EP0577862B1 - Dispositif de post-combustion - Google Patents

Dispositif de post-combustion Download PDF

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Publication number
EP0577862B1
EP0577862B1 EP92111347A EP92111347A EP0577862B1 EP 0577862 B1 EP0577862 B1 EP 0577862B1 EP 92111347 A EP92111347 A EP 92111347A EP 92111347 A EP92111347 A EP 92111347A EP 0577862 B1 EP0577862 B1 EP 0577862B1
Authority
EP
European Patent Office
Prior art keywords
damping
air
afterburner
combustion chamber
tube
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
EP92111347A
Other languages
German (de)
English (en)
Other versions
EP0577862A1 (fr
Inventor
Jakob Prof. Dr. Keller
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.)
ABB Research Ltd Sweden
Original Assignee
ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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 ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to DE59208193T priority Critical patent/DE59208193D1/de
Priority to EP92111347A priority patent/EP0577862B1/fr
Priority to CA002098810A priority patent/CA2098810A1/fr
Priority to US08/078,031 priority patent/US5431018A/en
Priority to JP5164642A priority patent/JPH0694227A/ja
Priority to KR1019930012484A priority patent/KR940002550A/ko
Publication of EP0577862A1 publication Critical patent/EP0577862A1/fr
Application granted granted Critical
Publication of EP0577862B1 publication Critical patent/EP0577862B1/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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
    • F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
    • F23M20/005—Noise absorbing means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2260/00—Function
    • F05B2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03341—Sequential combustion chambers or burners

Definitions

  • the invention relates to an afterburner for a gas turbine combustion chamber according to the preamble of claim 1.
  • Afterburner in gas turbine combustors are used to advantage when very low-emission oil or gas combustion is aimed for.
  • the gas flow downstream of the normal burner, into which fuel has already been introduced from a primary source can have an average temperature of approximately 850 ° C.
  • fuel that is injected through an afterburner can be ignited sufficiently quickly.
  • the ignition delay time is so short that the post-combustion process is initiated over a useful distance, for example 2 to 10 cm.
  • afterburners are not self-sufficient. A flame stabilization zone is intentionally avoided here.
  • An afterburner thus offers the possibility of also at very high speeds, i.e. to convert a lot of fuel in very short periods. Your advantage is that the time spent in a zone that is not perfectly pre-mixed can be kept almost as short as you like. It can therefore be mixed very quickly at high speed.
  • the fuel or an air-fuel mixture from the afterburner is usually blown into the afterburner chamber with a cross jet, where it is mixed in quickly and homogeneously. This is not possible with conventional burners, otherwise the flame stabilization required there would be lost.
  • the invention has for its object to dampen thermoacoustically fanned vibrations in an afterburner of the type mentioned.
  • a main burner with a Helmholtz resonator is already known from DE-A-33 24 805, which is supplied with two working means, namely combustion air and fuel.
  • the burner there must be self-sufficient in order to be able to function at all, ie it must be provided with flame stabilization (not shown, aerodynamic or mechanical) in order to implement a clearly defined reaction zone.
  • the actual damping pipes do not open into the combustion chamber in the area of the burner mouth, but rather open at specific intervals along the gas line path into the gas line path itself in order to be effective. This is to build up a standing pressure wave in the so-called gas line path between the burner mouth and the resonator, which is intended to dampen the corresponding vibration. After each of the resonance volumes there is connected to the fuel line via damping pipes, there is therefore no supply pipe and therefore no flow through a Helmholtz resonator.
  • the damping system can be effectively integrated into the afterburner, and because of the simple construction of an afterburner it is possible to design the afterburner itself or parts thereof as a damper.
  • the damping tube is designed as an annular channel.
  • the afterburner is thus encased in an air curtain that comes from the Helmholz resonator.
  • the damping medium flowing out of the damping tube in a ring shape into the afterburning chamber is therefore a component of the afterburning air.
  • the air used for damping purposes is therefore not considered lost.
  • a Nac burner arranged in a combustion chamber wall 1 is shown in simplified form in FIG.
  • the fuel is injected into the afterburning chamber 9 via an oil line 2 arranged centrally in the burner and / or via an annular gas lance 3 which surrounds the oil line 2.
  • the intention is, on the one hand, to fuel the gas very quickly into the existing gas volume to interfere, on the other hand to delay the reaction as long as possible. This avoids that very hot zones prevail over longer time intervals before the mixing process is complete.
  • the injected fuel jet is enveloped by an air jacket. This air jacket is brought up to the burner mouth 8 via an air duct 4.
  • the ends of the damper tube are rounded off at the inlet and outlet.
  • the exit of the annular damper tube is located in the immediate area of the burner mouth 8, so that it is encased by a further annular air curtain.
  • the location of the damping is decisive for the stabilization of a thermoacoustic oscillation.
  • the greatest increase occurs when the reaction rate and the pressure disturbance oscillate in phase.
  • the strongest reaction rate usually occurs near the center of the combustion zone.
  • the ring-shaped arrangement of the damping tube in the region of the mouth of the afterburner therefore has the effect that the damping effect is achieved at an optimal point.
  • the feed pipes 5 are dimensioned such that they cause a relatively high pressure drop for the inflowing air.
  • the limitation of the pressure drop in the damping pipes results from the requirement that even with uneven pressure distribution on the inside of the combustion chamber wall, a sufficient purge air flow into the afterburning chamber is always guaranteed.
  • hot gas must not enter the Helmholz resonator in the opposite direction at any point.
  • the Helmholz resonator is therefore dimensioned so that adequate purging is guaranteed. This prevents the damper from heating up and the resulting damper frequency drifting away.
  • the choice of the size of the Helmholtz volume 6 results from the requirement that the phase angle between the fluctuations in the damping air mass flows through the supply and Damping pipes should be greater than or equal to ⁇ / 2.
  • this requirement means that the volume should be at least so large that the Helmholtz frequency of the resonator, which is formed by the volume 6 and the openings 5 and 7, at least the frequency of the combustion chamber vibration to be damped.
  • the volume of the Helmholtz resonator used is preferably designed for the lowest natural frequency of the afterburner. It is also possible to choose an even larger volume. It is thereby achieved that a pressure fluctuation on the inside of the afterburning space leads to a strongly opposite phase fluctuation of the air mass flow, because the fluctuations in the damping air mass flows through the supply pipes and the damping pipes are no longer in phase.
  • the basic features of a flow through a Helmholtz resonator as can be used in a combustion chamber, but also everywhere else, are shown in FIG. 2.
  • the resonator essentially consists of the feed pipe 5a, the resonance volume 6a and the damping pipe 7a.
  • the feed pipe 5a determines the pressure drop.
  • the speed at the end of the feed pipe is adjusted so that the dynamic pressure of the jet together with the losses corresponds to the pressure drop across the combustion chamber. Only enough air is supplied that the interior of the damper does not heat up. Heating by radiation from the area of the combustion chamber would result in the frequency not remaining stable. The flushing should therefore only dissipate the radiated heat. So far, Helmholtz resonators are known.
  • This measure ensures, among other things, that the flow at the inlet and outlet of the damping tube does not completely separate, as is the case with sharp-edged entry and exit.
  • the entry and exit losses are lower, which means that the pulsating flow is much less lossy.
  • This low-loss design leads to very high vibration amplitudes, which in turn means that the desired high beam loss at the ends of the damping tube is further increased. In other words, the increase in amplitude more than compensates for the reduction in the loss coefficient.
  • the result is a Helmholtz resonator that has two to three times the damping power compared to the known resonators with flow.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fluidized-Bed Combustion And Resonant Combustion (AREA)
  • Gas Burners (AREA)
  • Spray-Type Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (3)

