EP0918194A1 - Procédé et arrangement d'un système de brûleur et procédé et dispositif pour déterminer les propriétés d'un brûleur - Google Patents

Procédé et arrangement d'un système de brûleur et procédé et dispositif pour déterminer les propriétés d'un brûleur Download PDF

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Publication number
EP0918194A1
EP0918194A1 EP97810904A EP97810904A EP0918194A1 EP 0918194 A1 EP0918194 A1 EP 0918194A1 EP 97810904 A EP97810904 A EP 97810904A EP 97810904 A EP97810904 A EP 97810904A EP 0918194 A1 EP0918194 A1 EP 0918194A1
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EP
European Patent Office
Prior art keywords
acoustic
burner
test
downstream
upstream
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.)
Withdrawn
Application number
EP97810904A
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German (de)
English (en)
Inventor
Christian Oliver Dr. Paschereit
Wolfgang Dr. Polifke
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 Switzerland
ABB Research Ltd Sweden
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ABB Research Ltd Switzerland
ABB Research Ltd Sweden
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Publication date
Application filed by ABB Research Ltd Switzerland, ABB Research Ltd Sweden filed Critical ABB Research Ltd Switzerland
Priority to EP97810904A priority Critical patent/EP0918194A1/fr
Publication of EP0918194A1 publication Critical patent/EP0918194A1/fr
Withdrawn legal-status Critical Current

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    • 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
    • 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

