EP1640661B1 - Système aérodynamique à effervescence d'injection air/carburant dans une chambre de combustion de turbomachine - Google Patents

Système aérodynamique à effervescence d'injection air/carburant dans une chambre de combustion de turbomachine Download PDF

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Publication number
EP1640661B1
EP1640661B1 EP05291869A EP05291869A EP1640661B1 EP 1640661 B1 EP1640661 B1 EP 1640661B1 EP 05291869 A EP05291869 A EP 05291869A EP 05291869 A EP05291869 A EP 05291869A EP 1640661 B1 EP1640661 B1 EP 1640661B1
Authority
EP
European Patent Office
Prior art keywords
fuel
tubular structure
air
gas
feed channel
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.)
Expired - Lifetime
Application number
EP05291869A
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German (de)
English (en)
French (fr)
Other versions
EP1640661A3 (fr
EP1640661A2 (fr
Inventor
Igor Mantchenkov
Thomas Noel
Alexander Novikov
Vladimir Orlov
Valery Pikalov
Gilles Rollin
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
SNECMA SAS
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Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1640661A2 publication Critical patent/EP1640661A2/fr
Publication of EP1640661A3 publication Critical patent/EP1640661A3/fr
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Publication of EP1640661B1 publication Critical patent/EP1640661B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/16—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour in which an emulsion of water and fuel is sprayed

