EP0059137A1 - Zündvorrichtung für Brennstoff, der in einem schnellströmenden Gasstrom eingespritzt wird - Google Patents

Zündvorrichtung für Brennstoff, der in einem schnellströmenden Gasstrom eingespritzt wird Download PDF

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Publication number
EP0059137A1
EP0059137A1 EP82400222A EP82400222A EP0059137A1 EP 0059137 A1 EP0059137 A1 EP 0059137A1 EP 82400222 A EP82400222 A EP 82400222A EP 82400222 A EP82400222 A EP 82400222A EP 0059137 A1 EP0059137 A1 EP 0059137A1
Authority
EP
European Patent Office
Prior art keywords
enclosure
ignition
catalytic
fuel
tubular conduit
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
EP82400222A
Other languages
English (en)
French (fr)
Other versions
EP0059137B1 (de
Inventor
Gérard Joseph Pascal Bayle-Laboure
Marc François Bernard Buisson
Roger Bernard Linstrumelle
Jean-Claude Pachot
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 EP0059137A1 publication Critical patent/EP0059137A1/de
Application granted granted Critical
Publication of EP0059137B1 publication Critical patent/EP0059137B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C13/00—Apparatus in which combustion takes place in the presence of catalytic material
    • 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
    • F23R3/40—Continuous combustion chambers using liquid or gaseous fuel characterised by the use of catalytic means

