EP0455559A1 - Verbrennungsluftzufuhreinrichtung für Gasturbine - Google Patents

Verbrennungsluftzufuhreinrichtung für Gasturbine Download PDF

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Publication number
EP0455559A1
EP0455559A1 EP91401167A EP91401167A EP0455559A1 EP 0455559 A1 EP0455559 A1 EP 0455559A1 EP 91401167 A EP91401167 A EP 91401167A EP 91401167 A EP91401167 A EP 91401167A EP 0455559 A1 EP0455559 A1 EP 0455559A1
Authority
EP
European Patent Office
Prior art keywords
pivoting
diaphragms
adjusting
piston
combustion chamber
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
EP91401167A
Other languages
English (en)
French (fr)
Other versions
EP0455559B1 (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 EP0455559A1 publication Critical patent/EP0455559A1/de
Application granted granted Critical
Publication of EP0455559B1 publication Critical patent/EP0455559B1/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/26—Controlling the air flow
    • 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
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2250/00—Geometry
    • F05B2250/40—Movement of component
    • F05B2250/41—Movement of component with one degree of freedom
    • F05B2250/411—Movement of component with one degree of freedom in rotation

Definitions

  • Known gas turbines are provided with oxidant supply devices whose flow rate is adjustable by means of pivoting diaphragms.
  • FR-A-2 572 463 describes and represents such diaphragms.
  • the present invention relates to a device for supplying oxidant, such as air, to a combustion chamber of a gas turbine, comprising in particular a plurality of diaphragms for adjusting the quantity of oxidant admitted into the combustion chamber, each diaphragm comprising a crown, which is pivotally mounted relative to the casing of the gas turbine, the pivoting of which constitutes the means of adjusting the cross-section for the passage of the oxidant into the combustion chamber, and which is coupled to a device for controlling its pivoting.
  • oxidant such as air
  • the subject of the invention is the adoption of the provisions according to which at least certain diaphragms are grouped into two adjacent diaphragms, the two crowns of the diaphragms of a group of two diaphragms each include, a member for adjusting the pivoting of said crown; and, finally, the members for adjusting the pivoting of the two rings of the two said diaphragms are coupled to a single control member belonging to said device for controlling the pivoting.
  • the main advantage of a feeding device according to the invention lies in its simplicity and compactness, and consequently in the saving in weight and cost price achieved.
  • the gas turbine the combustion chamber of which is represented, in cross section, by a circular ring 1, is provided with oxidizer supply devices 2, here in even number (16 devices), grouped in pairs.
  • Each device 2 for supplying oxidant in air in the embodiment shown, comprises a fixed cylindrical ring 3, provided with inlet passages 4 for the oxidant inside the combustion chamber 5, and a ring 6, which is pivotally mounted around the axis 7 of the fixed crown 3 which surrounds said fixed crown 3 and which is provided with passages 8 capable of being arranged opposite the intake passages 4 of the fixed crown and thus allowing admission of the oxidant in the combustion chamber 5 or, on the contrary, as a function of the relative position of the crowns 3 and 6, to no longer be disposed opposite said intake passages 4, and then to remove, or reduce, the combustion of the oxidant in the combustion chamber.
  • the assembly of a fixed crown 3 and the associated pivoting crown 6 is often also called a "diaphragm".
  • the illustrated embodiment is only for example.
  • Each pivoting ring 6 is provided with an arm 9, which constitutes a member for adjusting its pivoting and which is provided with an oblong slot 10.
  • a first piston rod 11, integral with a piston 12, is associated with the two arm 9 of each group of two oxidant supply devices 2, by means of a shaft 13 introduced concomitantly into the openings 10 of the two said arms 9 and into a bore 14, which is provided with the free end of the first rod piston 11.
  • the two spokes passing through the pivot axis 7 and through the axis of the shaft 13 of a group of two oxidizer supply devices 2 form an angle 2A between them, and each form, with the axis 15 of the first piston rod 11, an angle A, so that said axis 15 of this first piston rod 11 constitutes the bisector of the angle of said two radii.
  • Each piston 12 is slidably mounted in a cylinder 16, in a direction substantially radial with respect to the wall 1 of the combustion chamber and parallel to the axis 15 of the first piston rod 11, the latter passing through without sealing, with a slight clearance J, the wall 1 and the cylinder 16 being moreover fixed to the wall 1 by screws 17.
  • a deformable bellows 18 is contained in the chamber 19 delimited inside the cylinder 16, surrounds the first piston rod 11 and, secured with tightness to the piston 12 and to the bottom 20 of the cylinder which is fixed to the wall 1, itself delimits, inside the cylinder 16, a working chamber 21, which is in permanent communication, by the 'through play J, with combustion chamber 5.
  • This cam 25 is integral with a support 29 which is pivotally mounted relative to the cylinder 16 about an axis 26 parallel to the common axis 15 of the two piston rods 11 and 22, by means of a bearing pivot 27 fixed to the body of the cylinder 16 by a screw 28.
  • a pinion 30 is also integral with the support 29 of the cam and cooperates with a screw end 31.
  • the assembly of the jack constituted by the cylinder 16 and the piston, the two piston rods 11 and 22, the cam 25, its support 29, and the pinions 30 and worm 31, constitutes the control device 32 pivoting of the two pivoting rings 6 of a group of two oxidizing feed devices 2.
  • the worms 31 of the various control devices 32 are also connected to each other by flexible connections 33, as well as to a single drive device 34, comprising a motor for driving one in rotation, and consequently of each of the endless screws 31.
  • the embodiment which has just been described is compact since a single control device 32 controls the pivoting of the two pivoting rings 6 of two oxidizer or diaphragm supply devices 2.
  • a single drive device 34 allows the adjustment of the positions of all the cams 25. This compact embodiment is therefore also light and at a relatively moderate cost price. It will have been noted that the pressurized gas contained in the enclosure of the combustion chamber casing reaches the working chamber 21 of each cylinder via the clearance J and places the end 22A of each second rod in abutment. piston 22 on the face 24 of the cam 25, thus having an antagonistic effect to that of said cam.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Mechanically-Actuated Valves (AREA)
EP91401167A 1990-05-03 1991-05-03 Verbrennungsluftzufuhreinrichtung für Gasturbine Expired - Lifetime EP0455559B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9005556 1990-05-03
FR909005556A FR2661714B1 (fr) 1990-05-03 1990-05-03 Dispositif d'alimentation en comburant d'une turbine a gaz.