Definitions

  • the present invention relates to the general field of injection systems of an air / fuel mixture in a turbomachine combustion chamber. It is more particularly an aerodynamic type injection system provided with means for creating an effervescence of the fuel before it is mixed with the air.
  • the classic process for developing and optimizing a combustion chamber of a turbomachine has the main objective of reconciling the implementation of the operational performances of the chamber (combustion efficiency, stability range, ignition range and relight, life of the combustion chamber, etc.) depending on the mission envisaged for the aircraft on which the turbomachine is mounted while minimizing pollutant emissions (nitrogen oxides, carbon monoxide, unburned hydrocarbons, etc. .). To do this, it is particularly possible to play on the nature and performance of the fuel / air mixture injection system in the combustion chamber, the distribution of the dilution air in the chamber and the dynamics of the air / fuel mixture. fuel in the room.
  • the combustion chamber of a turbomachine typically consists of a system for injecting an air / fuel mixture into a flame tube, a cooling system and a dilution system.
  • the combustion is organized mainly within a first part of the flame tube (called the primary zone) in which it is stabilized by means of zones of recirculation of the air / fuel mixture induced by the flow of air coming from the injection system.
  • the primary zone a first part of the flame tube
  • the dilution zone the chemical activity used is lower and the flow is diluted by means of dilution holes.
  • the atomization time thus represents the time required for the disintegration of the fuel layer by air and the formation of an air / fuel spray. It mainly depends on the performance and technology of the injection system used and aerodynamics in the vicinity of the fuel table.
  • the evaporation time also depends on the injection system used. It is directly a function of the size of the droplets resulting from the disintegration of the fuel layer; the smaller the droplets, the lower the evaporation time.
  • the mixing time corresponds to the time required for the fuel vapors from the evaporation of the droplets to mix with the air. It mainly depends on the level of turbulence inside the combustion chamber and therefore the dynamics of the flow in the primary zone.
  • chemical time it represents the time required for chemical reactions to develop. It depends on the pressures and temperatures at the entry of the hearth and the nature of the fuel used.
  • the injection system used therefore plays a key role in the process of developing a combustion chamber, in particular in the optimization of the characteristic times of atomization and evaporation of the fuel.
  • Aerodynamic injection systems known from the prior art for example that disclosed in EP-1 331 441-A , have many disadvantages.
  • the atomization of the fuel deteriorates sharply, which decreases the stability of the combustion at the risk of seeing the fireplace go out and increases the pollutant emissions type oxides of nitrogen.
  • the main purpose of the present invention is therefore to overcome such drawbacks by proposing an aerodynamic injection system which makes it possible to reduce the characteristic times of atomization and evaporation of the fuel at all operating speeds of the turbomachine.
  • an aerodynamic injection system of an air / fuel mixture in a turbomachine combustion chamber comprising a tubular structure of axis XX 'which opens at a downstream end for the air / fuel mixture.
  • fuel at least one air supply channel which is connected to a compressor stage of the turbomachine and which opens into the tubular structure so as to introduce air at a pressure P A , and an annular passage of fuel which is formed in the tubular structure about its axis XX ', is connected to at least one fuel supply channel in which fuel flows at a pressure P C , and opens at a downstream end in the tubular structure forming in this enlargement, characterized in that it further comprises means for injecting into the at least one fuel supply channel a gas at a pressure P G which is greater than P A and greater than or equal to P C to to create an effervescence of the fuel during its introduction into the tubular structure.
  • the injection system comprises at least one gas injection channel which opens into the fuel supply channel and which is connected to a gas supply line.
  • the gas injection channel opens substantially perpendicularly into the fuel supply channel.
  • the injection system may comprise an annular gas distribution cavity which is formed in the tubular structure around the fuel passage, is connected to the gas supply line and opens into the gas injection channel.
  • the injection system may also include an annular fuel dispensing cavity that is formed in the tubular structure, is connected to a fuel supply line and opens into the fuel supply channel.
  • the air supply channel opens into the tubular structure at an upstream end thereof.
  • the injection system may comprise an external air swirle which is arranged around the tubular structure, is offset radially with respect to the fuel passage and is intended to inject air at the outlet of the tubular structure in a substantially axial direction.
  • the external air swirler may be connected to a compressor stage of the turbomachine and a diverging bowl may be mounted downstream of the tubular structure.
  • the air supply channel is disposed around the tubular structure and opens axially into the fuel passage at an upstream end thereof.
  • the annular fuel passage may have a sectional decrease in the flow direction of the fuel to accelerate the flow of fuel into the tubular structure.
  • the gas used is air which is preferably taken from a compressor stage of the turbomachine before being compressed.
  • a device for controlling the flow of gas injected into the fuel supply channel is provided.
  • a combustion chamber comprising such an injection system of an air / fuel mixture and a turbomachine comprising such a combustion chamber.
  • the aerodynamic injection system 2, 2 ' is in the general form of a tubular structure 4 of axis XX' which is open at its downstream end 4b for the air / fuel mixture.
  • the injection system 2, 2 ' comprises at least one air supply duct 6, 6' which is connected to a compressor stage (not shown) of the turbomachine and which opens into the tubular structure 4.
  • the air is thus introduced into the tubular structure 4 by this or these channels 6, 6 'at a pressure P A , for example of the order of 0.5 to 50 bar.
  • the injection system 2, 2 ' also comprises an annular fuel passage 8 which is formed in the tubular structure, about its axis XX'.
