EP0964206B1 - Chambre de combustion de turbine à gaz à géométrie variable - Google Patents

Chambre de combustion de turbine à gaz à géométrie variable Download PDF

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Publication number
EP0964206B1
EP0964206B1 EP99401204A EP99401204A EP0964206B1 EP 0964206 B1 EP0964206 B1 EP 0964206B1 EP 99401204 A EP99401204 A EP 99401204A EP 99401204 A EP99401204 A EP 99401204A EP 0964206 B1 EP0964206 B1 EP 0964206B1
Authority
EP
European Patent Office
Prior art keywords
injection
combustion chamber
comburant
fact
combustion
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
EP99401204A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0964206A1 (fr
Inventor
Guy Grienche
Gérard Schott
Jean-Hervé Le Gal
Gérard Martin
Patrice Laborde
Raphael Spagne
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.)
IFP Energies Nouvelles IFPEN
Safran Helicopter Engines SAS
Original Assignee
IFP Energies Nouvelles IFPEN
Turbomeca SA
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 IFP Energies Nouvelles IFPEN, Turbomeca SA filed Critical IFP Energies Nouvelles IFPEN
Publication of EP0964206A1 publication Critical patent/EP0964206A1/fr
Application granted granted Critical
Publication of EP0964206B1 publication Critical patent/EP0964206B1/fr
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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/34—Feeding into different combustion zones
    • F23R3/346—Feeding into different combustion zones for staged combustion
    • 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

