom 1.
  • the fixing is carried out by means of a fastening device 3 known per se, of which a part 30 of homothetic cylindrical shape of that hole 10 passes through the latter.
  • two adjacent injection systems 2 are spaced apart from each other by a distance e (distance measured from the outside of the projections 32 of fastening device 3) .
  • FIG 2 there is shown fictitiously a zone of the same turbomachine chamber 1 bottom according to the figure 1 but in which two new-generation injection systems, multipoint type 2, would be implanted if their fixing in the holes 10 was performed in a similar manner to the injection systems 2 according to the invention.
  • figure 1 there is shown fictitiously a zone of the same turbomachine chamber 1 bottom according to the figure 1 but in which two new-generation injection systems, multipoint type 2, would be implanted if their fixing in the holes 10 was performed in a similar manner to the injection systems 2 according to the invention. figure 1 .
  • analogous fixation is meant here an attachment of multipoint injection systems with conventional fasteners 3 having the same types of parts, arranged identically and a ratio of identical size with their associated injection system to obtain the same operating and fastening characteristics and, in particular, an identical operating clearance between the multipoint injection system and the conventional fastening device.
  • each injection system 2 comprises in the form of a single piece, an injection bowl 20.
  • This bowl 20 firstly comprises a diverging cone 200 internally to burst a jet, mixture of air and fuel from other elements of the injection system. It also comprises a flange 201 which extends at the end of the cone 200 downstream of the injection.
  • the one-piece bowl 20 includes also a flange 202 for holding the sliding bowl in the fixing device 3.
  • the bowl 20 finally comprises a holding portion 203 disposed substantially orthogonal to the flange 201 and the flange 202 and connecting the cone 200 to the flange.
  • the flange 201, the flange 202 and the holding portion 203 each have a cylindrical outer shape.
  • the inventors have thus come to the conclusion that the dimensions of the new-generation injection elements have to be reduced, by at least reducing the dimensions of the injection systems 2 and those of the associated fastening devices 3 which protrude from the side of the hole. upstream of the injection (that is to say the side of the chamber floor 10 which faces the reader on the figure 1 ).
  • each protruding part 202 of the peripheral injection systems at the hole and each projecting part 31, 32 of the circumferential fasteners at the hole of the injection systems 2a have an oblong shape with secant lines, the largest dimension from oblong to straight secants extending in the radial direction XX 'of the chamber bottom 1.
  • the injection bowl 20 of each injection system has a flange 202 of cylindrical shape externally truncated by a flat surface 2020 and secondly, the ring 31 and the sleeve 32 of the fastening devices 3 has a cylindrical external shape truncated by a flat portion 310, 320 and between which the truncated bowl flange 202 is maintained sliding.
  • the flats 2020, 310 and 320 are therefore nested one inside the other in the fixing position.
  • a first solution is to truncate the cylindrical shape for a part 31, 32 of the fasteners by a flat part 310, 320 and for part 20 of the injection system by a flat portion 2020 and sandwich the latter by the other two 310, 320.
  • the two outer flats 320 adjacent fixing devices ( figure 3 ) so that they are parallel to each other.
  • the minimum clearance E between two adjacent parallel flats 320 is at least 0.5 mm.
  • each portion 200 passing through injection bowls 2 and each part 30 of the fastening devices passing through the corresponding hole 10 has an outer shape respectively.
  • the radial operating clearance j r between the portion 203 of the injection bowl 20 and the portion 30 through the attachment device 3 surrounding it is equal to the tangential operating clearance j t between these parts 203, 30 ( Figures 3A and 3B ).
  • the deflectors 34 are not cylindrical and are truncated so as to cover the entire surface of the chamber bottom without interference between two adjacent deflectors.
  • a second complementary solution consists firstly in making each hole 10 with an oblong shape at right tangent with the largest dimension of the oblong section at right tangent extending in the radial direction XX 'of the chamber floor 1. It also consists in producing each part 200 of the injection bowl 20 and each part 30 fixing devices, passing through the corresponding hole 10 with an oblong straight tangent external shape respectively and an oblong straight tangent internal shape homothetic to the shape of the corresponding hole so that the radial operating clearance is greater than the tangential operating clearance.
  • each oblong shape with tangent straight lines consists of two half-circles of the same diameter connected to each other by two straight lines parallel to the radial direction XX 'of the chamber bottom 1.
  • a dog clutch abutment system is used to provide the FAIL SAFE function which makes it possible to ensure the mechanical maintenance of the injection system 2 at the bottom of chamber 1 in the event of weld failure and / or brazing of the parts 30, 32 of the fixing device 3 between them and / or at the bottom of the chamber 1.
  • a dog clutch system is not applicable because it applies only to cylindrical parts.
  • a mechanical holding part in the form of an elastically deformable rod 33 housed in the groove 321 of the sheath 32.
  • the part 30 of the fixing device which passes through the hole is a one-piece piece which extends on the side of the hole 10 furthest downstream of the injection.
  • This part therefore advantageously serves as a deflector 34 which protects the chamber bottom portion 1 around the injection systems 2.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
EP08164788A 2007-09-24 2008-09-22 Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef Withdrawn EP2040000A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0757791A FR2921464B1 (fr) 2007-09-24 2007-09-24 Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef

