EP2856036B1 - Virole de chambre de combustion de turbomachine - Google Patents

Virole de chambre de combustion de turbomachine Download PDF

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Publication number
EP2856036B1
EP2856036B1 EP13728462.6A EP13728462A EP2856036B1 EP 2856036 B1 EP2856036 B1 EP 2856036B1 EP 13728462 A EP13728462 A EP 13728462A EP 2856036 B1 EP2856036 B1 EP 2856036B1
Authority
EP
European Patent Office
Prior art keywords
shell ring
holes
inserts
dilution
shell
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.)
Active
Application number
EP13728462.6A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2856036A2 (fr
Inventor
Denis Jean Maurice Sandelis
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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Application filed by Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Publication of EP2856036A2 publication Critical patent/EP2856036A2/fr
Application granted granted Critical
Publication of EP2856036B1 publication Critical patent/EP2856036B1/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
    • F23R3/02—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
    • 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
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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
    • F23R2900/03044—Impingement cooled combustion chamber walls or subassemblies
    • 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

Definitions

  • the present invention relates to a turbomachine combustion chamber shell.
  • the ferrule in question here delimits a flame tube where the combustion takes place, and which is therefore subjected to a significant heating on its inner face, while its outer face is traversed by a flow of fresh gas, originating from the compressors of the turbomachine and which mixes with the combustion gases downstream of the shell before passing into the turbines.
  • Such a ferrule is traversed by several kinds of drilling, including relatively large diameter dilution holes intended to let part of the external flow into the flame tube to improve the composition of the combustion mixture, and holes finer ventilation, more numerous and distributed over most of the surface of the ferrule, to also allow an air inlet of the external flow, but whose effect is to protect the ferrule from heating, by forming a grazing flow downstream on the inner face of the shell and therefore a boundary layer cooler than the combustion gases.
  • This boundary layer is reformed badly immediately downstream of the large diameter holes, which break the grazing flow, and that the corresponding parts of the ferrule, subjected almost entirely to heating, are subject to deformations and stresses resulting from dilations. differentials, which can give rise to creeks.
  • the document FR 2 892 180 A1 which relates to a combustion chamber shell comprising primary bores, dilution bores, ventilation bores, and where the lack of ventilation downstream of the large bores is remedied by a fourth category of bores regularly located on the circumferences.
  • the ferrule passing immediately downstream of the large holes; as well as the document FR 2 404 110 A1 , which describes a ferrule composed of two separate layers and joined at the same time by ribs.
  • the dilution bores can be provided with a cylindrical ring which passes through them and comprises an upper rim. The ring makes it possible to obtain favorable characteristics of the ventilation flow; the upper rim is therefore hollowed out, or completely interrupted; but this document does not suggest interrupting ventilation holes under the wafer to create a room where the air breath stays for a moment.
  • a turbomachine combustion chamber shell comprising dilution bores and ventilation bores surrounding the dilution holes and finer and more numerous than them, characterized in that it comprises platelets extending over and around the dilution bores on an outer face of the ferrule, the ferrule is devoid of ventilation holes at portions above the platelets, the plates each comprising a flange for attachment to the ferrule and an orifice extending over one of the respective dilution bores, and the wafers are pierced by bores directed towards said portions of the ferrule.
  • the essential effect obtained is that the pressure that prevails around the ferrule causes air to penetrate through the holes of the wafer, in jets that strike the outer face of the ferrule and produce at this point the desired cooling, with a greater intensity than ventilation holes arranged through the shell, that the air passes very quickly. Instead, the air sucked under the wafer flows over the outer face of the ferrule after reaching it, moving towards the dilution piercing, and this flow time causes greater heat removal. .
  • the rather low speed with which it is then animated can allow it to take up quite easily a tangent direction downstream, which will help to restore the boundary layer on the inner face of ferrule and will further improve ventilation.
  • the platelets may be parallel to or inclined to the shell in an axial direction of the shell.
  • the piercings of the platelets are advantageously perpendicular to the ferrule, but they can also be placed obliquely; all these arrangements are to be decided in each design.
  • the wafers it is advantageous for the wafers to extend more in the downstream direction of the shell than in other directions from the centers of the dilution bores, since the portions of the ferrule which are subjected to intense heating are precisely downstream of the ferrule. these holes.
