EP0251895A1 - Gasturbinenringbrennkammer mit Primärluftregeleinrichtung - Google Patents

Gasturbinenringbrennkammer mit Primärluftregeleinrichtung Download PDF

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Publication number
EP0251895A1
EP0251895A1 EP87401444A EP87401444A EP0251895A1 EP 0251895 A1 EP0251895 A1 EP 0251895A1 EP 87401444 A EP87401444 A EP 87401444A EP 87401444 A EP87401444 A EP 87401444A EP 0251895 A1 EP0251895 A1 EP 0251895A1
Authority
EP
European Patent Office
Prior art keywords
cap
combustion chamber
chamber
external
rotation
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
EP87401444A
Other languages
English (en)
French (fr)
Other versions
EP0251895B1 (de
Inventor
Gérard Marcel François Mandet
Rodolphe Martinez
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.)
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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 EP0251895A1 publication Critical patent/EP0251895A1/de
Application granted granted Critical
Publication of EP0251895B1 publication Critical patent/EP0251895B1/de
Expired 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • 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

  • the present invention relates to annular combustion chambers, in particular for turbomachines comprising so-called variable geometry injectors.
  • One solution consists in continuously adapting, depending on the engine speed, the distribution of the air flow intended to form the fuel-air fuel mixture by means of movable shutters capable of diaphragm glus or less the air inlets associated with the injectors.
  • This type of control means poses two problems, one relating to the existence of as many rods, forks and other levers, in the vein, as there are injectors thus disturbing the flow of the cooling gases of the external wall of the chamber, the other problem coming from the large number of control devices passing through the casing and the sealing of which must be ensured in an identical and multiplied manner.
  • the synchronization of the diaphragms is carried out by a ring positioned between the chamber casing and the external wall of the chamber and connecting the levers of the various diaphragms.
  • This type of ring also has the drawback of disturbing the flow of cooling gases from the external wall and of preventing the production of a regular cooling wall film.
  • each diaphragm control lever passes through the cylindrical surface of the chamber and the roller bearing, which in turn makes the realization somewhat illusory, on the other hand due to a very poor guiding of the cooling air on the external wall of the chamber and towards the external swirl of the injector and by the presence of a cavity annular formed by the cylindrical bearing surface carrying the control ring, this cavity forming a dead end around the injector and creating uncontrolled turbulence which disturbs the guiding of the air towards the spin.
  • the object of the present invention is to improve control devices for this type of combustion chamber with variable geometry injectors by eliminating the control rings arranged in the vein between the chamber casing and the external wall of the chamber and avoiding also the control rings external to the casing, while ensuring optimal synchronization of rotation of all the diaphragms.
  • the invention also aims to allow this control of the diaphragms on a combustion chamber comprising on its outer wall a rounded circular ferrule, called a cap, ensuring the guiding of the air on the one hand towards the injection devices and on the other hand towards the external wall to produce a parietal film, without disturbing said cooling film.
  • the invention therefore relates to an annular combustion chamber, in particular for turbomachines comprising a series of air and fuel injectors with axes parallel to the longitudinal axis of symmetry of the chamber, regularly distributed in a crown on the bottom chamber, each injector having an external swirl swirl intended for the introduction into the injection device of a first fraction of air to form a fuel air-fuel mixture.
  • the external turbulence tendrils are formed of fins defining channels which can be closed by a movable diaphragm in rotation around the injector, the combustion chamber comprises on the radially external part of its chamber bottom a cap with quarter-round section oriented downstream, said cap being capable of guiding the first fraction of the compressed air in the vein towards the injection device and a second fraction of said compressed air towards the external wall of the combustion chamber to ensure cooling by external convection.
  • the cap is made to rotate about the longitudinal axis of symmetry of the combustion chamber under the action of a first control means and comprises second means for simultaneously driving each diaphragm in rotation by the external turbulence spin of each injector around the axis of the latter.
  • the second means for simultaneously driving all the diaphragms in rotation are constituted by lugs regularly distributed over the upstream part of the cap, the number of lugs being equal to that of the diaphragms whose rotation movement must be controlled, each lug cooperating with a fork carried by the diaphragm which it controls.
  • a rotary bearing means can be interposed between the cap and the external wall of the combustion chamber, this means possibly being, according to a preferred embodiment, constituted by a ball ring in rolling contact on a first biconical circular track of the inner part of the cap and on a second circular track of the outer wall of the chamber, or according to a second embodiment, by a ring made of anti-friction material.
  • annular combustion chamber for a turbomachine in particular for an aviation turbojet engine, is formed of an internal wall 1 and an external wall 2, each formed of several successive rings making between them an annular chamber of which the bottom chamber 3 receives a number of devices 4 for injecting air and fuel regularly distributed in a ring around its periphery.
  • the injection devices 4 will be described in more detail with reference to Figures 2 and following.