  • This fuel passage 8 opens at its downstream end 8b into the tubular structure 4 forming in it a sudden enlargement.
  • the fuel passage 8 which is centered on the axis XX 'of the tubular structure 4, is connected to at least one fuel supply channel 10 in which fuel is circulated at a pressure P C.
  • This passage 8 makes it possible to introduce fuel into the tubular structure 4 in the axial direction XX '.
  • the pressure P C of the fuel circulating in the fuel supply channel 10 is of the order of 4 to 80 bar.
  • the annular fuel passage 8 may, for example, be connected to twenty fuel supply channels 10 which are regularly distributed over the entire circumference of the tubular structure 4 in order to obtain a homogeneous distribution of fuel in passage 8.
  • the fuel supply channels 10 are inclined tangentially with respect to the annular fuel passage 8, for example at an angle of about 45 ° ( Figure 2). In this way, the fuel is rotated during its introduction in the passage 8.
  • the injection system 2, 2 'further comprises at least one gas injection channel 12 which opens into the fuel supply channel (s) 10 and which is connected to a fuel line. gas supply 14.
  • a gas injection channel 12 can be provided for each fuel supply channel 10.
  • the injection system 2 thus comprises twenty channels. injection of gas 12 distributed on the circumference of the tubular structure 4. Alternatively, it could also be expected fewer gas injection channels that fuel supply channels.
  • the gas is introduced into the fuel supply channel (s) 10 at a pressure P G which is greater than the pressure P A of the air introduced into the tubular structure 4 by the channel (s). 6, 6 'and which is greater than or approximately equal to the pressure P C of the fuel flowing in the fuel supply channel (s) 10.
  • the introduction of the gas into the fuel supply channel (s) 10 at a pressure P G greater than the pressure P A and greater than or equal to the pressure P C makes it possible to create a liquid / gas mixture at the pressure P C before its introduction into the tubular structure 4.
  • the effervescence of the fuel is characterized by the atomization of the fuel produced by the sudden expansion of the gas during introduction into the tubular structure 4.
  • the effervescence of the fuel occurs when the following conditions are met: the gas must be at least at a pressure P G substantially equal to that (P C ) of the fuel (or slightly overpressure relative thereto) and the mixing of the gas with the fuel must occur in a substantially confined space (in this case, mixing takes place in the confluence zone of the gas injection channels 12 and fuel supply 10).
  • the effervescence of the fuel is characterized by the presence of gas bubbles in the sheet of fuel flowing in the fuel passage 8.
  • the expansion of the gas bubbles during the introduction of the mixture into the tubular structure 4 allows thus to facilitate its subsequent atomization.
  • the characteristic times of atomization and evaporation of the fuel are therefore reduced.
  • the gas is an inert gas which has no direct influence on the combustion of the air / fuel mixture.
  • the gas is air that is taken from a compressor stage of the turbomachine and is compressed again to reach a pressure P G greater than the pressure P A of the air supplying the channel or channels. air supply 6, 6 '.
  • the gas injection channel (s) 12 open substantially perpendicularly into the fuel supply channel (s) 10. This particular arrangement makes it possible to promote the appearance of the effervescence of the fuel. fuel.
  • An annular gas cavity 16 may be formed in the tubular structure 4 around the fuel passage 8. Such a gas cavity 16 is centered on the axis XX 'of the tubular structure 4 so as to be coaxial with the fuel passage 8 It is connected to the gas supply pipe 14 and opens into the gas injection channel (s) 12. This gas cavity 16 thus acts as a gas distribution cavity.
  • annular fuel cavity 18 may be formed in the tubular structure 4. As illustrated in the figures, this fuel cavity 18 is also centered on the axis XX 'of the tubular structure 4 so as to be coaxial with the passage 8 and the gas cavity 16. It is connected to a fuel supply line 20 and opens into the fuel supply channel (s) 10. This fuel cavity 18 also acts as a fuel distribution cavity.
  • the injection system 2, 2 'further comprises a device 22 for controlling the flow of gas injected into the fuel supply channel 10.
  • a device 22 thus makes it possible to control the gas flow that must be injected to achieve the effervescence of the fuel.
  • the control of the gas flow can be a function of the flow rate and the pressure P C of the fuel.
  • the injection system 2 may comprise two rows of air supply ducts 6 spaced axially from one another and regularly distributed over the entire circumference of the tubular structure 4. These channels 6 may to open at the upstream end 4a of the tubular structure 4.
  • the injection system 2 preferably comprises an external air swirler 24 which is arranged around the tubular structure 4 and is offset radially with respect to the fuel passage 8.
  • This external air swirler 24 is intended to inject air at the outlet of the tubular structure 4 in a substantially axial direction and also with a rotation effect.
  • the effervescence fuel that is introduced into the tubular structure 4 through the fuel passage 8 is atomized by the shearing effect of the air from the air supply ducts 6 and the external air swirler 24. .
  • the air supplying the external air swirler 24 is preferably taken from a compressor stage of the turbomachine, for example at the same stage as the air introduced into the tubular structure 4 by the air supply channel (s).
  • a divergent bowl 26 may be mounted downstream of the tubular structure 4.
  • the injection system 2 ' comprises a single air supply channel 6'.
  • This one is annular; it is arranged around the tubular structure 4 and opens axially into the fuel passage 8 at an upstream end 8a thereof.
  • the air introduced through this channel 6 'at a pressure P A thus flows into the fuel passage 8 before being introduced into the tubular structure 4 at the widening thereof.
  • the fuel passage 8 preferably has a reduction of section 8c in the direction of flow of the fuel to accelerate the flow of fuel in the tubular structure 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Nozzles (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP05291869A 2004-09-23 2005-09-09 Système aérodynamique à effervescence d'injection air/carburant dans une chambre de combustion de turbomachine Expired - Lifetime EP1640661B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0410052A FR2875585B1 (fr) 2004-09-23 2004-09-23 Systeme aerodynamique a effervescence d'injection air/carburant dans une chambre de combustion de turbomachine

