US20180149365A1 - Turbine engine cvc combustion chamber module comprising a pre-combustion chamber - Google Patents

Turbine engine cvc combustion chamber module comprising a pre-combustion chamber Download PDF

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Publication number
US20180149365A1
US20180149365A1 US15/578,316 US201615578316A US2018149365A1 US 20180149365 A1 US20180149365 A1 US 20180149365A1 US 201615578316 A US201615578316 A US 201615578316A US 2018149365 A1 US2018149365 A1 US 2018149365A1
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United States
Prior art keywords
combustion
combustion chamber
constant
type
volume
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.)
Abandoned
Application number
US15/578,316
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English (en)
Inventor
Guillaume TALIERCIO
Christophe Nicolas Henri Viguier
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines 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
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Assigned to SAFRAN HELICOPTER ENGINES reassignment SAFRAN HELICOPTER ENGINES ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: TALIERCIO, Guillaume, VIGUIER, CHRISTOPHE NICOLAS HENRI
Publication of US20180149365A1 publication Critical patent/US20180149365A1/en
Abandoned legal-status Critical Current

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    • 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/02—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion characterised by the arrangement of the combustion chamber in the chamber in the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/12—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the combustion chambers having inlet or outlet valves, e.g. Holzwarth gas-turbine plants
    • 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
    • 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
    • F23C13/06—Apparatus in which combustion takes place in the presence of catalytic material in which non-catalytic combustion takes place in addition to catalytic combustion, e.g. downstream of a catalytic element
    • 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
    • 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
    • F23R7/00—Intermittent or explosive combustion chambers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • 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 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/03002—Combustion apparatus adapted for incorporating a fuel reforming device
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2227/00—Ignition or checking
    • F23N2227/40—Catalytic ignition