Definitions

  • the present invention relates to the field of gas turbines and more particularly combustion chambers associated with such turbines.
  • One of the problems at the root of the present invention relates to the pollution caused by the operation of these turbines. More specifically, emissions of nitrogen oxides (NOx) and carbon monoxide Carbon (CO) must be reduced as these are the most harmful to the environment.
  • NOx nitrogen oxides
  • CO carbon monoxide Carbon
  • Nitrogen oxides are mainly thermal nitrogen oxides which are formed at high temperature, that is to say above 1700 K in combustion chambers of gas turbines where fumes have times to stay generally between 2 and 10 milliseconds.
  • Carbon monoxide (CO) is, for its part, formed at lower temperature ( ⁇ 1600 K), by incomplete combustion of the fuel.
  • the optimal temperature range to have emissions reduced in both NOx and CO is between about 1650 K and 1750 K.
  • Figure 1 illustrates, by curves (CO and NOx) the respective emissions of carbon monoxide and oxides of nitrogen depending on the temperature T (in K) under the operating conditions of a chamber of combustion of a gas turbine.
  • NO and CO emissions are thus directly related to richness of the air-fuel mixture in the combustion chamber; that is to say the ratio of air flow to fuel flow. Knowing that the richness of the mixture must be imposed, if one seeks to operate in a certain temperature range, such as that mentioned above, the adiabatic flame temperature of the mixture will vary approximately proportionally to wealth.
  • the fuel flow is the only parameter to control the operating speed of the turbine. It follows that for a given fuel flow, the air flow is perfectly fixed to a value depending only on the characteristics of the machine and in particular passage sections in the hearth. By After that, wealth is totally determined.
  • FIG. a combustion chamber having a pilot stage followed by two others stages each having an air inlet and a fuel inlet such as natural gas for example. It is then necessary to realize the combustion on each floor successively, and according to the total power demanded. The combustion-pilot is performed, regardless of the diet.
  • This solution theoretically allows to obtain acceptable wealth in the illuminated stages, for each engine speed, if a number is available sufficient floors.
  • the major disadvantage is that it requires a circuit complex fuel supply, which gives rise to problems of reliability, regulation and especially of cost.
  • Another concept for obtaining combustion chambers operating over a certain temperature range consists in equipping it with a set of flaps, valves or other closure means allow control the air flow in the fireplace, as already described in patent application FR-A-2 270 448.
  • a set of flaps, valves or other closure means allow control the air flow in the fireplace, as already described in patent application FR-A-2 270 448.
  • the order and the actuation of such elements is complex, difficult to implement.
  • the set is also expensive.
  • the present invention therefore aims to propose a reliable, simple solution to the problem of regulating wealth in a room of combustion of a gas turbine.
  • This control is to be able to achieve combustion in an optimal temperature range, particularly with regard to carbon monoxide, and nitrogen oxides.
  • the present invention thus allows automatic regulation of the combustion air flow.
  • Mechanical servoing is advantageously achieved thanks to a very limited number of parts mechanical.
  • the subject of the invention is a gas turbine combustion chamber comprising at least one so-called pilot injection zone in which at least one first pilot fuel injection means and a first first oxidant injection means associated; a combustion zone in which at least one second of main fuel injection and second injection means of associated oxidant, the assembly being maintained under pressure P2 to inside an enclosure.
  • said combustion chamber further comprises a mechanical means for regulating the second flow of oxidizer, which reacts to the pressure difference between the inside (P2) and the pressure atmospheric pressure (Po) outside the enclosure, said pressure difference being directly related to the engine regime.
  • said regulating means comprises at least one shutter element which more or less closes the second air inlets in the combustion chamber, several connecting rods between the elements shutter and a support member, a compression member, a sealing bellows placed around the compression element defining with the support member the volume at atmospheric pressure (Po) vis-à-vis the pressure vessel (P2).
  • first fuel injection means and the first oxidant injection means are disposed substantially at near the longitudinal axis (XX ') of the combustion chamber.
  • the second of main fuel injection and the second injection means of oxidant are arranged on a circumference downstream of the pilot combustion relative to the direction of flame propagation.
  • the combustion chamber according to the invention comprises a third means of injecting oxidant which opens, in the chamber of combustion, downstream of the second oxidant injection means relative to the direction of propagation of the flame.
  • the means for regulating the second oxidant flow rate allows to regulate the flow rate of the third air injection means (function of bypass).
  • the compression member may comprise a stack of washers or springs.
  • the chamber comprises three areas of grouping of the second main injection means of fuel (7) and main oxidant injection (8), each zone being angularly spaced 120 °.
  • the hearth 1 is delimited by an internal ferrule 2 which presents two different diameters: the smallest diameter contains the pilot-combustion zone 11 while the larger-diameter zone 12 is the one where the main combustion develops.
  • the pilot combustion zone 11 provides for idling combustion and the combustion can be maintained during other operation.
  • injectors 3 of fuel such as for example natural gas and injectors or air inlets 4.
  • a bottom 5 is provided to delimit zone 11.
  • the arrivals of fuel 3 and air 4 are located near the bottom 5, circumferentially, and not far from the longitudinal axis XX 'of the chamber.
  • the pilot combustion zone 11 is a zone of stability of the flame, where a flame exists whatever the operating conditions.
  • Air-turning fins 6 can be provided at level of air inlets 4.
  • the fuel injectors 3 can be implanted in these fins without departing from the scope of the invention.
  • Zone 12 therefore has a larger diameter than that of zone 11: this is where the main combustion is operated.
  • a second fuel injection means 7 is disposed at the boundary between zones 11 and 12.
  • a second injection means 8 is located near the second fuel injector 7.
  • fins 9 may also be arranged at the injectors 8.
  • means 7, 8 and 9 are located on a circumference of the shell 2, and several groups may be provided. Here three groups are planned, each one angularly spaced 120 °.
  • the general air supply is made by an annular space 13 delimited by the ferrule 2 and an outer envelope 14.
  • a pressure P2 reigns in this space; this pressure is slightly higher than the pressure P1, the difference being due to the pressure losses created by the different air inlet openings.
  • the present invention provides a means for of flow regulation, which reacts to the pressure difference between the space ring (P2) and the outside of the enclosure 14 or reigns a pressure Po ( ⁇ Atmospheric pressure).
  • the regulating means comprises a ferrule 15 capable of sliding along the axis XX 'in front of the openings 8 (preferentially equipped with fins 9) and thus allowing a variation of the section of passage of the air.
  • the ferrule 15 is fixed, by any means known per se, at the end lower part of several rods 16. At their other end, the rods 16 carry a support plate 17 which is itself linked to a compression element 18. A stack of conical washers or springs may be provided for this purpose.
  • a bellows 19 or other sealing means is also provided around the compression element 18.
  • the bellows 19 is a separation between the internal volume of the combustion chamber, where the pressures P2 and P1, and the external volume where the pressure Po prevails.
  • the ferrule 15 may be provided with additional openings which place the space 13 in communication with an annular space 21 inside the ferrule 2.
  • an additional ferrule 20 coaxial with the ferrule 2 is provided on a part of the height of the ferrule 2.
  • the ferrule 20 may have a height that corresponds to the zone 12 of combustion. On this height, the air coming from openings 10 and which passes through in the annular space 21, will allow to reject air downstream of the combustion zone 12 while cooling the walls of said zone of 12. It is thus possible to maintain an acceptable wealth within the main focus regardless of the diet.
  • the main effect of bypass 21 is limit the decline of wealth in the household 1, especially at part.
  • the openings 10 are designed so that at full charging, no air passes through them (case of Figure 4), while at charge partial or low, air passes into space 21 in order to be rejected downstream of the combustion zone 12 while cooling the wall of the ferrule 2.
  • the openings 10 are rather wide open so that air can pass through the space 21 and cool the wall 20 without participate in the combustion in zone 12. It can thus maintain a acceptable wealth in it and avoid high CO emissions.
  • the combustion chamber according to the invention does not requires no specific mechanical device for regulating arrivals air.
  • the regulation is done here of itself, by the relative pressure in the combustion chamber and therefore depending on the engine speed.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP99401204A 1998-06-11 1999-05-18 Chambre de combustion de turbine à gaz à géométrie variable Expired - Lifetime EP0964206B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9807409A FR2779807B1 (fr) 1998-06-11 1998-06-11 Chambre de combustion de turbine a gaz a geometrie variable
FR9807409 1998-06-11

