EP0109523B1 - Gasturbinenbrennkammer - Google Patents

Gasturbinenbrennkammer Download PDF

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Publication number
EP0109523B1
EP0109523B1 EP83110020A EP83110020A EP0109523B1 EP 0109523 B1 EP0109523 B1 EP 0109523B1 EP 83110020 A EP83110020 A EP 83110020A EP 83110020 A EP83110020 A EP 83110020A EP 0109523 B1 EP0109523 B1 EP 0109523B1
Authority
EP
European Patent Office
Prior art keywords
chamber
gas turbine
combustion chamber
primary combustion
combustion chambers
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
Application number
EP83110020A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP0109523A1 (de
Inventor
Helmut Maghon
Wolfram Krockow
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.)
Kraftwerk Union AG
Original Assignee
Kraftwerk Union AG
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 Kraftwerk Union AG filed Critical Kraftwerk Union AG
Publication of EP0109523A1 publication Critical patent/EP0109523A1/de
Application granted granted Critical
Publication of EP0109523B1 publication Critical patent/EP0109523B1/de
Expired legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • 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
    • 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
    • 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

Definitions

  • the invention relates to a gas turbine combustion chamber according to the preamble of claim 1.
  • Such a gas turbine combustion chamber is known from DE-PS 2417 147.
  • the primary combustion chambers in this known gas turbine combustion chamber are dimensioned in such a way that the combustion in them does not end.
  • the flames thus strike from the primary combustion chambers into the common chamber designed as a secondary combustion chamber, in which a common secondary flame is formed when the primary flames are mixed.
  • the arrangement of the individual primary combustion chambers on a dome-shaped closure of the secondary combustion chamber is intended to lead to the most compact possible secondary flame through intensive mixing of the primary flames, which guarantees reliable ignition even when separate primary combustion chambers are switched on, without separate ignition devices. So that a complete burnout can take place in the secondary combustion chamber, holes are provided in the jacket through which additional combustion air reaches the common secondary flame.
  • the known gas turbine combustion chamber has the advantage that the division of the combustion process into many small primary combustion chambers shortens the residence time of the combustion air in the high-temperature zone of the flame, which leads to a reduction in the formation of NO x .
  • By switching individual primary combustion chambers on and off, favorable mixture ratios of fuel and combustion air can be maintained even when the load changes.
  • the invention has for its object to provide a gas turbine combustion chamber with a plurality of primary combustion chambers, in which the NO x formation can be reduced even further.
  • the invention is based on the finding that, in the case of afterburning in the large volume of a secondary combustion chamber, the additional dwell time also results in an additional NO x formation and, on the other hand, in the case of a large number of primary combustion chambers with a narrow view in terms of low NO x formation
  • Working area requires a particularly intensive mixing of the hot gas jets emerging from the respective connected primary combustion chambers with the cold air jets emerging from the respective switched off primary combustion chambers.
  • the common chamber, into which the primary combustion chambers open is designed as a pure mixing chamber, for which the shape of a sphere is realized as far as possible.
  • the complete combustion therefore already takes place in the primary combustion chambers which are respectively connected, so that post-combustion with additional NO x formation is prevented in the mixing chamber.
  • the spherical shape of the mixing chamber ensures optimal mixing in the case of radially oriented primary combustion chambers, the primary combustion chambers arranged on the spherical zone facing the outlet opening being particularly important due to their orientation inclined backwards with respect to the main hot gas flow.
  • Another advantage of the spherical shape is that the surface of a sphere offers space for a very large number of primary combustion chambers. It is expedient if all the primary combustion chambers are arranged on latitudes of the sphere. The primary combustion chambers of adjacent latitudes can then be arranged offset to one another, which ensures particularly space-saving accommodation.