Definitions

  • the present invention relates to the field of turbomachines, and more particularly to field of constant-volume combustion type turbomachine combustion chambers.
  • the invention is applicable to any type of terrestrial or aeronautical turbomachines, and for example to aircraft turbomachines such as turbojet engines and turboprop engines.
  • turbomachine combustion chamber including a pre-combustion chamber
  • turbomachine including such a combustion chamber module
  • a turbomachine combustion chamber operates according to the Brayton thermodynamic cycle, with a so-called constant-pressure combustion.
  • patent application FR 2 945 316 A1 describes making a CVC type combustion chamber.
  • the chamber comprises at the input a compressed gas intake valve able to switch between an open position and a closed position, and includes at the output a burnt gas exhaust valve also able to switch between an open position and a closed position.
  • the positions of the valves are driven in a synchronised way in order to implement the three successive phases of the Humphrey cycle, namely intake-combustion-exhaust.
  • the Humphrey cycle implies to preserve the load during some period of time in a physically enclosed volume.
  • This operating mode induces a pulsed regimen. Indeed, the air from the compressor is taken in inside the combustion chamber. Then, after the cams are closed, a spark initiates the combustion in the chamber. Once this combustion is ended, the chamber is opened to let hot gases escape to the turbine in order to produce power, or directly to the nozzle in order to produce aerodynamic pressure.
  • the constant-volume combustion process of a Humphrey cycle combustion chamber requires energy input to each combustion cycle in order to be able to trigger a combustion by propagation of a flame front.
  • a combustion requires a significant energy which is repeated over time.
  • One purpose of the invention is therefore to fulfil at least partially the abovementioned needs and drawbacks related to embodiments of prior art.
  • the invention aims at providing an alternative solution of energy input necessary to the ignition of a constant-volume combustion type turbomachine combustion chamber.
  • turbomachine combustion chamber module including at least one constant-volume combustion type combustion chamber, characterised in that it further includes, upstream of said at least one constant-volume combustion type combustion chamber, a pre-combustion chamber capable of producing hot combustion gases supplying said at least one constant-volume combustion type combustion chamber to allow the ignition thereof.
  • the invention can be possible to produce, upstream of the CVC type combustion chamber(s) of a combustion module in accordance with the invention, through a pre-combustion chamber, hot gases feeding the energy necessary to the ignition of the CVC type combustion chamber(s).
  • the invention can enable a desired capacity to be provided for allowing the ignition of the CVC type combustion chamber(s) under so-called “severe” operating conditions, in particular in case of cold and high altitude.
  • the invention can make it possible to integrate, on a turbomachine combustion module, a specific system for the thermal ignition of one or more CVC type combustion chambers, so as to limit the engine destabilisation and to optimise the engine efficiency.
  • the combustion chamber module according to the invention can further include one or more of the following characteristics taken alone or according to any technically possible combinations.
  • the pre-combustion chamber is of the constant-pressure combustion type, implementing an isobaric process.
  • Said at least one combustion chamber being of the CVC type, it advantageously includes a compressed gas intake valve able to assume an open position as well as a closed position in which it opposes to the compressed gas intake, and further a burnt gas exhaust valve able to assume an open position as well as a closed position in which it opposes to the exhaust of burnt gas outside the chamber.
  • the pre-combustion chamber is configured to produce predominantly burnt gases of carbon monoxide and dihydrogen.
  • the module according to the invention can include, downstream of the pre-combustion chamber and upstream of said at least one constant-volume combustion type combustion chamber, an oxidation catalyst module, making it possible in particular to increase the dihydrogen rate of the hot combustion gases supplying said at least one constant-volume combustion type combustion chamber to allow the ignition thereof.
  • the module according to the invention includes a plurality of constant-volume combustion type combustion chambers distributed about an axis of rotation of the turbomachine.
  • the pre-combustion chamber can supply hot combustion gases to the constant-volume combustion type combustion chambers through a rotary distributor type system.
  • one object of the invention is also, according to another of its aspects, to provide a turbomachine, characterised in that it includes a combustion chamber module as previously defined.
  • the combustion chamber module and the turbomachine according to the invention can include any of the previously set-out characteristics, taken alone or according to any technically possible combinations with other characteristics.
  • FIG. 1 represents a side schematic view of a turbojet engine gas generator including an exemplary constant-volume combustion type combustion chamber in accordance with the invention
  • FIG. 2 represents a front schematic view of the combustion chamber module of FIG. 1 .
  • upstream and downstream are to be considered with respect to a main normal flow direction F of the gases (from upstream to downstream) for a turbomachine.
  • axis T of the turbomachine it is meant the radial axis of symmetry of the turbomachine.
  • the axial direction of the turbomachine corresponds to the direction of the axis T of the turbomachine.
  • a radial direction of the turbomachine is a direction perpendicular to the axis T of the turbomachine.
  • the adjectives and adverbs axial, radial, axially and radially are used in reference to the aforementioned axial and radial directions.
  • FIG. 1 there is represented, in a side schematic view, an exemplary embodiment of an aircraft turbomachine gas generator 1 , preferably a turbojet engine, including an exemplary constant-volume combustion CVC type combustion chamber module 4 in accordance with the invention.
  • an aircraft turbomachine gas generator 1 preferably a turbojet engine, including an exemplary constant-volume combustion CVC type combustion chamber module 4 in accordance with the invention.
  • the gas generator 1 includes, conventionally, from upstream to downstream, one or more compressor modules 2 , a combustion chamber module 4 , and one or more turbine modules 3 .
  • the compressor modules 2 and the turbine modules 3 are connected by a shaft system 5 , which drives a receiver of the aircraft turbomachine, for example a fan (not represented) in the case of a turbojet engine.
  • the combustion chamber module 4 includes a plurality of CVC type combustion chambers 7 and, upstream of the same, a pre-combustion chamber 6 capable of producing hot combustion gases supplying the CVC type combustion chambers 7 to allow the ignition thereof.
  • the pre-combustion chamber 6 is of the constant-pressure combustion type. It produces hot gas jets upstream of the CVC type combustion chambers 7 to feed energy required for the ignition thereof.
  • the isobaric pre-combustion chamber 6 is quite particularly employed in a rich operation to produce burnt gases predominantly doped with carbon monoxide CO and dihydrogen H 2 . In this way, these gases are conducive to the ignition of the main CVC type combustion chambers 7 and favour the reduction in the combustion initiation delay with respect to the use of burnt gases produced with a low CO and H 2 richness.
  • FIG. 2 represents, in a front schematic view, transverse to the axis of rotation T of the turbomachine, the combustion chamber module 4 of FIG. 1 .
  • the plurality of combustion chambers 7 of the CVC type is evenly distributed about the shaft system 5 centred on the engine axis T.
  • the CVC type combustion chambers 7 are for example provided to be 4, this number being in no way limiting. They all are preferentially identical.
  • the number of these CVC type combustion chambers 7 is preferentially an even number, so as to be able to neutralise two chamber barrels diametrically opposite in case of abnormality on one of them, and thus avoid dissymmetries of flow at the input of the turbine.
  • the CVC type combustion chambers 7 are arranged in a so-called barrel configuration, by being preferably intended to remain fixed with respect to the engine casing upon operating the turbomachine.
  • Each combustion chamber 7 is of the CVC type, that is closed at its ends by two synchronised intake and exhaust valves in order to implement the three successive phases of the Humphrey cycle, namely intake-combustion-exhaust. Even if they are identical, the CVC type combustion chambers 7 are preferably intentionally phase shifted with respect to each other as regards the implementation of the Humphrey cycle.
  • a given chamber which is in an intake phase could be adjacent to another chamber in a combustion phase, and so on.
  • the isobaric pre-combustion chamber 6 supplies hot combustion gases to the CVC type combustion chambers 7 through a rotary distributor type system 8 , which enables hot gases to be dispensed to the CVC type combustion chambers 7 as represented by the arrows D in FIG. 2 .
  • an oxidation catalyst module downstream of the pre-combustion chamber 6 and upstream of the CVC type combustion chambers 7 , an oxidation catalyst module.
  • This oxidation catalyst is thereby located at the output of the pre-combustion chamber 6 and enables in particular the dihydrogen H 2 rate of the hot combustion gases supplying the CVC type combustion chambers 7 to be increased to allow the ignition thereof.
  • a high dihydrogen rate is known to favour the tolerance of a combustion system to the dilution by residual gases. It can be therefore possible to improve the reliability of the entire system which is provided.
US15/578,316 2015-06-11 2016-06-09 Turbine engine cvc combustion chamber module comprising a pre-combustion chamber Abandoned US20180149365A1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1555324A FR3037384B1 (fr) 2015-06-11 2015-06-11 Module de chambre de combustion cvc de turbomachine comportant une prechambre de combustion
FR1555324 2015-06-11
PCT/FR2016/051383 WO2016198792A1 (fr) 2015-06-11 2016-06-09 Module de chambre de combustion cvc de turbomachine comportant une préchambre de combustion

