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EP2993406A1 - Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz - Google Patents

Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz Download PDF

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Publication number
EP2993406A1
EP2993406A1 EP14183316.0A EP14183316A EP2993406A1 EP 2993406 A1 EP2993406 A1 EP 2993406A1 EP 14183316 A EP14183316 A EP 14183316A EP 2993406 A1 EP2993406 A1 EP 2993406A1
Authority
EP
European Patent Office
Prior art keywords
passage
burner
fuel
primary fuel
primary
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Withdrawn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
EP14183316.0A
Other languages
German (de)
English (en)
Inventor
Matthias Hase
Berthold Köstlin
Bernd Prade
Stefan Wyhnalek
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.)
Siemens AG
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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 Siemens AG, Siemens Corp filed Critical Siemens AG
Priority to EP14183316.0A priority Critical patent/EP2993406A1/fr
Publication of EP2993406A1 publication Critical patent/EP2993406A1/fr
Withdrawn legal-status Critical Current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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous 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
    • 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 operating a gas turbine with which pressure pulsations in the combustion chamber of the gas turbine can be reduced.
  • the invention also relates to a burner which is particularly suitable for carrying out the method.
  • At least one burner of the gas turbine is operated accordingly.
  • a burner suitable for carrying out the method comprises a primary fuel passage with a passage exit facing the combustion zone and an air passage arranged adjacent to the primary fuel passage with an air passage exit pointing to the combustion zone.
  • a mixed with fuel or pure compressor air flow from the air passage is introduced adjacent to a flowing from the Primärbrennstoffpassgage primary fuel flow into the combustion zone.
  • the two passage exits can for example be arranged concentrically to one another.
  • a generic burner is for example in the WO 2011 157458 A1 disclosed.
  • the disclosure of the patent specification is included in the present patent application.
  • the primary fuel supply unit of the burner of the prior art is designed to be charged with synthesis gas. This also preferably applies to the burner of the present invention. Due to the lower calorific value of the synthesis gas such passages are designed for particularly high flow rates.
  • the primary fuel supply unit includes a primary mixer tube and a downstream fuel nozzle. To form the fuel passage, the primary mixer tube and the outer wall of the fuel nozzle are spaced from the secondary fuel supply unit. The passage is thus annular space.
  • the fuel nozzle includes a fuel nozzle inlet facing the primary mixing tube and a fuel nozzle exit facing the combustion zone. Downstream of the fuel nozzle inlet and along a first passage section, the height of the primary fuel passage is substantially constant. Adjacent to this first passage section is a second passage section extending up to the fuel nozzle exit.
  • the primary mixing tube and the fuel nozzle could also be integrally formed.
  • the fuel nozzle is arranged as an exchangeable component in the burner.
  • the Indian WO 2011157458 A1 disclosed burner has to reduce pressure pulsations swirl vanes in the primary fuel passage with a specially designed for this purpose inlet length to the fuel nozzle inlet.
  • the invention has for its object to provide a generic burner, which is suitable in the operation of the gas turbine for performing the method and is operable so that at least in a first operating state of the gas turbine pressure pulsations of the gas turbine are particularly effectively avoided or at least reduced.
  • the invention is also based on the object of specifying a method for operating a gas turbine, with which a generic burner in at least a first operating state the gas turbine is operated such that pressure pulsations of the gas turbine are particularly effectively avoided or at least reduced.
  • the object is achieved in a burner of the type mentioned above in that the ratio of the cross-sectional area of the primary fuel passage at the fuel nozzle outlet divided by the cross-sectional area at the beginning of the second passage section is 0.7 to 0.9.
  • the burner according to the invention makes it possible to operate the burner at the same load range and supply pressure at a much lower speed level in the primary fuel passage, which is preferably designed as a synthesis gas passage due to the small reduction in cross-sectional area in the fuel nozzle than in the aforementioned burner of the prior art.
  • the frequencies of the instabilities occurring in the shear flow which are excited in the shear flow between the two fluid streams (ie, the fluid flow emerging from the air passage and the fluid flow emerging from the primary fuel passage), shift to smaller values.
  • These instabilities are pressure fluctuations, especially occurring vortex streets.
  • the instabilities occurring in a shear flow can be due, for example, to so-called Kelvin-Helmholtz instabilities.
