EP0461026A1 - Brennstoffeinspritzvorrichtung mit Vorverdampfer - Google Patents

Brennstoffeinspritzvorrichtung mit Vorverdampfer Download PDF

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Publication number
EP0461026A1
EP0461026A1 EP91401458A EP91401458A EP0461026A1 EP 0461026 A1 EP0461026 A1 EP 0461026A1 EP 91401458 A EP91401458 A EP 91401458A EP 91401458 A EP91401458 A EP 91401458A EP 0461026 A1 EP0461026 A1 EP 0461026A1
Authority
EP
European Patent Office
Prior art keywords
bowl
wall
chamber
combustion chamber
vaporization
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
EP91401458A
Other languages
English (en)
French (fr)
Other versions
EP0461026B1 (de
Inventor
Alexandre Forestier
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
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA, SNECMA SAS filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP0461026A1 publication Critical patent/EP0461026A1/de
Application granted granted Critical
Publication of EP0461026B1 publication Critical patent/EP0461026B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/21—Finger-ring forming or sizing

Definitions

  • the present invention relates to the mounting of combustion chambers of turbomachines.
  • turbomachinery in particular aviation turbojets, are equipped with annular combustion chambers and comprise, arranged between the fuel injectors and the combustion chamber proper, fuel pre-vaporization bowls.
  • pre-vaporization bowls are mounted mobile in their housing, this to take account of the significant relative movements which occur in operation between injectors and chambers.
  • the bowls must therefore be mounted floating radially with respect to the chamber and axially with respect to the injectors.
  • turbojet engines are designed in a modular way and the assembly sequence of the combustion chambers is carried out by assembling the chamber equipped with its spraying bowls, inside the chamber casing, itself equipped of its injectors. This assembly is carried out with the engine in a horizontal position.
  • the radial mobility of the bowls relative to the chamber means that they take by gravity, a low position eccentric by several millimeters relative to their theoretical axis.
  • the present invention aims to avoid this type of risk during assembly while retaining the bowls the possibility of sliding radially in their housing and absorbing in operation the relative movements between chamber and injectors.
  • the invention therefore relates to a fuel injection assembly inside a turbomachine combustion chamber, mounted on the wall delimiting said chamber and comprising a spray bowl mounted floating relative to the wall of the combustion chamber, parallel to a determined direction.
  • a part of a structure integral with the pre-vaporization bowl and a part integral with the wall of the combustion chamber are aligned substantially parallel to said determined direction, and are capable of being arranged at a variable distance l 'from one another, however, that at least one magnet is fixed on one of said parts and is able to cooperate with the other part to fix it or, on the contrary, detach from it, in the first case, now in position the pre-vaporization bowl relative to the combustion chamber, and, in the second case, leaving said pre-vaporization bowl free to float relative to said part of the wall of the combustion chamber.
  • FIG. 1 represents an annular combustion chamber, the inner 1 and outer 2 walls of which appear.
  • a circular opening 4 On the dome 3 of the chamber bottom is pierced a circular opening 4 inside which is fixed a circular support flange 5 comprising a cylindrical downstream part 5a, welded externally inside the opening 4, and a cylindrical upstream part 5b inside which a stop ring 6 is mounted, the two cylindrical parts 5a and 5b of different diameters being connected by a central central part 5c.
  • the pre-vaporization bowl 7 has an internal ferrule 7a and an external ferrule 7b, separated upstream by fins 8 forming a swirl swirl for the pre-vaporization air.
  • the two ferrules 7a and 7b form a frustoconical passage 7c downstream of which the ferrule 7b flares in frustoconical veil 7d forming the bowl proper.
  • a cylindrical outer wall 7e is welded to the downstream edge of this veil 7d.
  • a mounting ring 9 On the outer edge of the 7th wall is welded a mounting ring 9 whose cross section is square.
  • the ferrule therefore comprises a cylindrical part 9a and a flat part 9b.
  • a tongue 9c extends radially on the outer edge of the flat part 9b of the mounting ring 9.
  • the tongue passes through a notch 5d of the cylindrical part 5b of the support flange so that the bowl can slide radially along the axis XX ′ of the support flange, said axis being coincident with the diameter of the chamber which carries the center 0 of the bowl.
  • the stop ring 6 is then welded inside the support flange 5 so that the only clearance left at the ferrule 9 and therefore to the bowl 7 is a radial clearance.
  • Such a combustion chamber comprising pre-spraying bowls regularly distributed over its circumference has the support flanges of its bowls oriented so that their tongues 9c as well as the direction of action of the force exerted by the elastic means are radial.
  • the injector 11 is mounted without radial play, but floating axially inside the internal ferrule 7a of the bowl 7.
  • a permanent magnet 15 is fixed, on the underside of said intersection of the cylindrical part 5b.
  • This magnet is placed above a magnetizable patch 12, itself fixed on the upper face of the upper intersection of the cylindrical outer wall 7e of the pre-vaporization bowl with the diameter XX ′.
  • the fixings of the permanent magnet 15 and of the magnetizable patch 12 are produced by welding 13 on the respective parts.
  • the magnetizable patch 12 and the permanent magnet 15 are arranged opposite one another, either at close mutual distance (FIGS. 1 and 2), or magnetically bonded to each other (FIGS. 3 and 4) .
  • the material of the magnetizable patch is "Z12C13" (AFNOR standard).
  • the pre-vaporization bowl 7 is suspended from the permanent magnet 15 in the configuration of FIGS. 3 and 4, which avoids the direct support of the pre-vaporization bowl by the nose 14 of the injector 11, and protects said constraint injector corresponding.
  • the nose 14 of the injector 11 then has the possibility of moving freely relative to the pre-spray bowl 17 in the direction of the axis 16.
  • the permanent magnet 15 will remain ready to receive the magnetizable patch 12 and thus relieve the nose 14 of the injector again from the weight of the pre-vaporization bowl.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Spray-Type Burners (AREA)
EP91401458A 1990-06-05 1991-06-05 Brennstoffeinspritzvorrichtung mit Vorverdampfer Expired - Lifetime EP0461026B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9006947A FR2662784B1 (fr) 1990-06-05 1990-06-05 Ensemble d'injection pour turbomachine, comprenant un bol de prevaporisation.
FR9006947 1990-06-05