Publications (2)

Publication Number Publication Date
EP0455559A1 true EP0455559A1 (de) 1991-11-06
EP0455559B1 EP0455559B1 (de) 1993-12-08

Family

ID=9396273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP91401167A Expired - Lifetime EP0455559B1 (de) 1990-05-03 1991-05-03 Verbrennungsluftzufuhreinrichtung für Gasturbine

Country Status (4)

Country Link
US (1) US5159807A (de)
EP (1) EP0455559B1 (de)
DE (1) DE69100735T2 (de)
FR (1) FR2661714B1 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0514260A1 (de) * 1991-05-16 1992-11-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Luftzufuhrregeleinrichtung für eine Gasturbine
FR2939171A1 (fr) * 2008-11-28 2010-06-04 Snecma Turbomachine a systemes d'injection de carburant distincts, utilisant des joints d'etancheite identiques.

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4220060C2 (de) * 1992-06-19 1996-10-17 Mtu Muenchen Gmbh Einrichtung zur Betätigung einer den Durchsatz von Verbrennungsluft steuernden Dralleinrichtung eines Brenners für Gasturbinentriebwerke
FR2704628B1 (fr) * 1993-04-29 1995-06-09 Snecma Chambre de combustion comportant un système d'injection de comburant à géométrie variable.
FR2748553B1 (fr) * 1996-05-09 1998-06-19 Snecma Systeme d'injection a geometrie variable adoptant un debit d'air en fonction du regime moteur
FR2754590B1 (fr) * 1996-10-16 1998-11-20 Snecma Dispositif d'alimentation en comburant d'une turbine a gaz comprenant des diaphragmes de reglage du debit commandes par paires
FR2779807B1 (fr) * 1998-06-11 2000-07-13 Inst Francais Du Petrole Chambre de combustion de turbine a gaz a geometrie variable
EP1312865A1 (de) * 2001-11-15 2003-05-21 Siemens Aktiengesellschaft Ringbrennkammer für eine Gasturbine
US7000396B1 (en) * 2004-09-02 2006-02-21 General Electric Company Concentric fixed dilution and variable bypass air injection for a combustor
US8276386B2 (en) * 2010-09-24 2012-10-02 General Electric Company Apparatus and method for a combustor
US9709279B2 (en) 2014-02-27 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9709278B2 (en) 2014-03-12 2017-07-18 General Electric Company System and method for control of combustion dynamics in combustion system
US9644846B2 (en) 2014-04-08 2017-05-09 General Electric Company Systems and methods for control of combustion dynamics and modal coupling in gas turbine engine
US9845956B2 (en) 2014-04-09 2017-12-19 General Electric Company System and method for control of combustion dynamics in combustion system
US9845732B2 (en) 2014-05-28 2017-12-19 General Electric Company Systems and methods for variation of injectors for coherence reduction in combustion system
US9551283B2 (en) * 2014-06-26 2017-01-24 General Electric Company Systems and methods for a fuel pressure oscillation device for reduction of coherence
US10113747B2 (en) 2015-04-15 2018-10-30 General Electric Company Systems and methods for control of combustion dynamics in combustion system