Publications (3)

Publication Number Publication Date
EP1640661A2 EP1640661A2 (fr) 2006-03-29
EP1640661A3 EP1640661A3 (fr) 2006-04-19
EP1640661B1 true EP1640661B1 (fr) 2007-07-25

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP05291869A Expired - Lifetime EP1640661B1 (fr) 2004-09-23 2005-09-09 Système aérodynamique à effervescence d'injection air/carburant dans une chambre de combustion de turbomachine

Country Status (7)

Country Link
US (1) US7506496B2 (enExample)
EP (1) EP1640661B1 (enExample)
JP (1) JP4695952B2 (enExample)
CN (1) CN100545433C (enExample)
DE (1) DE602005001742T2 (enExample)
FR (1) FR2875585B1 (enExample)
RU (1) RU2309329C2 (enExample)

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US8266911B2 (en) * 2005-11-14 2012-09-18 General Electric Company Premixing device for low emission combustion process
KR20100022491A (ko) * 2007-05-25 2010-03-02 코닝 인코포레이티드 유리 시트를 취급하기 위한 장치
US7874157B2 (en) * 2008-06-05 2011-01-25 General Electric Company Coanda pilot nozzle for low emission combustors
US8240150B2 (en) * 2008-08-08 2012-08-14 General Electric Company Lean direct injection diffusion tip and related method
US8359870B2 (en) * 2009-05-12 2013-01-29 General Electric Company Automatic fuel nozzle flame-holding quench
US9777637B2 (en) * 2012-03-08 2017-10-03 General Electric Company Gas turbine fuel flow measurement using inert gas
RU2511992C2 (ru) * 2012-06-27 2014-04-10 Николай Борисович Болотин Форсуночный блок камеры сгорания гтд
US11326775B2 (en) 2013-02-28 2022-05-10 Raytheon Technologies Corporation Variable swirl fuel nozzle
FR3003013B1 (fr) * 2013-03-05 2016-07-29 Snecma Dispositif de dosage compact pour injecteur a deux circuits de carburant, de preference pour turbomachine d'aeronef
EP3401529A1 (en) 2013-03-14 2018-11-14 United Technologies Corporation Hollow-wall heat shield for fuel injector component
EP2789915A1 (en) * 2013-04-10 2014-10-15 Alstom Technology Ltd Method for operating a combustion chamber and combustion chamber
FR3031798B1 (fr) 2015-01-20 2018-08-10 Safran Aircraft Engines Systeme d'injection de carburant pour turbomachine d'aeronef, comprenant un canal de traversee d'air a section variable
US9927126B2 (en) 2015-06-10 2018-03-27 General Electric Company Prefilming air blast (PAB) pilot for low emissions combustors
US10184665B2 (en) 2015-06-10 2019-01-22 General Electric Company Prefilming air blast (PAB) pilot having annular splitter surrounding a pilot fuel injector
FR3043173B1 (fr) * 2015-10-29 2017-12-22 Snecma Systeme d'injection aerodynamique pour turbomachine d'aeronef, a melange air/carburant ameliore
ES2645299B1 (es) * 2016-06-03 2018-09-12 Bsh Electrodomésticos España, S.A. Quemador de gas y aparato de cocción doméstico
US10520195B2 (en) * 2017-06-09 2019-12-31 General Electric Company Effervescent atomizing structure and method of operation for rotating detonation propulsion system
FR3105985B1 (fr) * 2020-01-03 2023-11-24 Safran Aircraft Engines Circuit multipoint d’injecteur amélioré
FR3139378A1 (fr) * 2022-09-05 2024-03-08 Safran Dispositif et procede d’injection de melange hydrogene-air pour bruleur de turbomachine
CN116878026B (zh) * 2023-07-25 2025-07-22 新奥能源动力科技（上海）有限公司 一种燃烧器组件及燃烧装置

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Also Published As

Publication number Publication date
US7506496B2 (en) 2009-03-24
RU2005129655A (ru) 2007-03-27
EP1640661A3 (fr) 2006-04-19
CN1769654A (zh) 2006-05-10
FR2875585A1 (fr) 2006-03-24
JP2006090327A (ja) 2006-04-06
US20060059914A1 (en) 2006-03-23
DE602005001742T2 (de) 2008-04-30
CN100545433C (zh) 2009-09-30
DE602005001742D1 (de) 2007-09-06
RU2309329C2 (ru) 2007-10-27
EP1640661A2 (fr) 2006-03-29
JP4695952B2 (ja) 2011-06-08
FR2875585B1 (fr) 2006-12-08

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