  1. Dispositif de post-combustion pour une chambre de combustion d'une turbine à gaz, dans lequel une arrivée de combustible (2, 3) disposée dans une paroi (1) de la chambre de combustion est entourée par un canal à air (4) annulaire, pour injecter un combustible en même temps que de l'air de post-combustion dans un courant de gaz circulant dans un volume de post-combustion (9), caractérisé en ce que le canal à air (4) communique avec un résonateur de Helmholtz parcouru par l'air de post-combustion, qui se compose essentiellement d'un tube d'arrivée (5), d'un volume de résonance (6) et d'un tube d'amortissement (7), dans lequel la sortie du tube d'amortissement (7) se trouve à proximité immédiate de l'embouchure (8) du brûleur dans le volume de post-combustion (9) et dans lequel le tube d'arrivée (5) relie le canal à air annulaire (4) avec le volume de résonance (6).
  2. Dispositif de post-combustion suivant la revendication 1, caractérisé en ce que le tube d'amortissement (7) est constitué par un canal annulaire, qui entoure le canal à air (4).
  3. Dispositif de post-combustion suivant la revendication 1, caractérisé en ce que le tube d'amortissement (7), qui relie le volume de résonance (6) au volume de post-combustion (9), est arrondi à l'extrémité d'entrée et à l'extrémité de sortie.
EP92111347A 1992-07-03 1992-07-03 Dispositif de post-combustion Expired - Lifetime EP0577862B1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
DE59208193T DE59208193D1 (de) 1992-07-03 1992-07-03 Nachbrenner
EP92111347A EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion
CA002098810A CA2098810A1 (fr) 1992-07-03 1993-06-18 Bruleur secondaire
US08/078,031 US5431018A (en) 1992-07-03 1993-06-18 Secondary burner having a through-flow helmholtz resonator
JP5164642A JPH0694227A (ja) 1992-07-03 1993-07-02 二次バーナ
KR1019930012484A KR940002550A (ko) 1992-07-03 1993-07-03 이차 버너

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP92111347A EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion

Publications (2)

Publication Number Publication Date
EP0577862A1 EP0577862A1 (fr) 1994-01-12
EP0577862B1 true EP0577862B1 (fr) 1997-03-12

Family

ID=8209779

Family Applications (1)

Application Number Title Priority Date Filing Date
EP92111347A Expired - Lifetime EP0577862B1 (fr) 1992-07-03 1992-07-03 Dispositif de post-combustion

Country Status (6)

Country Link
US (1) US5431018A (fr)
EP (1) EP0577862B1 (fr)
JP (1) JPH0694227A (fr)
KR (1) KR940002550A (fr)
CA (1) CA2098810A1 (fr)
DE (1) DE59208193D1 (fr)

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US8869533B2 (en) 2011-01-07 2014-10-28 Siemens Aktiengesellschaft Combustion system for a gas turbine comprising a resonator

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Publication number Priority date Publication date Assignee Title
US8869533B2 (en) 2011-01-07 2014-10-28 Siemens Aktiengesellschaft Combustion system for a gas turbine comprising a resonator

Also Published As

Publication number Publication date
EP0577862A1 (fr) 1994-01-12
KR940002550A (ko) 1994-02-17
CA2098810A1 (fr) 1994-01-04
JPH0694227A (ja) 1994-04-05
DE59208193D1 (de) 1997-04-17
US5431018A (en) 1995-07-11

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