Publications (2)

Publication Number Publication Date
EP0964206A1 EP0964206A1 (fr) 1999-12-15
EP0964206B1 true EP0964206B1 (fr) 2004-12-08

Family

ID=9527308

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99401204A Expired - Lifetime EP0964206B1 (fr) 1998-06-11 1999-05-18 Chambre de combustion de turbine à gaz à géométrie variable

Country Status (5)

Country Link
US (1) US6263663B1 (enExample)
EP (1) EP0964206B1 (enExample)
JP (1) JP4435331B2 (enExample)
DE (1) DE69922437T2 (enExample)
FR (1) FR2779807B1 (enExample)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8915086B2 (en) 2006-08-07 2014-12-23 General Electric Company System for controlling combustion dynamics and method for operating the same

Families Citing this family (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1819964A2 (en) * 2004-06-11 2007-08-22 Vast Power Systems, Inc. Low emissions combustion apparatus and method
JP4670035B2 (ja) * 2004-06-25 2011-04-13 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
JP2007113888A (ja) * 2005-10-24 2007-05-10 Kawasaki Heavy Ind Ltd ガスタービンエンジンの燃焼器構造
GB0815761D0 (en) * 2008-09-01 2008-10-08 Rolls Royce Plc Swirler for a fuel injector
US8099941B2 (en) * 2008-12-31 2012-01-24 General Electric Company Methods and systems for controlling a combustor in turbine engines
US8276386B2 (en) * 2010-09-24 2012-10-02 General Electric Company Apparatus and method for a combustor
US9316155B2 (en) * 2013-03-18 2016-04-19 General Electric Company System for providing fuel to a combustor
US9803555B2 (en) * 2014-04-23 2017-10-31 General Electric Company Fuel delivery system with moveably attached fuel tube
FR3065059B1 (fr) 2017-04-11 2020-11-06 Office National Detudes Rech Aerospatiales Foyer de turbine a gaz a geometrie variable auto-adaptative
WO2022079523A1 (en) * 2020-10-14 2022-04-21 King Abdullah University Of Science And Technology Adjustable fuel injector for flame dynamics control
RU2757705C1 (ru) * 2021-01-13 2021-10-20 Роман Лазирович Илиев Горелка с двухслойным вихревым противоточным течением
GB202112642D0 (en) 2021-09-06 2021-10-20 Rolls Royce Plc Controlling soot
GB202112641D0 (en) * 2021-09-06 2021-10-20 Rolls Royce Plc Controlling soot
CN116592391A (zh) * 2022-02-07 2023-08-15 通用电气公司 具有可变初级区燃烧室的燃烧器
CN115031260B (zh) * 2022-05-30 2023-08-22 中国人民解放军空军工程大学 一种旋转爆震燃烧室出口喉道位置固定的可调喷管
JP2025535131A (ja) * 2022-10-11 2025-10-22 イノロム アイヴイ ホールディングス イノベーション アンド ベンチャーズ リミテッド ２層渦対向流を有する２段バーナ

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3691761A (en) * 1967-11-10 1972-09-19 Squire Ronald Jackson Apparatus for regulation of airflow to flame tubes for gas turbine engines
DE2020416A1 (de) * 1970-04-27 1971-11-11 Motoren Turbinen Union Brennkammer fuer Gasturbinentriebwerke
US3869246A (en) * 1973-12-26 1975-03-04 Gen Motors Corp Variable configuration combustion apparatus
FR2270448A1 (en) * 1974-05-10 1975-12-05 Bennes Marrel Gas turbine combustion chamber - has spring loaded bellows controlling annular air flow control membrane
US4296599A (en) * 1979-03-30 1981-10-27 General Electric Company Turbine cooling air modulation apparatus
JP2644745B2 (ja) * 1987-03-06 1997-08-25 株式会社日立製作所 ガスタービン用燃焼器
FR2661714B1 (fr) * 1990-05-03 1994-06-17 Snecma Dispositif d'alimentation en comburant d'une turbine a gaz.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8915086B2 (en) 2006-08-07 2014-12-23 General Electric Company System for controlling combustion dynamics and method for operating the same

Also Published As

Publication number Publication date
FR2779807B1 (fr) 2000-07-13
EP0964206A1 (fr) 1999-12-15
DE69922437T2 (de) 2005-12-08
FR2779807A1 (fr) 1999-12-17
JP4435331B2 (ja) 2010-03-17
US6263663B1 (en) 2001-07-24
DE69922437D1 (de) 2005-01-13
JP2000009319A (ja) 2000-01-14

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