Publications (1)

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US20180149365A1 true US20180149365A1 (en) 2018-05-31

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US15/578,316 Abandoned US20180149365A1 (en) 2015-06-11 2016-06-09 Turbine engine cvc combustion chamber module comprising a pre-combustion chamber

Country Status (10)

Country Link
US (1) US20180149365A1 (fr)
EP (1) EP3308080B1 (fr)
JP (1) JP2018521261A (fr)
KR (1) KR20180017032A (fr)
CN (1) CN107743568A (fr)
CA (1) CA2988186A1 (fr)
FR (1) FR3037384B1 (fr)
PL (1) PL3308080T3 (fr)
RU (1) RU2714387C2 (fr)
WO (1) WO2016198792A1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3091899B1 (fr) * 2019-01-22 2020-12-25 Safran Aircraft Engines Ensemble pour turbomachine

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US3877219A (en) * 1972-06-30 1975-04-15 Mtu Muenchen Gmbh Constant volume combustion gas turbine with intermittent flows
US20040154306A1 (en) * 2001-07-06 2004-08-12 Benians Hubert Michael Compound gas turbine engines and methods of operation thereof
US20050039463A1 (en) * 2003-05-22 2005-02-24 Williams International Co., L.L.C. Rotary injector
US20050120700A1 (en) * 2003-12-08 2005-06-09 General Electric Company Two-stage pulse detonation system
US20050183413A1 (en) * 2004-02-19 2005-08-25 Japan Aerospace Exploration Agency Pulse detonation engine and valve
US20080233525A1 (en) * 2006-10-24 2008-09-25 Caterpillar Inc. Turbine engine having folded annular jet combustor
US20110167789A1 (en) * 2009-09-10 2011-07-14 Dahm Werner J A Rayleigh-taylor assisted combustion and combustors adapted to exploit rayleigh-taylor instability for increasing combustion rates therein
US20120017563A1 (en) * 2009-01-27 2012-01-26 Michel Aguilar Jet engine, in particular a jet engine for an aircraft
US20120317956A1 (en) * 2011-06-20 2012-12-20 Streamline Automation, Llc Constant Volume Combustion Chamber
US20140000551A1 (en) * 2011-12-08 2014-01-02 J. Eberspacher Gmbh & Co. Kg Process for operating a heater that can be operated with hydrocarbon fuel
US20150159876A1 (en) * 2012-08-24 2015-06-11 Alstom Technology Ltd Sequential combustion with dilution gas mixer