  • the platelets may, however, undergo shrinkage in this downstream direction of the ferrule, since the boundary layer is reconstituted in the same form, bypassing the dilution bores.
  • the plates each comprise an inner rim surrounding the respective orifice and extending towards the respective dilution passage, which allows to channel both the air sucked directly by the dilution holes passing. through the orifice of the wafer, and the air sucked by the holes of the wafer and blowing on the shell, which then passes around this inner edge.
  • Another aspect of the invention is a turbomachine combustion chamber comprising such a ferrule.
  • a turbomachine combustion chamber where the invention may be present is schematically represented in FIG. Figure 1 . It will be recalled that these combustion chambers are annular around an axis of the turbomachine, so that the figure 1 is only half a cut along the axis.
  • a fairing 1 comprises an outer shell 2, an inner shell 3, both generally conical and concentric with each other, and an annular chamber bottom 4 joining the ferrules 2 and 3.
  • the internal volume of the combustion chamber, forming a tube with flame 16 is delimited by the ferrules 2 and 3 and the chamber bottom 4 and opens on the opposite side to the chamber bottom 4 by an opening 5.
  • the combustion chamber is surrounded by an outer casing 6 and an inner casing 7 which delimit a flow vein 10 that the fairing 1 separates in two outer vein portions 8 and 9 which circumvent and run along the fairing 1.
  • the air flow stream 10 comes from a nozzle 11 located opposite an opening 12 formed between rear fairings 13 and 14 of the ferrules 2 and 3 (in this description, "back” and “front” are considered with reference to the direction of the airflow).
  • Fuel injectors 15 extend through the outer casing 6, the opening 12 and the chamber bottom 4 into the flame tube 16. Candles 17 also pass through the outer casing 6 at the front of the fuel injectors 15 and also through the outer shell 1 to flush in the flame tube 16. The largest part of the air flow thus borrows the veins 8 and 9, even if a portion penetrates under the shrouds 13 and 14 by the opening 12.
  • the ferrules 2 and 3 are traversed by numerous holes, including ventilation holes 38 thin and numerous and diluting holes 39 of larger diameter, less numerous and distributed over a circle or a small number of circles.
  • ventilation holes 38 thin and numerous and diluting holes 39 of larger diameter, less numerous and distributed over a circle or a small number of circles.
  • the common effect of these holes is to let air from the veins 8 and 9 into the flame tube 16 at lower pressure for various purposes.
  • the invention can be implemented on one or the other of the ferrules 2 and 3.
  • Platelets 40 are disposed on the outer face of ferrule 2 or 3 and around dilution holes 39. They each comprise a main portion 41 extending above ferrule 2 or 3, an outer flange 42 surrounding the portion main 41 and attached to the ferrule 2 or 3, an orifice 43 extending in front of the respective dilution bore 39 but smaller radius, an inner rim 44 surrounding the orifice 43 and extending into most of the the depth of the dilution bore 39, and the holes 45 passing through the main portion 41 and opening in front of a portion facing the ferrule 2 or 3, which is devoid of the ventilation holes 38 there.
  • the plate 40 thus delimits a chamber 49 almost closed in front of the ferrule 2 or 3 of the respective dilution bore 39.
  • the wafer 40 is generally triangular in shape, extending further in the downstream direction of the flow while becoming narrower and narrower, so as to correspond as much as possible to the zone of ferrule 2 or 3 where the cracks can appear.
  • the dilution piercing 39 is provided with fixing sectors 46 projecting towards the center of said bore, which come to touch and grip the inner rim 44.
  • This inner rim 44 and the attachment sectors 46 delimit airflow sectors having through the holes 45 of the plates 40, including here two lateral sectors 47 symmetrical with respect to an axial direction of the shell 2 or 3 and a downstream sector 48.
  • the centers O1 and O2 of the inner flange 44 and drilling 39 are axially offset, so that the sectors 47 or 48 have an irregular shape and the downstream sector 48 is wider, which promotes the flow of the chamber 49 by the downstream sector 48 and the reconstruction of a ventilation limit layer downstream of dilution drilling 39.
  • the specific flow provided by the wafer 40 is as follows. Air from the flow of the vein 8 or 9 under excess pressure is blown into the chamber 49 through the holes of the plates 45 and refreshes the ferrule 2 or 3 around the respective dilution bore 39, and in particular the downstream portion. of it, by its outer face. This air then flows into the flame tube 16 through the flow sectors 47 and 48 and in particular through the latter. Upon entering the flame tube 16, its flow can quickly become axial downstream of the combustion chamber and reconstitute a boundary layer in the aforementioned zone of the shell 2 or 3 downstream of the dilution bore 38 and further contributes to protect her.
  • the main portions 41 of the plates 40 may or may not be parallel to the portion facing the shell 2 or 3, and the holes 45 perpendicular or otherwise to this portion.
  • the main portions 41 may in particular be inclined in the axial direction of the shell 2 or 3, according to the contour 41 ', to better intercept the flow air by creating a larger obstacle.