  • connection to the gas turbine can be carried out in a structurally particularly simple manner as a penetration of the ball and cylinder.
  • the burners of the primary combustion chambers are immersed in the nozzle of the outer combustion chamber shell.
  • the burner can then be installed through these nozzles. If the inside diameter of the nozzle is larger than the outside diameter of the primary combustion chamber, then the entire primary combustion chamber can also be installed through the nozzle.
  • a central manhole is provided in the spherical combustion chamber jacket, to which a closable opening of the mixing chamber is assigned.
  • the mixing chamber is then accessible through the manhole and the associated opening, which in particular makes it easier to inspect the refractory lining of the primary combustion chambers and the mixing chamber.
  • the primary combustion chambers are equipped with premix burners.
  • premix burners enable particularly low-pollutant operation.
  • the small working range of the premixing burners compared to diffusion burners can be maintained without any problems by the special requirements of the gas turbine combustion chamber according to the invention.
  • openings for the access of quenching air are provided in the area of the primary combustion chambers located behind the combustion zone and before the junction into the mixing chamber. This measure is based on the knowledge that even after complete combustion in the primary combustion chambers in the mixing chamber, a certain after-reaction associated with NO x formation can occur. By supplying the quenching air, however, such after-reactions are frozen before the reactants enter the mixing chamber. This effect can be intensified in that the entire mixed air can be introduced into the mixing chamber exclusively via the burners with the fuel supply switched off and in the form of quenching air via the openings of the primary combustion chambers. With the exception of the mixed air flowing through the switched off primary combustion chambers during part-load operation, all of the mixed air is used as quenching air.
  • combustion air is exclusive.
  • the primary combustion chambers apart from the openings for the access of quenching air, no further openings are then provided for the supply of combustion air or mixed air.
  • the gas turbine combustion chamber has a mixing chamber 1, which has the shape of a ball indicated by the dash-dotted line K and at the outlet opening 10 of which a cylindrical transition section 11 connects to the gas turbine.
  • the outlet opening 10 of the mixing chamber 1 is thus formed by penetrating the ball K and the cylinder of the transition section 11, the diameter of the transition section 11 being smaller than the diameter of the ball K and the longitudinal axis of the transition section 11 passing through the center of the ball K.
  • the jacket of the mixing chamber 1 is composed of a hemisphere HK to be regarded as the end and a spherical zone KZ lying between the hemisphere HK and the outlet opening 10.
  • the primary combustion chambers 2 of adjacent latitudes are each offset from one another.
  • Each of the primary combustion chambers 2 is equipped with a premix burner 3, each of these premix burners 3 being immersed in an associated connection piece 40 of the outer combustion chamber jacket 4.
  • the fuel feeds 30 of the associated premix burners 3 are passed through the end cover 400 of the individual connecting pieces 40.
  • the connecting pieces 40 are dimensioned such that the primary combustion chambers 2 and the premix burner 3 can be fitted through them.
  • the outer combustion chamber jacket 4 has the shape of a ball enclosing the mixing housing 1 at a distance, to which a frustoconical transition section 41 and a short cylindrical section 42 with a connecting flange 43 adjoin the gas turbine connection.
  • a central manhole 44 is provided, to which a closable opening of the mixing chamber 1 is assigned.
  • the lid 12 of this closable opening can be seen in the drawing as a flattened area of the ball K.
  • the compressor air indicated by arrows V is supplied via the annular space formed between the cylindrical transition section 11 of the mixing chamber 1 and the cylindrical section 42 of the combustion chamber jacket 2.
  • the compressor air V then reaches the intermediate space between the mixing chamber 1 and the spherical region of the combustion chamber jacket 4, where it is divided into burner air indicated by arrows B and quenching air indicated by arrows A.
  • the burner air B passes as combustion air into the premix burners 3 and the primary combustion chambers 2 and in the premix burners 3 with the fuel supply 30 switched off through the premix burners 3 and the primary combustion chambers 2 as Mixed air into the mixing chamber 1.