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US5406799A (en) * 1992-06-12 1995-04-18 United Technologies Corporation Combustion chamber
US5314329A (en) * 1992-07-10 1994-05-24 Bepex Corporation Pulse combustor ignitor system
RU2087805C1 (ru) * 1993-11-02 1997-08-20 Научно-производственное предприятие Товарищество с ограниченной ответственностью "ЭСТ" Камера сгорания
RU2121113C1 (ru) * 1996-05-28 1998-10-27 Акционерное общество "Авиадвигатель" Камера сгорания газовой турбины
DE19950891C2 (de) * 1999-10-22 2002-08-14 Eisenmann Kg Maschbau Regenerative Nachverbrennungsvorrichtung
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US7448200B2 (en) * 2005-03-24 2008-11-11 United Technologies Corporation Pulse combustion device
RU2393363C1 (ru) * 2009-03-03 2010-06-27 Николай Петрович Генералов Газотурбинный двигатель
US8341932B2 (en) * 2009-03-19 2013-01-01 General Electric Company Rotary air valve firing patterns for resonance detuning
EP2857658A1 (fr) * 2013-10-01 2015-04-08 Alstom Technology Ltd Turbine à gaz avec agencement de combustion séquentielle

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2056198A (en) * 1934-08-18 1936-10-06 Robert E Lasley Power plant
US3877219A (en) * 1972-06-30 1975-04-15 Mtu Muenchen Gmbh Constant volume combustion gas turbine with intermittent flows
US20040154306A1 (en) * 2001-07-06 2004-08-12 Benians Hubert Michael Compound gas turbine engines and methods of operation thereof
US20050039463A1 (en) * 2003-05-22 2005-02-24 Williams International Co., L.L.C. Rotary injector
US20050120700A1 (en) * 2003-12-08 2005-06-09 General Electric Company Two-stage pulse detonation system
US20050183413A1 (en) * 2004-02-19 2005-08-25 Japan Aerospace Exploration Agency Pulse detonation engine and valve
US20080233525A1 (en) * 2006-10-24 2008-09-25 Caterpillar Inc. Turbine engine having folded annular jet combustor
US20120017563A1 (en) * 2009-01-27 2012-01-26 Michel Aguilar Jet engine, in particular a jet engine for an aircraft
US20110167789A1 (en) * 2009-09-10 2011-07-14 Dahm Werner J A Rayleigh-taylor assisted combustion and combustors adapted to exploit rayleigh-taylor instability for increasing combustion rates therein
US20120317956A1 (en) * 2011-06-20 2012-12-20 Streamline Automation, Llc Constant Volume Combustion Chamber
US20140000551A1 (en) * 2011-12-08 2014-01-02 J. Eberspacher Gmbh & Co. Kg Process for operating a heater that can be operated with hydrocarbon fuel
US20150159876A1 (en) * 2012-08-24 2015-06-11 Alstom Technology Ltd Sequential combustion with dilution gas mixer

Also Published As

Publication number Publication date
JP2018521261A (ja) 2018-08-02
FR3037384B1 (fr) 2017-06-23
WO2016198792A1 (fr) 2016-12-15
FR3037384A1 (fr) 2016-12-16
RU2018100160A3 (fr) 2019-09-17
PL3308080T3 (pl) 2020-04-30
RU2018100160A (ru) 2019-07-11
CA2988186A1 (fr) 2016-12-15
EP3308080A1 (fr) 2018-04-18
KR20180017032A (ko) 2018-02-20
CN107743568A (zh) 2018-02-27
EP3308080B1 (fr) 2019-11-27
RU2714387C2 (ru) 2020-02-14

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