Publications (1)

Publication Number Publication Date
EP2040000A1 true EP2040000A1 (fr) 2009-03-25

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP08164788A Withdrawn EP2040000A1 (fr) 2007-09-24 2008-09-22 Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef

Country Status (6)

Country Link
US (1) US20090078797A1 (ru)
EP (1) EP2040000A1 (ru)
JP (1) JP2009074793A (ru)
CA (1) CA2639975A1 (ru)
FR (1) FR2921464B1 (ru)
RU (1) RU2481482C2 (ru)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3211312A1 (en) * 2016-02-25 2017-08-30 General Electric Company Combustor assembly

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2964725B1 (fr) 2010-09-14 2012-10-12 Snecma Carenage aerodynamique pour fond de chambre de combustion
FR3003632B1 (fr) 2013-03-19 2016-10-14 Snecma Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent
US11280492B2 (en) 2018-08-23 2022-03-22 General Electric Company Combustor assembly for a turbo machine
FR3084731B1 (fr) * 2019-02-19 2020-07-03 Safran Aircraft Engines Chambre de combustion pour une turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749388A (en) * 1953-08-06 1956-05-23 Lucas Industries Ltd Liquid fuel combustion chambers
EP0476927A2 (en) * 1990-09-17 1992-03-25 General Electric Company Fuel injector nozzle support
DE19948956A1 (de) * 1999-10-11 2001-04-12 Asea Brown Boveri Montagevorrichtung
US20060130483A1 (en) * 2004-12-17 2006-06-22 Howell Stephen J Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
EP1826492A1 (fr) * 2006-02-27 2007-08-29 Snecma Agencement pour une chambre de combustion de turboréacteur

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB579511A (en) * 1942-05-18 1946-08-07 Albert George Elliott Improvements in or relating to jet-propulsion apparatus for aircraft
US3589127A (en) * 1969-02-04 1971-06-29 Gen Electric Combustion apparatus
SU908140A1 (ru) * 1978-06-05 1983-12-15 Предприятие П/Я Г-4561 Камера сгорани газотурбинного двигател
US5274991A (en) * 1992-03-30 1994-01-04 General Electric Company Dry low NOx multi-nozzle combustion liner cap assembly
US6976363B2 (en) * 2003-08-11 2005-12-20 General Electric Company Combustor dome assembly of a gas turbine engine having a contoured swirler
US7310952B2 (en) * 2003-10-17 2007-12-25 General Electric Company Methods and apparatus for attaching swirlers to gas turbine engine combustors
US7673460B2 (en) * 2005-06-07 2010-03-09 Snecma System of attaching an injection system to a turbojet combustion chamber base

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB749388A (en) * 1953-08-06 1956-05-23 Lucas Industries Ltd Liquid fuel combustion chambers
EP0476927A2 (en) * 1990-09-17 1992-03-25 General Electric Company Fuel injector nozzle support
DE19948956A1 (de) * 1999-10-11 2001-04-12 Asea Brown Boveri Montagevorrichtung
US20060130483A1 (en) * 2004-12-17 2006-06-22 Howell Stephen J Gas turbine engine carburetor with flat retainer connecting primary and secondary swirlers
EP1826492A1 (fr) * 2006-02-27 2007-08-29 Snecma Agencement pour une chambre de combustion de turboréacteur

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3211312A1 (en) * 2016-02-25 2017-08-30 General Electric Company Combustor assembly
US10473332B2 (en) 2016-02-25 2019-11-12 General Electric Company Combustor assembly

Also Published As

Publication number Publication date
FR2921464B1 (fr) 2014-03-28
CA2639975A1 (fr) 2009-03-24
JP2009074793A (ja) 2009-04-09
US20090078797A1 (en) 2009-03-26
RU2481482C2 (ru) 2013-05-10
RU2008138065A (ru) 2010-03-27
FR2921464A1 (fr) 2009-03-27

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