  • the quenching air A passes through openings 20 arranged in the end region of the primary combustion chambers 2 into the primary combustion chambers 2 and immediately thereafter into the mixing chamber 1.
  • the hot gas jets emerging from the respectively connected primary combustion chambers 2 are mixed intensively with the cold air jets emerging from the switched off primary combustion chambers.
  • the hot gas flow cooled to the turbine inlet temperature then leaves the mixing chamber 1 through its outlet opening 10 and flows - as indicated by the arrows H - through the transition section 11 to the inner casing of the gas turbine.
  • the hot gas jets which already carry the mixed air supplied as quenching air A are mixed with one another in the mixing chamber 1.
  • the cold air jets supplied via the switched-off primary combustion chambers 2 are then also included in this mixing.
  • the mixing is particularly intense due to the spherical shape of the mixing chamber 1 and the radial alignment of the hot gas jets and the cold air jets present during part-load operation.
  • this intensive mixing is optimized by the primary combustion chambers 2 arranged on the spherical zone KZ of the mixing chamber 1, since their longitudinal axes are inclined backwards with respect to the main direction of the hot gas flow H.
  • FIG. 2 shows the arrangement of two gas turbine combustion chambers designed according to FIG. 1 on the opposite sides of a gas turbine designated overall by GT.
  • the gas turbine combustion chamber shown on the left in the drawing the spatial arrangement of the connecting piece 40 and the manhole 44 on the spherical combustion chamber jacket 4 can be seen.
  • the connecting pieces 40 In the gas turbine combustion chamber shown on the right in the drawing, the connecting pieces 40 have been omitted in order to illustrate their arrangement on a total of four width circles BK of the spherical combustion chamber jacket 4.
  • Fig. 3 shows a longitudinal section through a primary combustion chamber 2 and the associated premix burner 3.
  • the primary combustion chamber 2 which could also be referred to as a flame tube, consists of a cylindrical flame tube jacket 21, at one end of which an end cover 22 is arranged and at the other end a connecting flange 23 is arranged.
  • the front end cover 22 has a central opening through which the premix burner 3 opens into the primary combustion chamber 2 provided with a refractory lining 24.
  • the end cover 22 has a further opening, which is arranged more towards the outer edge and via which a pilot burner 25 opens through the refractory lining 24 into the primary combustion chamber 2.
  • On the upper end flange 250 of the pilot burner 25, an ignition electrode 251, an air supply 252 and a gas supply 253 can be seen.
  • the openings 20 for access to the quenching air A are aligned radially and pass through the flame tube jacket 21 and the refractory lining 24.
  • the openings 20 are located in the end region of the primary combustion chamber 2, which is attached to the mixing chamber 1 shown in FIG. 1 via the connecting flange 23.
  • the premix burner 3 consists of an essentially cylindrical burner housing 31 which carries a swirl body 32 and a fuel nozzle 33 at one end and a flame holder 34 at the other end.
  • the liquid fuel supplied via the fuel feed 30 and atomized in the fuel nozzle 33 is evaporated and mixed with the burner air B. So that this mixing is as intensive as possible, the burner air B is swirled as it flows through the swirl body 32.
  • the homogeneous mixture consisting of the supplied burner air B and the vaporized fuel is only ignited in the primary combustion chamber 2 by the pilot burner 25, the flame holder 34 serving to stabilize the flame, but nevertheless preventing the flame from kicking back into the premixing chamber 35.
  • a flange 36 is provided, which is fixed on the end cover 22 of the primary combustion chamber 2 in a heat-elastic manner.
  • an electrical igniter can optionally also be used to ignite the mixture in the primary combustion chamber 2.
  • the combustion of the mixture generated in the premix burner 3 is completely completed within the primary combustion chamber 2 before the openings 20 for the access of the quenching air A, with the extremely short residence time of the burner air B in the flame zone forming only extremely small amounts of NO x .
  • the quenching air A supplied immediately after the combustion zone cools the hot gases and prevents a further increase in the nitrogen oxides by freezing the NO x formation reactions.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
EP83110020A 1982-10-19 1983-10-06 Gasturbinenbrennkammer Expired EP0109523B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3238684 1982-10-19
DE19823238684 DE3238684A1 (de) 1982-10-19 1982-10-19 Gasturbinenbrennkammer