Definitions

  • the invention relates to a fuel ignition device injected into a gaseous oxidizing medium in rapid flow, usable in particular for the ignition of the heating of an aviation turbojet.
  • French patent No. 2,351,258 discloses an ignition device comprising an enclosure placed in a gas flow and provided with an ignition member such as a spark plug.
  • This known device is characterized in that said enclosure receives through a grid or perforated inlet plate a fuel mixture which is ignited in said enclosure by said device, and is provided with a tubular conduit receiving at its upstream end a jet of fuel which it discharges, with gases taken up by said upstream end in said flow, in said enclosure downstream from said ignition member.
  • the ignition member such as a candle ceases to be supplied, so that the enclosure of the ignition device is not permanently lit.
  • the present invention relates to an improvement of the ignition device described above, the object of this improvement being essentially to improve the operation of the ignition device, in particular at high temperatures.
  • the fuel ignition device injected into a gaseous oxidizing medium in rapid flow is of the type which has just been indicated, and it is characterized in that the enclosure, provided with an ignition member such as an electric spark plug, further comprises a catalytic ignition element, which is disposed in said enclosure upstream from the downstream end of the tubular conduit intended to discharge a jet of fuel, and outside of, for example, around said tubular conduit.
  • the additional element of catalytic ignition which is provided according to the present invention, offers a double advantage: on the one hand, as the element of catalytic ignition acts only on gases brought to an already high temperature, of the order of 350 ° C., this additional ignition device supplements the ignition member such as an electric candle, in the operating range of the turbojet engine which corresponds to the high gas temperatures, so as to increase reliability of the ignition device in this operating range.
  • the catalytic ignition element being able to act permanently, without consuming energy, it makes it possible to use the ignition device according to the present invention to produce a pilot flame.
  • French Patent No. 1,454,312 describes a device for igniting fuel injected into a stream of oxidizing gas, comprising at least one catalytic element disposed in a circulation passage inside a mass of refractory material. It is further indicated that the catalytic element or elements can be used for post-combustion in the ejection nozzle of a turbojet engine.
  • an ignition device devoid of an ignition member such as an electric candle, malfunctions at low temperatures de.s-ejected gases.
  • the purely catalytic action ignition device which is described in this prior patent, needs to be supplied with a flow of pressurized air, derived from the outlet of the compressors of the turbojet; some of its achievements also require a special fuel supply.
  • the ignition device according to the present invention therefore offers the additional advantage of not requiring any special supply of compressed air and possibly fuel, since, as already indicated in the patent 2 351 258, the ignition device according to the present invention is supplied directly by the hot gases which the turbine sends into the afterburner channel and by the jet of fuel coming from the injection rail mounted in said afterburner channel .
  • French Patent No. 2,382,584 describes a gas turbine in the combustion chamber of which are arranged, in series, a pilot burner, powered by a fuel injector and associated with a conventional electrical ignition device, as well as a catalytic combustion zone, placed downstream of the combustion chamber.
  • a conventional electrical ignition device powered by a fuel injector and associated with a conventional electrical ignition device, as well as a catalytic combustion zone, placed downstream of the combustion chamber.
  • the conventional ignition device and the catalytic element do not act on the same mass of gas, and they are obviously not arranged in the same ignition device usable for the post-combustion of a turbojet.
  • US Patent No. 4,040,252 describes a combustion chamber comprising an axial premix section, into which the fuel is injected, the stream of hot gases then being guided towards a peripheral section, of annular shape, containing catalytic elements.
  • the means used to ignite the fuel in the premix chamber does not act on the same mass of gas as that which passes through the catalytic elements. Nor is it an ignition device for afterburning.
  • the ignition device is capable of two main embodiments; these differ from each other in that the catalytic ignition element is disposed in the enclosure, in a first embodiment, downstream from the part of the ignition member such as a candle, which penetrates into said enclosure, and, in the case of the other embodiment, at the level, and preferably facing the part of the ignition member such as a candle, which penetrates into said enclosure.
  • the action of the catalytic ignition element takes place in series in the case of the first form of realization, and in parallel in the case of the second.
  • FIG. 1 shows in axial section an ignition device according to the present invention, which can be. mounted in particular in the post-combustion channel of an aviation turbojet, like the ignition device 11 illustrated in FIGS. 1 and 2 of patent 2 351 258.
  • the reference 1 designates an envelope of generally tubular shape, open at its two ends; this tubular casing 1 has a constant diameter over most of its length, and a slightly larger diameter in its upstream part 1a, which is arranged opposite the injection rail 2 and the anvil 3, as described in patent 2,351,258.
  • a grid 4 which is fixed by its flange 4a to the wall of said upstream part 1a, by suitable means, for example rivets 5.
  • the perforations of the grid 4 are determined so as to calibrate the flow rate of the gaseous mixture which penetrates inside the tubular casing 1 in the direction of the arrows f.
  • a tubular conduit 6, for example metallic, is arranged inside the tubular casing 1, coaxially with the latter, the upstream end 6a of the tubular conduit 6 passes through a central hole of the grid 4 which thus serves as its support.
  • An ignition member such as an electric candle 7 is engaged by its active end 7a inside the envelope 1, through an opening 1b arranged in the middle part of its side wall. The tightness of the envelope 1 at the level of the spark plug 7 is ensured by a sleeve 8.
  • a catalytic ignition element the assembly of which is designated by 9, is disposed in the tubular enclosure 1, upstream from the downstream end 6b of the tubular conduit 6, and around said tubular conduit 6.
  • the ignition element catalytic 9 is further placed, in enclosure 1, downstream from part 7a of the spark plug 7 which enters enclosure 1, said catalytic element 9 being placed between two transverse grids 10a and 10b, made of or coated with a refractory material, and inside an envelope also made of refractory material; in the embodiment considered, this refractory envelope is constituted by two half-shells, 11a and 11b, inserted between the two grids, 10a and 10b.
  • the catalytic element, itself 9, is constituted for example by wire mesh or metallic foam, in particular platinum foam.
  • the internal wall of the enclosure 1 and the external wall of the tubular conduit 6 are also coated with a refractory material, at least in their parts comprised between the two grids 10a and 10b.
  • the assembly 9-10a-10b -11a-11b is preferably engaged with gentle friction in the annular space between the tubular casing 1 and the tubular conduit 6, so that it can be easily extracted from said annular space by the open downstream end of the tubular enclosure 1, so as to facilitate the exchange of the catalytic ignition element 9 when its operation ceases to be satisfactory.
  • Stop means are advantageously provided, such as for example a circlip upstream of the grid 10a and a circlip downstream of the grid 10b, which can be accommodated in grooves provided for this purpose in the tubular casing 1.
  • the ignition device illustrated in FIG. 1 and previously described operates as follows: the injection rail 2 projects, by its upstream nozzles, 2a, fuel which is sprayed onto the anvil 3; the fuel thus pulverized is entrained by the flow of hot gases, coming from the turbine (not shown) in the direction- indicated by the arrows f, the gas mixture entering the annular enclosure 1 through the perforations of the grid 4. At the same time, the downstream nozzle 2b of the injection manifold 2 projects fuel into the tubular conduit 6, as described in the main patent.
  • the electric spark plug 7 is supplied and it effectively produces the ignition of the gas mixture which is located in the annular space between the tubular enclosure 1 and the tubular conduit 6; the combustion gas mixture then passes through the grid 10a, the catalyst element 9, and the grid 10b, then leaves the enclosure 1 via its open downstream end, at which the gas mixture causes the ignition of the fuel leaving the downstream end of the tubular conduit 6b, as described in patent 2,351,258.
  • the catalytic action of the catalyst element 9 is practically negligible due to its low temperature; its temperature rises gradually, however. by heat exchange with the gas mixture in combustion which passes through it.
  • the catalytic element 9 When the catalytic element 9 reaches a temperature of the order of 350 ° C., said catalytic element functions as an ignition element, so that the electric spark plug 7 can cease to be supplied.
  • FIGS. 2 and 3 which represent a second embodiment, the same references have been used to designate bodies which are homologous to those of the embodiment of FIG. 1.
  • This second embodiment differs from that illustrated in the FIG. 1, only in that the catalytic ignition element 9 is disposed in the enclosure 1 at, and even opposite the part 7a of the electric spark plug 7 which enters the enclosure 1. Consequently, when the electric candle 7 is powered and that the catalytic element 9 has been brought to a sufficient temperature, the two ignition elements act in parallel on the gas mixture which passes through the annular space between the enclosure 1 and the conduit 6, whereas, in the same conditions, they acted in series on the gas mixture in the case of the embodiment of FIG. 1.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Exhaust Gas After Treatment (AREA)
EP82400222A 1981-02-17 1982-02-09 Zündvorrichtung für Brennstoff, der in einem schnellströmenden Gasstrom eingespritzt wird Expired EP0059137B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR8103046 1981-02-17
FR8103046A FR2500064B2 (fr) 1981-02-17 1981-02-17 Dispositif d'allumage de carburant injecte dans un milieu gazeux en ecoulement rapide