Definitions

  • the invention relates to a method for designing a Combustion system, in particular a combustion chamber Gas turbine.
  • the invention further relates to a method and a device for determining thermoacoustic Properties of a burner, especially one Gas turbine burner.
  • Thermoacoustic combustion instabilities are one Danger to a variety of different combustion systems, such as household burners, gas turbines or rocket engines
  • the instabilities show a feedback of the Fluctuations in pressure and speed with the Heat release rate of the combustion process.
  • Vibration amplitude come up, which leads to undesirable effects, how about a high mechanical load on the Combustion chamber, increased emissions due to an inhomogeneous Burn or extinguish the flame.
  • thermoacoustic Properties of the system As early as possible. To model calculations can be used for this purpose in which the physical combustion system through a network acoustic elements.
  • the acoustic Elements correspond to the different components of the Systems, such as combustion chamber, fuel and air supply, Burner and flame, combustion chamber hood and cooling channels.
  • Burner and flame For the most of these components provide simple analytical Models have a sufficient description of their thermoacoustic Characteristics.
  • the complex presents difficulties Burner and flame response to thermoacoustic Disturbances, i.e. modeling the acoustic Transfer function or the source strength of the burner and Flame.
  • thermoacoustic advantageous design of a combustion system of the independent claim 1 the method for determining the Multipole transfer matrix and source strength of a burner of the independent claim 7 and the flow-through trainer to determine the multipole transfer matrix and source strength of a burner of independent claim 12.
  • thermoacoustic advantageous design of a combustion system includes Combustion system at least one combustion chamber and one Burner.
  • the combustion system is through a network acoustic elements, with a first acoustic Element the burner and a second acoustic element the Combustion chamber represents.
  • Other elements of the network For example, combustion chamber hood, cooling channels, Represent compressor diffuser and the like.
  • the burner is represented by an acoustic signal Multiple gate represented with source term.
  • the simplest case of the description is an acoustic one-port, in which the burner with flame is represented by a source strength f s and a reflection coefficient r s .
  • the relationship f r s G + f s , the Riemann invariants f and g then describe the progress of the acoustic wave in the positive and negative direction.
  • This treatment is suitable if the burner is always installed under the same conditions. Different combustion systems usually differ in their acoustic boundary conditions upstream and downstream of the burner. If the boundary conditions change, it then becomes necessary to redetermine the source strength and the reflection coefficient.
  • the burner is preferably represented by an acoustic two-port with source term.
  • the acoustic two-port is given by the equation described, wherein and are acoustic vectors that describe the pressure p and the velocity v upstream (index u) and downstream (index d) of the burner.
  • the vector describes the source strength of the burner and T is a four-pin transfer matrix with the components
  • equation (1) can also be written as
  • the acoustic double gate has two gates, which are called the entrance gate ( p u ) and the exit gate ( p d ).
  • the corresponding multipole transfer matrix then takes the place of the four-pole transfer matrix from equation (1).
  • the corresponding 2 n -pol transfer matrix represents an nxn matrix.
  • thermoacoustic fluctuations of the Network of acoustic elements can be calculated. Thereby in usually the amplitude and / or phase of the pressure fluctuations determined in response to a given suggestion.
  • the Answer depends on the frequency, in annular geometries in usually additionally from the azimuthal mode number m.
  • the Calculated pressure fluctuations are based on specified criteria compared to the thermoacoustic stability of the To assess the combustion system.
  • the individual acoustic elements adjusted until the predetermined criteria are met. For example by changing the geometry of the combustion chamber or the thermoacoustic properties of the burner happen.
  • Combustion system In addition to the combustion chamber and burner, this can be done Combustion system other elements, such as one Combustion chamber hood, plenum, compressor diffuser, cooling channels and the like. Then in the performing network appropriate acoustic elements are included if this is necessary for a more precise assessment of the stability is.
  • thermoacoustic fluctuations of the network are preferably calculated using the following method: First, the transfer matrices that can be derived from the acoustics and fluid dynamics are set up for the individual elements. The individual elements are then linked to form a network, so that the overall system in the form of a linear system of equations, the system equation is described.
  • the vector of the unknowns y is made up of the acoustic variables pressure and speed, or the equivalent Riemann invariants f and g , and possibly other auxiliary variables.
  • the vector of the inhomogeneities r represents the existing excitation mechanisms such as external or internal excitation due to fluid mechanical instabilities, discontinuities in the compressor or the fuel pumps, actuators, loudspeakers and the like.
  • Equation (3) thus allows the calculation of the system response, ie the amplitudes of the system variables at the ends of the respective elements, on a given excitation.
  • thermoacoustic properties of a Brenners can be better described. Will the thermoacoustic properties of the burner through a Multipole transfer matrix and a source strength are specified them from one combustion system to another Combustion system easier to transfer. Are these sizes for a burner and combustion system has been determined when installing the burner in a new environment, no new one Determination of its properties necessary. Rather, it can new environment along with the burner with the familiar Properties of the burner directly on stability to be examined. This reduces the experimental effort drastically and leads to a significant time saving the design and construction of the combustion system.
  • thermoacoustic properties of a burner can be modified with in compliance with the flow-through test stand according to the invention of the inventive method for determining the multipole transfer matrix and source strength of a burner determined become.
  • the flow through test stand for determining the multipole transfer matrix and source strength of a burner includes one Device for introducing a burner, means for Changing the acoustic conditions upstream and / or downstream of the burner and means for measuring the Pressure distribution upstream and downstream of the burner.