  • a ferrule 5 of quarter-round section here called a cap surmounts the chamber bottom 3 and the upstream part of the external wall 2 to distribute a first fraction F1 of the flow of compressed air coming from the compressor (located upstream of the chamber and not shown here) to the injection devices 4 and a second fraction F2 of the compressed air flow to the annular space between the outer wall 2 of the chamber and the chamber casing 6, this fraction F2 of the flow having for purpose on the one hand to ensure the external cooling of the walls of the chamber, and on the other hand to enter the chamber through mixing orifices 7 and dilution 8 to be mixed there with the fuel vaporized by the injection devices , mixture which will be burned and to bring the temperature of the air leaving the combustion chamber to a level compatible with the maximum temperature allowable by the high pressure turbine stages located downstream of the chamber and not shown here.
  • each injection device 4 comprises a central fuel injector 9, an internal spin 10 and an external turbulence spin 11, the two spins 10 and 11 cooperating with the injector 9 to deliver into the intermediate bowl 12 a sheet of sprayed fuel.
  • a diaphragm 13 makes it possible to continuously open or close the external spin 12 to adapt the air flow that it delivers to the engine speed.
  • the cap 5 is rotatably mounted on the upstream part of the external wall 2 by means of a ball ring formed by a cylindrical cage 14 pierced with round holes for housing the balls 15 and of which the downstream part 14a is curved outward to come into abutment against a step 16 of the cap 5 during assembly of the assembly, as will be seen later .
  • the balls 15 are in rolling contact on the one hand on a first circular biconical track 17 produced on the internal part of the cap 5 and on the other hand on a second biconical track produced by the cooperation of two parts: the upstream end frustoconical 2a of the external upstream shell 2 and a frustoconical bearing 18a of an internal ring 18 disposed internally at the shell upstream of the external wall 2.
  • the ring 18 comprises a single orifice 18b intended for the successive introduction of the balls 15 into the holes of the cage 14 and also comprises regularly distributed bores 18c intended to cooperate with bores 2b the ferrule 2 to allow the fixing of the internal ring on the ferrule by bolts 19.
  • the rotation of the cap 5 is obtained by a control device comprising a rotating shaft 20 mounted by means of a sealing gland 21 through the chamber casing, the shaft 20 bearing on its inside end of the housing, a fork 22 which is engaged with a single radial ball joint 23 carried by the cap 5.
  • the shaft 20 is rotated externally to the casing 6 by any known mechanical means (gear and rack system, link %), hydraulic (cylinder and link) or electrohydraulic controlled by the turbojet regulator.
  • the cap 5 rotates the diaphragms 13 of each injection device 4 by means of a threaded lug 21 cooperating with one end 21a, eccentric with respect to its thread, engaged in a fork 13a of the diaphragm 13.
  • the internal ring 18 is then placed under the ferrule 2 in the position in FIG. 3 where the orifice 18b for introducing the balls is released from the ferrule 2.
  • the cage 14 and then the cap 5 are put in place.
  • the balls 15 are then introduced one by one through the orifice 18b of the ring 18 and are positioned in the holes of the cage 14, the internal ring 18 being able to rotate freely thus makes it possible to compare the orifice 18b with each of the cage positioning holes 14.
  • the internal ring is then put in place by sliding under the ferrule 2 which then masks the orifice 18b until coincidence of the bores 2b and 18c, then secured for the bolts 19 whose screws are introduced through a notch 24 unique from the downstream edge of the cap 5 which can rotate freely.
  • the establishment of the ring 18 realizes the formation of the second biconical track formed of the frustoconical surfaces 2a, 18a forming the internal raceway of the balls 15, the cap 5 is pushed back towards the chamber bottom at the same time as the internal ring 18, which positions the ball ring on its two rolling tracks 17 and 2a, 18a.
  • the eccentric pins 21 can then be screwed into the bores 22, having first taken care to have engaged the locknuts 25, the ends 21a of the pins being positioned in the forks 13a of the diaphragms 13.
  • the diaphragms are adjusted by bringing all the injectors back to the full opening (or full closing) position (and the locknuts 25 can then be tightened to block the lugs, thus making it possible to synchronize the opening of all the injectors.
  • the fork 22 of the first means for controlling the rotation of the cap can be engaged on the ball 23 of the cap and then be secured to the shaft 20.
  • a sealing device for the bearing means formed by the ball ring or the ring 30 can be provided for example by adding internally to the cap 5 a radial ring 31 ( shown only in Figure 5) which will be (once the cap in position) upstream of the rolling means to prevent impurities (fatty substances, dust, etc.) from entering it.
  • the control device as provided by the present invention has the advantage of leaving in the vein a minimum number of parts since a single fork 22 and a single ball joint 23 allows the rotation of the cap which itself will cause around their respective axes the rotation of all the diaphragms simultaneously, the cap always fulfilling its function of guiding the air without the air flow being disturbed by additional elements introduced into the vein.
  • the device in its preferred mode of embodiment where the rolling contact is made by means of a ball ring is simple enough to function correctly in the whole temperature range of use of the combustion chamber by means of a suitable calculation of the clearances between the cap, the balls and the inner ring. These clearances will be made up thanks to the axial force exerted by the air on the cap and the biconical shape of the two rolling tracks. Thus in operation, the cap will remain self-centered with respect to the chamber while supporting the relative expansions without jamming.
  • the materials used can remain the same as on a conventional chamber, for example the superalloy known under the trade name "Hastelloy X" with possibly a hardening surface treatment on the conical tracks.
  • injectors of different types can be combined with the devices with intermediate bowls previously mentioned.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
EP87401444A 1986-07-03 1987-06-24 Gasturbinenringbrennkammer mit Primärluftregeleinrichtung Expired EP0251895B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8609652 1986-07-03
FR8609652A FR2601115B1 (fr) 1986-07-03 1986-07-03 Chambre de combustion annulaire comportant un moyen de commande unique des diaphragmes d'injecteurs