Publications (2)

Publication Number Publication Date
EP0059137A1 true EP0059137A1 (de) 1982-09-01
EP0059137B1 EP0059137B1 (de) 1985-05-15

Family

ID=9255273

Family Applications (1)

Application Number Title Priority Date Filing Date
EP82400222A Expired EP0059137B1 (de) 1981-02-17 1982-02-09 Zündvorrichtung für Brennstoff, der in einem schnellströmenden Gasstrom eingespritzt wird

Country Status (5)

Country Link
US (1) US4455822A (de)
EP (1) EP0059137B1 (de)
JP (1) JPS57153929A (de)
DE (1) DE3263471D1 (de)
FR (1) FR2500064B2 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0702135A1 (de) * 1994-04-14 1996-03-20 Precision Combustion, Inc. Brennstoffeinspritz- und Zündeinheit

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5660043A (en) * 1992-02-14 1997-08-26 Precision Combustion, Inc. Torch assembly
US5720163A (en) * 1992-02-14 1998-02-24 Precision Combustion, Inc. Torch assembly
US5636511A (en) * 1992-02-14 1997-06-10 Precision Combustion, Inc. Torch assembly
JP4784181B2 (ja) * 2005-07-06 2011-10-05 マックス株式会社 換気装置及び建物
US20110067685A1 (en) * 2009-09-23 2011-03-24 Myers Robert L Gas-Fueled Food Cooker with a Sealed Heating Conduit
US9562692B2 (en) 2013-02-06 2017-02-07 Siemens Aktiengesellschaft Nozzle with multi-tube fuel passageway for gas turbine engines
US10352571B2 (en) * 2016-01-15 2019-07-16 General Electric Company Catalytic ignition system
CN112502839A (zh) * 2020-11-27 2021-03-16 陕西航空电气有限责任公司 一种航空发动机催化点火装置