  • the Acoustic conditions can be determined by passive acoustic Loads, such as attachable pipe pieces of various lengths and diameter can be changed.
  • the acoustic conditions can preferably be upstream and / or downstream through active acoustic sources, such as speakers or other acoustic signaling devices can be changed.
  • the acoustic sources are preferably axial and azimuthal distributed.
  • the sources are at the same axial position preferably on the circumference of the trainer in equals azimuthal angular distances. So you can by adjusting the phase differences between the sources achieve different azimuthal excitation modes.
  • the Pressure distribution is preferably measured by microphones, however there are also other sensors, such as piezoelectric Pressure sensors in the context of the invention.
  • the Test stand a plenum chamber upstream of the burner, one Combustion chamber downstream of the burner and a cooling air supply on.
  • Test states There will be at least two different acoustic signals Test states set and with each test state the Pressure distribution measured upstream and downstream of the burner.
  • the various acoustic test states can be passive acoustic loads and / or through active acoustic sources can be set.
  • the change in acoustic Conditions can be both upstream and downstream of the Brenners done, however, the change can only be made to one side of the burner is sufficient.
  • the different Test conditions should be chosen so that they are linear from each other are independent.
  • the pressure distribution is preferred with Microphones measured, the measurement lies with other sensors however within the scope of the invention. In particular, the measurement acoustic speed using modern methods Flow measurement technology, such as laser Doppler anemometry in Scope of the invention.
  • the trainer 10 consists of the plenum chamber 12 upstream the burner 20, the combustion chamber 14 downstream of the burner, the Exhaust system 18, the combustion air supply 22, and Cooling air supply 24.
  • the plenum chamber 12 contains perforated Plates (not shown) to increase the turbulence of the air flow to reduce.
  • the combustion chamber 14 consists of air-cooled double-walled quartz glass 16 for a perfect optical To ensure access to the flame.
  • the exhaust system 18 consists of an air-cooled tube with the same Cross section like the combustion chamber, so that acoustic reflections be avoided due to different cross-sectional areas.
  • the acoustic boundary conditions of the exhaust system can on the adjustable end 26 can be varied over a wide range.
  • the speaker arrays 30 and 32 each consist of four Speakers on the scope of the test stand in azimuthal distances of 90 ° are attached.
  • the gas flow upstream and downstream of the burner 20 can pass through it be stimulated in a controlled manner.
  • For axially symmetrical excitation become the speakers of an array with a phase difference operated from zero.
  • By a non-zero Phase difference are also not axially symmetrical excitations adjustable.
  • the pressure fluctuations become upstream and downstream measured with the water-cooled microphone arrays 34 and 36.
  • Condenser microphones are preferably used with which Phase and amplitude of the pressure fluctuations with high Accuracy can be measured.
  • the microphone diaphragms are housed in small chambers and are protected from heat radiation.
  • the burner When the burner is described as an acoustic single gate, various methods are suitable for determining the unknowns r s and f s , which are differentiated as methods with and without an external source.
  • External source methods are performed in two steps. First, the reflection coefficient of the source is determined with external excitation. Known methods such as the two-microphone method are used for this. In a second step, the external source is switched off and the source strength of the burner is determined using a known terminating impedance of the acoustic system. In methods without external sources, the unknowns r s and f s are determined with the aid of the "multi-load" method, in which two linearly independent test states are set by different acoustic termination conditions at the outlet of the system.
  • the acoustic four-pole transfer matrix contains four unknown, complex components and the source strength vector p s contains two complex components.
  • the complete description of the burner as an active acoustic two-port requires in the most general case the determination of six unknowns. This requires the measurement of three linearly independent test states.
  • Experimental studies have shown that the source strength vector is small in many cases, since there are only slight differences between the results with and without a burner flame. An explicit determination of the swelling strength can thus be dispensed with in many cases without introducing a major error in the determination of the thermoacoustic properties.
  • only four unknowns have to be determined, for which a measurement on two linearly independent test states is sufficient. It is preferable to choose exactly two different test states, since the resulting system of four linearly independent equations has a clear solution.
  • two acoustic test states are carried out two different acoustic loads are set.
  • the test states are different Suggestions with active acoustic sources, here the Speakers. This method is preferred because with her more clearly different acoustic conditions can be set and it leads to fewer errors.
  • thermoacoustic parameters of a burner in a trainer After determining the thermoacoustic parameters of a burner in a trainer according to the invention, a Combustion system to contain such a burner using the method described above to thermoacoustic Stability. After that, a so designed System manufactured and approximately one as a combustion system Gas turbine are used.
  • the azimuthal structure of acoustic disturbances in the annular gap is characterized by a mode number m .
  • the elements of the transfer matrices are then generally dependent on m .
  • g (x, t) g (t + x / c) represent a clockwise or counterclockwise shaft.
  • the size c denotes the speed of sound.
  • annular gap of low height is particularly relevant for the modeling of annular combustion chambers. Applies to the m th mode of an annular gap with radius R f (x, y, t) ⁇ exp (i ⁇ t-ik x + cos (k y y) g (x, y, t) ⁇ exp (i ⁇ t-ik x- ) cos (k y y) .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Combustion (AREA)
EP97810904A 1997-11-24 1997-11-24 Procédé et arrangement d'un système de brûleur et procédé et dispositif pour déterminer les propriétés d'un brûleur Withdrawn EP0918194A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP97810904A EP0918194A1 (fr) 1997-11-24 1997-11-24 Procédé et arrangement d'un système de brûleur et procédé et dispositif pour déterminer les propriétés d'un brûleur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP97810904A EP0918194A1 (fr) 1997-11-24 1997-11-24 Procédé et arrangement d'un système de brûleur et procédé et dispositif pour déterminer les propriétés d'un brûleur