  • Kelvin-Helmholtz instabilities In general, at a given operating state of the burner and thus a predetermined Relative velocity in said shear flow an instability of substantially a frequency excited.
  • the relative velocities and proportionally thereto the excited frequencies are at the claimed interval at least a factor of 1.5 to 2 below the frequencies of the burner of the prior art.
  • the burner according to the invention is suitable for carrying out the claimed method, for example burners of a gas turbine of the power class of the gas turbine type SGTx-2000E LC (product name of the applicant).
  • the specified interval makes it possible to obtain relevant areas of fuel split, speed and swirl number.
  • the cross-sectional area of the primary fuel passage along the second passage portion may decrease substantially steadily / continuously.
  • the ratio of the cross-sectional areas is 0.8 to 0.9.
  • the inner side of the outer wall of the fuel nozzle facing the secondary fuel feed unit has a substantially cylindrical jacket-shaped design along the first passage section.
  • a further preferred embodiment of the invention may provide that the outer wall of the fuel nozzle along the second passage portion is formed tapered in the flow direction.
  • the ratio of the height of the primary fuel passage at the fuel nozzle outlet divided by the radius of the fuel nozzle outlet is 0.125 to 0.16, in particular 0.149 to 0.151.
  • the radius of the fuel nozzle exit divided by the radius of the air passage exit 0.5 to 0.6, in particular 0.54 to 0.56, is.
  • a swirl generator can be arranged in the fuel nozzle upstream of the second passage section.
  • the swirl generator may comprise, for example, a number of swirl vanes arranged circumferentially in the fuel nozzle.
  • the swirl generator can for example also consist of fluid acted upon, circumferentially arranged on the outer wall of the fuel nozzle air nozzles, which inject to impinge the passage flow with a swirl, for example, air with a directed in the circumferential direction of the primary fuel passage component.
  • the swirl generator could, for example, also be a disk arranged transversely to the passage and penetrated by a multiplicity of holes extending through the disk.
  • the holes are made according to the desired twist.
  • the spin in the primary fuel passage is defined as the ratio of angular momentum to the product of the nozzle exit radius and the axial momentum of the primary fuel flow flowing in the passage Angular momentum and axial momentum are considered at the nozzle exit.
  • the swirl generator can be selected such that in at least a first operating state of the burner, a swirl of 1.6 to 2.2, in particular from 1.7 to 2.0, in the primary fuel passage can be effected.
  • the claimed interval has proved to be stabilizing for the combustion, in particular at the lower speed level according to the invention in the primary fuel passage. If a swirl generator with swirl blades is formed, the swirl blades are designed in such a way and arranged with a blade angle that the claimed area of the swirl can be effected.
  • the swirl generator comprises a circumferentially arranged in the fuel nozzle number of swirl vanes, each having a leading edge, wherein the inlet length between the fuel nozzle inlet and the leading edge divided by the height in the region of the swirl generator of the primary fuel passage 0.95 to 0.5 , in particular 0.6 to 0.7.
  • the claimed interval has proved to be stabilizing for the combustion, in particular at the lower speed level according to the invention in the primary fuel passage.
  • an advantageous embodiment of the invention can provide that the outer wall of the fuel nozzle comprises a number of injection openings which fluidly connect the primary fuel passage with the air passage, wherein the sum of the cross-sectional areas of the injection openings and their arrangement in the primary fuel passage are selected in that for at least one first operating state of the burner, a primary fuel split in the air passage of 10% - 30%, in particular 15% to 20%, is effected.
  • the claimed interval of the fuel split ensures a broadening of the time delay profile of the primary fuel flow, which has proven to be advantageous or particularly advantageous for the additional reduction of pressure pulsations.
  • the fuel introduced into the air passage via the injection openings can preferably be injected into the air passage beyond the width of the shear flow. This results in an advantageous broadening of the time delay profile of the introduced via the two outputs in the combustion chamber primary fuel flow.
  • the injection openings are arranged in the downstream end region of the first passage section.
  • injection openings are arranged downstream of a swirl generator arranged in the air passage.
  • the injection openings may have a slot-shaped cross-sectional area, wherein the longitudinal axes of the slots extend at an angle to a main flow direction in the air passage.
  • length to width of the cross-sectional area of the slots may be 3-7, more preferably 4-5.