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)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
EP13728462.6A 2012-05-25 2013-05-23 Virole de chambre de combustion de turbomachine Active EP2856036B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1254847A FR2991028B1 (fr) 2012-05-25 2012-05-25 Virole de chambre de combustion de turbomachine
PCT/FR2013/051117 WO2013175126A2 (fr) 2012-05-25 2013-05-23 Virole de chambre de combustion de turbomachine

Publications (2)

Publication Number Publication Date
EP2856036A2 EP2856036A2 (fr) 2015-04-08
EP2856036B1 true EP2856036B1 (fr) 2018-09-12

Family

ID=46754628

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13728462.6A Active EP2856036B1 (fr) 2012-05-25 2013-05-23 Virole de chambre de combustion de turbomachine

Country Status (9)

Country Link
US (1) US9377200B2 (ru)
EP (1) EP2856036B1 (ru)
CN (1) CN104520647B (ru)
BR (1) BR112014027018B1 (ru)
CA (1) CA2871923C (ru)
FR (1) FR2991028B1 (ru)
IN (1) IN2014DN08528A (ru)
RU (1) RU2626876C2 (ru)
WO (1) WO2013175126A2 (ru)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102012022259A1 (de) * 2012-11-13 2014-05-28 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerschindel einer Gasturbine sowie Verfahren zu deren Herstellung
WO2015100346A1 (en) 2013-12-23 2015-07-02 United Technologies Corporation Multi-streamed dilution hole configuration for a gas turbine engine
EP3018417B8 (en) * 2014-11-04 2021-03-31 Raytheon Technologies Corporation Low lump mass combustor wall with quench aperture(s)
US10386072B2 (en) * 2015-09-02 2019-08-20 Pratt & Whitney Canada Corp. Internally cooled dilution hole bosses for gas turbine engine combustors
US20180283689A1 (en) * 2017-04-03 2018-10-04 General Electric Company Film starters in combustors of gas turbine engines
US11187412B2 (en) 2018-08-22 2021-11-30 General Electric Company Flow control wall assembly for heat engine

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1052475A (fr) * 1952-03-15 1954-01-25 Snecma Chambres de combustion convenant en particulier aux turbines à gaz
GB777782A (en) 1955-06-24 1957-06-26 Ici Ltd Purification of terephthalic acid
US4132066A (en) 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
US4875339A (en) * 1987-11-27 1989-10-24 General Electric Company Combustion chamber liner insert
US4887432A (en) * 1988-10-07 1989-12-19 Westinghouse Electric Corp. Gas turbine combustion chamber with air scoops
FR2855249B1 (fr) * 2003-05-20 2005-07-08 Snecma Moteurs Chambre de combustion ayant une liaison souple entre un fond de chambre et une paroi de chambre
RU2260748C2 (ru) * 2003-12-02 2005-09-20 Открытое акционерное общество "Авиадвигатель" Камера сгорания газотурбинного двигателя
FR2881813B1 (fr) * 2005-02-09 2011-04-08 Snecma Moteurs Carenage de chambre de combustion de turbomachine
FR2892180B1 (fr) * 2005-10-18 2008-02-01 Snecma Sa Amelioration des perfomances d'une chambre de combustion par multiperforation des parois
FR2899315B1 (fr) 2006-03-30 2012-09-28 Snecma Configuration d'ouvertures de dilution dans une paroi de chambre de combustion de turbomachine
US8171634B2 (en) * 2007-07-09 2012-05-08 Pratt & Whitney Canada Corp. Method of producing effusion holes
US8789372B2 (en) * 2009-07-08 2014-07-29 General Electric Company Injector with integrated resonator

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

Also Published As

Publication number Publication date
US9377200B2 (en) 2016-06-28
US20150059344A1 (en) 2015-03-05
RU2014152849A (ru) 2016-07-20
CN104520647A (zh) 2015-04-15
CN104520647B (zh) 2016-02-24
EP2856036A2 (fr) 2015-04-08
WO2013175126A2 (fr) 2013-11-28
FR2991028A1 (fr) 2013-11-29
IN2014DN08528A (ru) 2015-05-15
WO2013175126A3 (fr) 2014-04-24
BR112014027018B1 (pt) 2021-05-25
FR2991028B1 (fr) 2014-07-04
RU2626876C2 (ru) 2017-08-02
CA2871923C (fr) 2020-02-11
BR112014027018A2 (pt) 2017-06-27
CA2871923A1 (fr) 2013-11-28

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