Publications (2)

Publication Number Publication Date
EP0251895A1 true EP0251895A1 (de) 1988-01-07
EP0251895B1 EP0251895B1 (de) 1989-10-11

Family

ID=9337020

Family Applications (1)

Application Number Title Priority Date Filing Date
EP87401444A Expired EP0251895B1 (de) 1986-07-03 1987-06-24 Gasturbinenringbrennkammer mit Primärluftregeleinrichtung

Country Status (4)

Country Link
US (1) US4825641A (de)
EP (1) EP0251895B1 (de)
DE (1) DE3760766D1 (de)
FR (1) FR2601115B1 (de)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992017736A1 (de) * 1991-03-30 1992-10-15 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Brenner für gasturbinentriebwerke
DE4228816A1 (de) * 1992-08-29 1994-03-03 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke
US5357743A (en) * 1992-08-29 1994-10-25 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Burner for gas turbine engines
FR3141755A1 (fr) 2022-11-08 2024-05-10 Safran Aircraft Engines Chambre de combustion d’une turbomachine

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6415610B1 (en) * 2000-08-18 2002-07-09 Siemens Westinghouse Power Corporation Apparatus and method for replacement of combustor basket swirlers
GB0811741D0 (en) * 2008-06-27 2008-07-30 Rolls Royce Plc A fuel control arrangement

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2457157A (en) * 1946-07-30 1948-12-28 Westinghouse Electric Corp Turbine apparatus
FR2572463A1 (fr) * 1984-10-30 1986-05-02 Snecma Systeme d'injection a geometrie variable.

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3490230A (en) * 1968-03-22 1970-01-20 Us Navy Combustion air control shutter
DE2028546C3 (de) * 1970-05-29 1979-12-13 Gebrueder Sulzer Ag, Winterthur (Schweiz) Wirbelbrenner
US3932110A (en) * 1974-09-12 1976-01-13 Foster Wheeler Energy Corporation Intervane burners
GB2085147A (en) * 1980-10-01 1982-04-21 Gen Electric Flow modifying device
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
FR2588919B1 (fr) * 1985-10-18 1987-12-04 Snecma Dispositif d'injection a bol sectorise
FR2596102B1 (fr) * 1986-03-20 1988-05-27 Snecma Dispositif d'injection a vrille axialo-centripete

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2457157A (en) * 1946-07-30 1948-12-28 Westinghouse Electric Corp Turbine apparatus
FR2572463A1 (fr) * 1984-10-30 1986-05-02 Snecma Systeme d'injection a geometrie variable.

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1992017736A1 (de) * 1991-03-30 1992-10-15 MTU MOTOREN- UND TURBINEN-UNION MüNCHEN GMBH Brenner für gasturbinentriebwerke
US5490378A (en) * 1991-03-30 1996-02-13 Mtu Motoren- Und Turbinen-Union Muenchen Gmbh Gas turbine combustor
DE4228816A1 (de) * 1992-08-29 1994-03-03 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke
US5357743A (en) * 1992-08-29 1994-10-25 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Burner for gas turbine engines
US5373693A (en) * 1992-08-29 1994-12-20 Mtu Motoren- Und Turbinen-Union Munchen Gmbh Burner for gas turbine engines with axially adjustable swirler
DE4228816C2 (de) * 1992-08-29 1998-08-06 Mtu Muenchen Gmbh Brenner für Gasturbinentriebwerke
FR3141755A1 (fr) 2022-11-08 2024-05-10 Safran Aircraft Engines Chambre de combustion d’une turbomachine

Also Published As

Publication number Publication date
EP0251895B1 (de) 1989-10-11
FR2601115A1 (fr) 1988-01-08
US4825641A (en) 1989-05-02
FR2601115B1 (fr) 1988-09-02
DE3760766D1 (en) 1989-11-16

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