Publications (2)

Publication Number Publication Date
EP0461026A1 true EP0461026A1 (de) 1991-12-11
EP0461026B1 EP0461026B1 (de) 1993-07-28

Family

ID=9397268

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91401458A Expired - Lifetime EP0461026B1 (de) 1990-06-05 1991-06-05 Brennstoffeinspritzvorrichtung mit Vorverdampfer

Country Status (5)

Country Link
US (1) US5172545A (de)
EP (1) EP0461026B1 (de)
JP (1) JP2578533B2 (de)
DE (1) DE69100199T2 (de)
FR (1) FR2662784B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2956724A1 (fr) * 2010-02-23 2011-08-26 Snecma Systeme d'injection de carburant pour une chambre de combustion de turbomachine
CN103047682A (zh) * 2012-12-27 2013-04-17 中国燃气涡轮研究院 一种带预膜式喷嘴的部分预混预蒸发燃烧室

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5577379A (en) * 1994-12-15 1996-11-26 United Technologies Corporation Fuel nozzle guide retainer assembly
US5961316A (en) * 1995-10-25 1999-10-05 Weil-Mclain Oil burner
US6912782B2 (en) 2003-04-09 2005-07-05 Honeywell International Inc. Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine
US7007480B2 (en) * 2003-04-09 2006-03-07 Honeywell International, Inc. Multi-axial pivoting combustor liner in gas turbine engine
US7690207B2 (en) * 2004-08-24 2010-04-06 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
US7134286B2 (en) * 2004-08-24 2006-11-14 Pratt & Whitney Canada Corp. Gas turbine floating collar arrangement
FR2885201B1 (fr) * 2005-04-28 2010-09-17 Snecma Moteurs Chambre de combustion aisement demontable a performance aerodynamique amelioree
FR2893390B1 (fr) * 2005-11-15 2011-04-01 Snecma Fond de chambre de combustion avec ventilation
US7926280B2 (en) * 2007-05-16 2011-04-19 Pratt & Whitney Canada Corp. Interface between a combustor and fuel nozzle
US9291139B2 (en) 2008-08-27 2016-03-22 Woodward, Inc. Dual action fuel injection nozzle
US20100186414A1 (en) * 2008-12-15 2010-07-29 Sonic Blue Aerospace, Inc. Magnetic ion plasma annular injection combustor
DE102011014972A1 (de) * 2011-03-24 2012-09-27 Rolls-Royce Deutschland Ltd & Co Kg Brennkammerkopf mit Halterungen für Dichtungen an Brennern in Gasturbinen
FR3026827B1 (fr) * 2014-10-01 2019-06-07 Safran Aircraft Engines Chambre de combustion de turbomachine
GB2543803B (en) * 2015-10-29 2019-10-30 Rolls Royce Plc A combustion chamber assembly
US20170227224A1 (en) * 2016-02-09 2017-08-10 Solar Turbines Incorporated Fuel injector for combustion engine system, and engine operating method

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
GB2073398A (en) * 1980-04-02 1981-10-14 United Technologies Corp Fuel nozzle guide and seal for a gas turbine engine
EP0214393A1 (de) * 1985-08-31 1987-03-18 BBC Brown Boveri AG Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2639095B1 (fr) * 1988-11-17 1990-12-21 Snecma Chambre de combustion de turbomachine a bols de prevaporisation montes flottants

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3273343A (en) * 1965-03-08 1966-09-20 Dickens Inc Combustion chamber construction in gas turbine power plant
GB2073398A (en) * 1980-04-02 1981-10-14 United Technologies Corp Fuel nozzle guide and seal for a gas turbine engine
EP0214393A1 (de) * 1985-08-31 1987-03-18 BBC Brown Boveri AG Einrichtung zur Dämpfung von Schaufelschwingungen bei Turbomaschinen

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2956724A1 (fr) * 2010-02-23 2011-08-26 Snecma Systeme d'injection de carburant pour une chambre de combustion de turbomachine
US8453459B2 (en) 2010-02-23 2013-06-04 Snecma Fuel injection system for a combustion chamber of a turbomachine
CN103047682A (zh) * 2012-12-27 2013-04-17 中国燃气涡轮研究院 一种带预膜式喷嘴的部分预混预蒸发燃烧室

Also Published As

Publication number Publication date
DE69100199T2 (de) 1993-12-09
JP2578533B2 (ja) 1997-02-05
FR2662784A1 (fr) 1991-12-06
FR2662784B1 (fr) 1992-08-14
JPH04227412A (ja) 1992-08-17
US5172545A (en) 1992-12-22
EP0461026B1 (de) 1993-07-28
DE69100199D1 (de) 1993-09-02

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