  • This embodiment of the slots enables advantageous injection of the fuel at reasonable production costs of the fuel nozzle.
  • the injection openings may be arranged in one or more circumferential rows.
  • the invention is also based on the object of specifying a method for operating a gas turbine, with which at least one burner of the gas turbine is operated in at least a first operating state of the gas turbine such that pressure pulsations of the gas turbine are particularly effectively avoided or at least reduced.
  • the object is achieved by a method for operating a gas turbine having at least one burner, wherein the burner has a primary fuel passage with a combustion chamber facing passage exit and a - arranged in particular concentric to the primary fuel passage - air passage with pointing to the combustion zone air passage exit.
  • a mixed or pure compressor air stream is introduced from the air passage and flowing into the combustion zone adjacent to a primary fuel stream flowing out of the primary fuel passgage.
  • the burner is operated in at least the first operating state with a mean air velocity in the air passage and a mean primary fuel velocity in the primary fuel passage such that due to a relative velocity between the two flows in the shear layer, an instability of a substantially first Frequency is excited, wherein the relative velocity is selected such that the first frequency is unsuitable by means of an interaction with the flame to initiate a pressure pulsation in the combustion chamber.
  • a first operating state and a first frequency can be selected such that even when passing through an operating interval comprising the first operating state, the traversing frequencies of instability in the shear flow so far are removed from the excitable eigenmodes of the combustion chamber, that even in the wider operating interval, an interaction with the flame is not given or at least reduced.
  • the shear flow can also be referred to as a shear layer.
  • the excited instabilities in the shear layer are pressure fluctuations, especially vortex streets.
  • the instabilities occurring in a shear flow can be due, for example, to so-called Kelvin-Helmholtz instabilities.
  • Kelvin-Helmholtz instabilities In general, in the case of a given operating state of the burner and thus a given relative velocity in the said shear flow, an instability of substantially one frequency is excited.
  • the first operating state in a load range of the gas turbine may be from 50 to 100%.
  • the method can be applied by suitable choice of the first frequency and the first operating state and with knowledge of the excitable eigenmodes of the combustion chamber on any type of gas turbine with corresponding burners according to claim 17.
  • the burner specified in claim 1 is only one embodiment of a burner, with which the inventive method, in particular when using the burner in a gas turbine of the type SGTx-2000E LC, can be performed.
  • the invention also includes carrying out the method for operating other types of gas turbine, provided that at least one burner of the gas turbine comprises corresponding passages as claimed in claim 17.
  • the gas turbine is operated at least in the first operating state at a relative speed of 50 to 100 m / s, in particular 60 to 80 m / s between the two passages of the burner.
  • the average velocity in the primary fuel passage at least in the first operating state is 120 to 180 m / s, in particular 140 to 160 m / s.
  • a swirl of 1.6 to 2.2, in particular 1.7 to 2.0 is impressed on the primary fuel flow in the primary fuel passage by means of a swirl generator.
  • the spin in the primary fuel passage is defined as the ratio of angular momentum to the product of the nozzle exit radius and the axial momentum of the primary fuel flow flowing in the passage, with angular momentum and axial momentum being considered at the nozzle exit.
  • the claimed interval of the fuel split ensures a broadening of the time delay profile of the primary fuel flow, which has proven to be advantageous or particularly advantageous for the additional reduction of pressure pulsations.
  • the fuel branched off into the air passage can be injected substantially deeper into the air passage than the shear layer is thick. This allows a particularly advantageous broadening of the delay time profile.
  • the flow in the air passage is preferably upstream of the injection openings to a pure compressor air flow without further fuel admixtures.
  • the air passage may comprise no further opening into the air passage fuel nozzles except for the injection openings.
  • FIG. 1 shows a sectional view of a gas turbine 1 according to the prior art in a schematically simplified representation.
  • the gas turbine 1 has in its interior a rotatably mounted about a rotation axis 2 rotor 3 with a shaft 4, which is also referred to as a turbine runner.
  • a turbine runner which is also referred to as a turbine runner.
  • an intake housing 6 a compressor 8
  • a combustion system 9 with at least one combustion chamber 10 each comprising a burner assembly with burners 11, a fuel supply system for the burner (not shown) and a housing 12, a turbine 14 and an exhaust housing 15.