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EP0918194A1 true EP0918194A1 (fr) 1999-05-26

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1703344A1 (fr) * 2005-02-10 2006-09-20 ALSTOM Technology Ltd Procédé pour produire une unité de régulation basée sur un modèle
DE102008022117A1 (de) 2007-06-15 2008-12-18 Alstom Technology Ltd. Verfahren und Prüfstand zum Bestimmen einer Transferfunktion
CN111751110A (zh) * 2020-07-04 2020-10-09 西北工业大学 一种用于固体推进剂振荡燃烧的碳纤维释热发声装置
CN115013187A (zh) * 2022-06-24 2022-09-06 哈尔滨工程大学 一种固体推进剂压强耦合响应函数测量方法及模具

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4144768A (en) * 1978-01-03 1979-03-20 The Boeing Company Apparatus for analyzing complex acoustic fields within a duct
US4557106A (en) * 1983-11-02 1985-12-10 Ffowcs Williams John E Combustion system for a gas turbine engine
US4644783A (en) * 1984-07-16 1987-02-24 National Research Development Corp. Active control of acoustic instability in combustion chambers
US5489202A (en) * 1992-11-09 1996-02-06 Foster Wheeler Energy Corporation Vibration of systems comprised of hot and cold components
WO1998014693A1 (fr) * 1996-09-30 1998-04-09 Silentor Notox A/S Silencieux pour flux de gaz

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4144768A (en) * 1978-01-03 1979-03-20 The Boeing Company Apparatus for analyzing complex acoustic fields within a duct
US4557106A (en) * 1983-11-02 1985-12-10 Ffowcs Williams John E Combustion system for a gas turbine engine
US4644783A (en) * 1984-07-16 1987-02-24 National Research Development Corp. Active control of acoustic instability in combustion chambers
US5489202A (en) * 1992-11-09 1996-02-06 Foster Wheeler Energy Corporation Vibration of systems comprised of hot and cold components
WO1998014693A1 (fr) * 1996-09-30 1998-04-09 Silentor Notox A/S Silencieux pour flux de gaz

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1703344A1 (fr) * 2005-02-10 2006-09-20 ALSTOM Technology Ltd Procédé pour produire une unité de régulation basée sur un modèle
DE102008022117A1 (de) 2007-06-15 2008-12-18 Alstom Technology Ltd. Verfahren und Prüfstand zum Bestimmen einer Transferfunktion
DE102008022117B4 (de) 2007-06-15 2019-04-04 Ansaldo Energia Switzerland AG Verfahren und Prüfstand zum Bestimmen einer Transferfunktion
CN111751110A (zh) * 2020-07-04 2020-10-09 西北工业大学 一种用于固体推进剂振荡燃烧的碳纤维释热发声装置
CN111751110B (zh) * 2020-07-04 2021-05-14 西北工业大学 一种用于固体推进剂振荡燃烧的碳纤维释热发声装置
CN115013187A (zh) * 2022-06-24 2022-09-06 哈尔滨工程大学 一种固体推进剂压强耦合响应函数测量方法及模具

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