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612060A (en) * 1946-05-16 1948-11-08 Havilland Engine Co Ltd Improvements in or relating to turbo-compressor apparatus
US2964907A (en) * 1957-11-15 1960-12-20 Rolls Royce Combustion stabilising device for combustion equipment
FR1454312A (fr) * 1964-11-19 1966-09-30 Rolls Royce Dispositif d'allumage pour moteurs
FR2154422A1 (de) * 1971-07-01 1973-05-11 Rolls Royce
DE2308688A1 (de) * 1973-02-22 1974-08-29 Volkswagenwerk Ag Startvorrichtung fuer reaktionsvergaser
US4033133A (en) * 1976-03-22 1977-07-05 California Institute Of Technology Start up system for hydrogen generator used with an internal combustion engine
FR2337306A1 (fr) * 1975-12-29 1977-07-29 Engelhard Min & Chem Procede et appareil pour bruler un combustible carbone
US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
FR2351258A1 (fr) * 1976-05-13 1977-12-09 Snecma Dispositif d'allumage de carburant injecte dans un milieu gazeux en ecoulement rapide
FR2360042A1 (fr) * 1976-07-26 1978-02-24 Engelhard Min & Chem Procede et appareil de combustion
FR2375543A1 (fr) * 1976-12-22 1978-07-21 Engelhard Min & Chem Procede pour effectuer la combustion entretenue d'un combustible carbone
FR2382584A1 (fr) * 1977-03-04 1978-09-29 Johnson Matthey Co Ltd Turbine a gaz

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5239008A (en) * 1975-09-16 1977-03-26 Westinghouse Electric Corp Method of starting catalist combustor equipped turbine

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB612060A (en) * 1946-05-16 1948-11-08 Havilland Engine Co Ltd Improvements in or relating to turbo-compressor apparatus
US2964907A (en) * 1957-11-15 1960-12-20 Rolls Royce Combustion stabilising device for combustion equipment
FR1454312A (fr) * 1964-11-19 1966-09-30 Rolls Royce Dispositif d'allumage pour moteurs
FR2154422A1 (de) * 1971-07-01 1973-05-11 Rolls Royce
DE2308688A1 (de) * 1973-02-22 1974-08-29 Volkswagenwerk Ag Startvorrichtung fuer reaktionsvergaser
FR2337306A1 (fr) * 1975-12-29 1977-07-29 Engelhard Min & Chem Procede et appareil pour bruler un combustible carbone
US4040252A (en) * 1976-01-30 1977-08-09 United Technologies Corporation Catalytic premixing combustor
US4033133A (en) * 1976-03-22 1977-07-05 California Institute Of Technology Start up system for hydrogen generator used with an internal combustion engine
FR2351258A1 (fr) * 1976-05-13 1977-12-09 Snecma Dispositif d'allumage de carburant injecte dans un milieu gazeux en ecoulement rapide
FR2360042A1 (fr) * 1976-07-26 1978-02-24 Engelhard Min & Chem Procede et appareil de combustion
FR2375543A1 (fr) * 1976-12-22 1978-07-21 Engelhard Min & Chem Procede pour effectuer la combustion entretenue d'un combustible carbone
FR2382584A1 (fr) * 1977-03-04 1978-09-29 Johnson Matthey Co Ltd Turbine a gaz

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0702135A1 (de) * 1994-04-14 1996-03-20 Precision Combustion, Inc. Brennstoffeinspritz- und Zündeinheit

Also Published As

Publication number Publication date
JPS57153929A (en) 1982-09-22
FR2500064B2 (fr) 1985-11-08
EP0059137B1 (de) 1985-05-15
FR2500064A2 (fr) 1982-08-20
DE3263471D1 (en) 1985-06-20
JPS6215736B2 (de) 1987-04-09
US4455822A (en) 1984-06-26

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