  • a gas turbine according to the invention may, for example, comprise an annular combustion chamber or have one or more tube combustion chambers.
  • the plurality of tube combustion chambers may be arranged, for example, annular.
  • the combustion system 9 communicates with an annular hot gas duct, for example.
  • a plurality of successively connected turbine stages form the turbine 14.
  • Each turbine stage is formed of blade rings. Viewed in the flow direction of a working medium follows in the hot runner formed by a number 17 vanes row formed from blades 18 row.
  • the guide vanes 17 are fastened to an inner housing of a stator 19, whereas the moving blades 18 of a row are attached to the rotor 3, for example by means of a turbine disk.
  • Coupled to the rotor 3 is, for example, a generator (not shown).
  • FIG. 2 shows a half of a rotationally symmetrical burner according to an embodiment of the invention in a longitudinal section.
  • the burner 24 is arranged rotationally symmetrically about a central burner axis 26.
  • the burner 24 includes a central secondary fuel supply unit 28, a primary fuel supply unit 30 arranged concentrically around the secondary fuel supply unit 28 and an annular air passage 32 arranged concentrically around the primary fuel supply unit 30 with an air passage exit 36 facing into the combustion zone 34.
  • the primary fuel supply unit 30 includes a primary mixer tube 38 and a downstream fuel nozzle 40.
  • the primary mixer tube 38 and an outer wall 42 of the fuel nozzle 40 are spaced from the secondary fuel supply unit 28 so that an annular primary fuel passage 44 is formed, with the fuel nozzle 40 forming a primary mixer tube 38 pointing fuel nozzle inlet 46 and a fuel nozzle exit 48 facing the combustion zone.
  • the height h of the primary fuel passage 44 is substantially constant downstream of the fuel nozzle inlet 46 and along a first passage portion 44a. Adjoining the first passage portion 44a is a second passage portion 44b extending to the fuel nozzle exit 48.
  • the ratio of the cross-sectional area 50 of the primary fuel passage 44 at the fuel nozzle exit 48 divided by the cross-sectional area 52 at the beginning of the second passage section is 0.7 to 0.9.
  • the ratio of the cross-sectional areas can be 0.8 to 0.9.
  • the drawing is to be understood schematically.
  • the inner side 54 of the outer wall 42 of the fuel nozzle 40, which faces the secondary fuel feed unit 28, along the first passage section 44a has a substantially cylinder jacket-shaped design.
  • the outer wall 42 of the fuel nozzle 40 is tapered along the second passage portion 44b in the flow direction.
  • the ratio of the height h a of the primary fuel passage 44 at the fuel nozzle outlet 48 divided by the radius of the fuel nozzle exit R a is preferably 0.125 to 0.16, in particular 0.149 to 0.151.
  • the ratio of the radius of the fuel nozzle outlet R a to the radius of the air passage exit R L is preferably 0.5 to 0.6, in particular 0.54 to 0.56.
  • a swirl generator having a circumferentially arranged number of swirl vanes is arranged.
  • the swirl vanes in the fuel nozzle are attached to the inside 54 and designated 56.
  • the swirl vanes in the air passage 32 are designated 58.
  • the swirl blades have a blade angle for imparting a twist to the flow past it. Depending on the blade angle, a stronger or less strong twist can be set. It is known to those skilled in the art how to arrange the blades in the passage to create a desired spin in the passage.
  • the swirl vanes 56 preferably have a blade angle which, in at least one first operating state of the burner, causes a swirl of 1.6 to 2.2, in particular 1.7 to 2.0.
  • the swirl in the primary fuel passage is defined as the ratio of angular momentum to the product of the nozzle exit radius and the axial momentum of the primary fuel flow flowing in the passage, with angular momentum and axial momentum being considered at the nozzle exit.
  • the swirl generator could also comprise other means instead of swirl blades, which are suitable for imparting a twist to the flow. Possible alternative embodiments of swirl generators are described, for example, above.
  • the swirl blades 56 arranged in the fuel nozzle have a leading edge 62.
  • the inlet length between the fuel nozzle inlet 46 and the leading edge 62 is denoted by S.
  • the ratio S through the height h of the passage in the region of the swirl generator is preferably 0.95 to 0.5, in particular 0.6 to 0.7.