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2174672A1 (de) * 1972-03-06 1973-10-19 Snecma
US3869246A (en) * 1973-12-26 1975-03-04 Gen Motors Corp Variable configuration combustion apparatus
US3902316A (en) * 1974-10-15 1975-09-02 Gen Motors Corp Deceleration detector
EP0030880A1 (de) * 1979-12-13 1981-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injektor für eine Gasturbinenbrennkammer
FR2572463A1 (fr) * 1984-10-30 1986-05-02 Snecma Systeme d'injection a geometrie variable.
EP0192266A2 (de) * 1985-02-22 1986-08-27 Hitachi, Ltd. Gasturbinenbrennkammer

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2020416A1 (de) * 1970-04-27 1971-11-11 Motoren Turbinen Union Brennkammer fuer Gasturbinentriebwerke
US3941313A (en) * 1972-03-06 1976-03-02 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Jet engine nacelle with drag augmenter auxiliary for thrust-reverser system
GB2085146B (en) * 1980-10-01 1985-06-12 Gen Electric Flow modifying device
FR2585770B1 (fr) * 1985-08-02 1989-07-13 Snecma Dispositif d'injection a bol elargi pour chambre de combustion de turbomachine
FR2596102B1 (fr) * 1986-03-20 1988-05-27 Snecma Dispositif d'injection a vrille axialo-centripete

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2174672A1 (de) * 1972-03-06 1973-10-19 Snecma
US3869246A (en) * 1973-12-26 1975-03-04 Gen Motors Corp Variable configuration combustion apparatus
US3902316A (en) * 1974-10-15 1975-09-02 Gen Motors Corp Deceleration detector
EP0030880A1 (de) * 1979-12-13 1981-06-24 Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." Injektor für eine Gasturbinenbrennkammer
FR2572463A1 (fr) * 1984-10-30 1986-05-02 Snecma Systeme d'injection a geometrie variable.
EP0192266A2 (de) * 1985-02-22 1986-08-27 Hitachi, Ltd. Gasturbinenbrennkammer

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0514260A1 (de) * 1991-05-16 1992-11-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Luftzufuhrregeleinrichtung für eine Gasturbine
FR2676529A1 (fr) * 1991-05-16 1992-11-20 Snecma Dispositif d'alimentation en comburant d'une turbine a gaz comprenant des diaphragmes de reglage du debit.
US5230212A (en) * 1991-05-16 1993-07-27 Societe Nationale d'Etude et de Construction de Moteurs "S.N.E.C.M.A." Oxidizer supply control system for a gas turbine engine
FR2939171A1 (fr) * 2008-11-28 2010-06-04 Snecma Turbomachine a systemes d'injection de carburant distincts, utilisant des joints d'etancheite identiques.
US8505311B2 (en) 2008-11-28 2013-08-13 Snecma Turbomachine with separate fuel injection systems, using identical sealing joints

Also Published As

Publication number Publication date
FR2661714A1 (fr) 1991-11-08
DE69100735D1 (de) 1994-01-20
FR2661714B1 (fr) 1994-06-17
US5159807A (en) 1992-11-03
DE69100735T2 (de) 1994-04-28
EP0455559B1 (de) 1993-12-08

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