Publications (2)

Publication Number Publication Date
EP0109523A1 EP0109523A1 (de) 1984-05-30
EP0109523B1 true EP0109523B1 (de) 1985-07-31

Family

ID=6176069

Family Applications (1)

Application Number Title Priority Date Filing Date
EP83110020A Expired EP0109523B1 (de) 1982-10-19 1983-10-06 Gasturbinenbrennkammer

Country Status (4)

Country Link
US (1) US4827724A (enrdf_load_stackoverflow)
EP (1) EP0109523B1 (enrdf_load_stackoverflow)
JP (1) JPS5989928A (enrdf_load_stackoverflow)
DE (2) DE3238684A1 (enrdf_load_stackoverflow)

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3241162A1 (de) * 1982-11-08 1984-05-10 Kraftwerk Union AG, 4330 Mülheim Vormischbrenner mit integriertem diffusionsbrenner
EP0193029B1 (de) * 1985-02-26 1988-11-17 BBC Brown Boveri AG Brennkammer für Gasturbinen
DE3606625A1 (de) * 1985-03-04 1986-09-04 Kraftwerk Union AG, 4330 Mülheim Pilotbrenner mit geringer no(pfeil abwaerts)x(pfeil abwaerts)-emission fuer feuerungsanlagen, insbesondere von gasturbinenanlagen, und verfahren zu seinem betrieb
DE3908542C2 (de) * 1989-03-16 1994-08-11 Daimler Benz Ag Vorrichtung zur Untersuchung von Verbrennungsvorgängen
US5596873A (en) * 1994-09-14 1997-01-28 General Electric Company Gas turbine combustor with a plurality of circumferentially spaced pre-mixers
DE19615910B4 (de) * 1996-04-22 2006-09-14 Alstom Brenneranordnung
GB2319078B (en) 1996-11-08 1999-11-03 Europ Gas Turbines Ltd Combustor arrangement
RU2225575C2 (ru) * 2001-12-06 2004-03-10 Межрегиональная общественная организация "Поволжское отделение Российской инженерной академии" Устройство для подвода топлива в камеру сгорания
JP6440433B2 (ja) * 2014-09-29 2018-12-19 川崎重工業株式会社 燃料噴射ノズル、燃料噴射モジュール、及びガスタービン
DE102020135067A1 (de) * 2020-12-29 2022-06-30 Chemin Gmbh Sondenkopf und Verwendung eines Sondenkopfs
US12173898B1 (en) 2023-09-01 2024-12-24 General Electric Company Combustion section with a primary combustor and a set of secondary combustors

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL69961C (enrdf_load_stackoverflow) * 1946-11-07
FR975715A (fr) * 1947-12-02 1951-03-08 Power Jets Res & Dev Ltd Perfectionnements apportés aux dispositifs de combustion
NL84788C (enrdf_load_stackoverflow) * 1951-06-12
GB715387A (en) * 1952-04-09 1954-09-15 Parsons & Marine Eng Turbine Improvements in or relating to combustion chambers for gas turbines or other prime movers
CH577627A5 (enrdf_load_stackoverflow) * 1974-04-03 1976-07-15 Bbc Sulzer Turbomaschinen
US3981675A (en) * 1974-12-19 1976-09-21 United Technologies Corporation Ceramic burner construction
US4012904A (en) * 1975-07-17 1977-03-22 Chrysler Corporation Gas turbine burner
CH595546A5 (enrdf_load_stackoverflow) * 1976-08-13 1978-02-15 Bbc Brown Boveri & Cie
US4351156A (en) * 1978-08-02 1982-09-28 International Harvester Company Combustion systems
DE2949388A1 (de) * 1979-12-07 1981-06-11 Kraftwerk Union AG, 4330 Mülheim Brennkammer fuer gasturbinen und verfahren zum betrieb der brennkammer
US4356698A (en) * 1980-10-02 1982-11-02 United Technologies Corporation Staged combustor having aerodynamically separated combustion zones

Also Published As

Publication number Publication date
DE3360470D1 (en) 1985-09-05
DE3238684A1 (de) 1984-04-19
JPS5989928A (ja) 1984-05-24
US4827724A (en) 1989-05-09
EP0109523A1 (de) 1984-05-30
JPH0223771B2 (enrdf_load_stackoverflow) 1990-05-25

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