  • the outer wall 42 of the fuel nozzle includes a number of injection ports 64 fluidly connecting the primary fuel passage 44 to the air passage 32, the sum of the cross-sectional areas 66 of the injection ports 64 and their location in the primary fuel passage 44 being selected such that for at least one first operating condition of the burner, a primary fuel split in the air passage of 10% - 30%, in particular 15% to 20%, can be effected.
  • the injection ports 64 are disposed in the downstream end portion of the first passage portion 44a.
  • the injection openings 64 are also arranged downstream of the swirl generator with swirl vanes 58 arranged in the air passage.
  • injection openings can be designed and arranged such that the branched off fuel is pressed into the air passage beyond the thickness of the shear layer in the at least first operating state, resulting in a particularly advantageous broadening of the delay time profile of the primary fuel flow flowing out of the two outlets.
  • the FIG. 3 shows that of the in FIG. 2 shown burner 24 included fuel nozzle 40 in a perspective view.
  • the fuel nozzle 40 comprises an exchangeable component of the burner 24.
  • the fuel nozzle comprises the outer wall 42, which, starting from the fuel nozzle inlet 46, initially has a substantially cylinder-jacket shape with swirl vanes 56 arranged on the inner side 54.
  • the injection openings 64 run through the wall 42.
  • the cylindrical region of the wall 42 is adjoined by a conically tapering region of the wall 42 extending up to the nozzle outlet 48.
  • the FIG. 4 shows a flowchart of the method according to the invention.
  • a first frequency is determined (step S1) for at least one first operating state of the gas turbine, which is unsuitable for starting a pressure pulsation in the combustion chamber by means of an interaction with the flame.
  • the largest possible operating range around the first operating state covers an instability frequency range which is likewise unsuitable for stimulating an interaction with the flame in the respective operating states.
  • the operating range preferably covers substantially the entire operating range of the gas turbine.
  • step S3 When selecting the first frequency is also taken into account whether (step S3) a burner for providing the necessary for the first operating state flow rates in the air passage and the primary fuel passage at associated relative speed between the two adjacent streams can be produced or selected.
  • the method is then carried out during operation of the gas turbine with the burner by operating (step M1) the burner in the first operating state with the corresponding relative speed and (method step M2) in the shear layer the first frequency of instability in the shear zone which is unsuitable for increasing the pressure pulsations is produced.
  • step M1 the burner in the first operating state with the corresponding relative speed
  • method step M2 in the shear layer the first frequency of instability in the shear zone which is unsuitable for increasing the pressure pulsations is produced.
  • the frequency must only be sufficiently far away from a stimulable eigenmode of the combustion chamber. These distances are known to the person skilled in the art or can be determined in a simple manner.
  • the instability stimulus may be based on the excitation of Kelvin-Helmholtz instability.
  • the burner can preferably be operated in the first operating state with synthesis gas having a relative speed of 50 to 100 m / s, in particular with a relative speed between the two passages of 60 to 80 m / s.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
EP14183316.0A 2014-09-03 2014-09-03 Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz Withdrawn EP2993406A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP14183316.0A EP2993406A1 (fr) 2014-09-03 2014-09-03 Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP14183316.0A EP2993406A1 (fr) 2014-09-03 2014-09-03 Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz

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EP2993406A1 true EP2993406A1 (fr) 2016-03-09

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EP14183316.0A Withdrawn EP2993406A1 (fr) 2014-09-03 2014-09-03 Procédé destiné au fonctionnement d'une turbine à gaz et d'un brûleur pour une turbine à gaz

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2107312A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Chambre de combustion pilote dans un brûleur
WO2011157458A1 (fr) 2010-06-18 2011-12-22 Siemens Aktiengesellschaft Brûleur de turbine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2107312A1 (fr) * 2008-04-01 2009-10-07 Siemens Aktiengesellschaft Chambre de combustion pilote dans un brûleur
WO2011157458A1 (fr) 2010-06-18 2011-12-22 Siemens Aktiengesellschaft Brûleur de turbine

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11156164B2 (en) 2019-05-21 2021-10-26 General Electric Company System and method for high frequency accoustic dampers with caps
US11174792B2 (en) 2019-05-21 2021-11-16 General Electric Company System and method for high frequency acoustic dampers with baffles

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