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EP2522909B1 - Gas turbine with burner and method for regulating a gas turbine with such a burner - Google Patents

Gas turbine with burner and method for regulating a gas turbine with such a burner Download PDF

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Publication number
EP2522909B1
EP2522909B1 EP11165818.3A EP11165818A EP2522909B1 EP 2522909 B1 EP2522909 B1 EP 2522909B1 EP 11165818 A EP11165818 A EP 11165818A EP 2522909 B1 EP2522909 B1 EP 2522909B1
Authority
EP
European Patent Office
Prior art keywords
combustion chamber
burner
optical sensor
insert
wall
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.)
Not-in-force
Application number
EP11165818.3A
Other languages
German (de)
French (fr)
Other versions
EP2522909A1 (en
Inventor
Andreas Böttcher
Olga Deiss
Sabine GRENDEL
Jens Kleinfeld
Andre Kluge
Tobias Krieger
Daniel Vogtmann
Marcus ZURHORST
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
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 EP11165818.3A priority Critical patent/EP2522909B1/en
Priority to RU2012119495/06A priority patent/RU2012119495A/en
Priority to CN2012101487241A priority patent/CN102777935A/en
Publication of EP2522909A1 publication Critical patent/EP2522909A1/en
Application granted granted Critical
Publication of EP2522909B1 publication Critical patent/EP2522909B1/en
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/02—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium
    • F23N5/08—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements
    • F23N5/082—Systems for controlling combustion using devices responsive to thermal changes or to thermal expansion of a medium using light-sensitive elements using electronic means
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/10—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to unwanted deposits on blades, in working-fluid conduits or the like
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N5/00—Systems for controlling combustion
    • F23N5/24—Preventing development of abnormal or undesired conditions, i.e. safety arrangements
    • F23N5/242—Preventing development of abnormal or undesired conditions, i.e. safety arrangements using electronic 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
    • 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
    • F23R3/60—Support structures; Attaching or mounting means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2229/00—Flame sensors
    • F23N2229/20—Camera viewing
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2231/00—Fail safe
    • F23N2231/10—Fail safe for component failures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23N—REGULATING OR CONTROLLING COMBUSTION
    • F23N2241/00—Applications
    • F23N2241/20—Gas turbines

Definitions

  • the invention relates to a burner gas turbine with at least one according to the preamble of claim 1, as from US 2006/0088793 A known.
  • the invention relates to a method for controlling a gas turbine with such a burner.
  • Combustion chambers are u. a. Component of gas turbines, which are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. The fuel is burned to burners in their downstream combustion chambers, wherein compressed air is supplied by an air compressor.
  • each burner can be assigned a separate combustion chamber, wherein the working medium flowing out of the combustion chambers can be brought together before or in the turbine unit.
  • the combustion chamber can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burner open into a common, usually annular combustion chamber.
  • the turbine unit has a number of rotatable turbine blades connected to the turbine shaft.
  • the turbine blades are arranged in a ring on the turbine shaft and thus form a number of blade rows.
  • the turbine comprises a number of fixed turbine vanes, which are also annular with the formation of rows of vanes on an inner casing the turbine are attached.
  • the turbine blades serve to drive the turbine shaft by momentum transfer from the working medium flowing through the turbine.
  • the turbine guide vanes serve to guide the flow of the working medium between two respective rows of rotor blades or rotor blade rings viewed in the flow direction of the working medium.
  • a successive pair of a turbine nozzle vane or vane row and a turbine blade ring or blade row downstream of the working medium in the flow direction form a turbine stage.
  • the combustion chamber wall is usually provided on its inner side with an existing of heat shield elements inner lining, which can be provided with particularly heat-resistant protective layers, and which are cooled by the actual combustion chamber wall through.
  • the invention is therefore based on the object of specifying an improved burner in a gas turbine. Another object is to specify a method for controlling a gas turbine with this burner.
  • the object related to the burner is achieved by the specification of a burner according to claim 1.
  • the object related to the method is achieved by the specification of a method according to claim 5.
  • the burner comprises a combustion chamber, a combustion chamber interior and a burner chamber wall and a number of downstream of the combustion chamber arranged turbine blades with a first row of turbine blades.
  • the burner comprises a burner insert which secures the burner to the combustion chamber wall.
  • the burner insert has a combustion chamber insert wall.
  • the combustion chamber insert wall is upstream of the combustion chamber interior.
  • the burner comprises at least one Zumischbrennstofflanze, which is supplied in the Zumischbrunstoff safely with Zumischbrennstoff and is formed during operation without Zumischbrennstoff as a fuel lance dummy.
  • at least one optical sensor is arranged on or adjacent to the combustion chamber insert wall during operation of the burner with admixed fuel.
  • At least one optical sensor disposed in the fuel lance dummy in operation without Zumischbrennstoff invention, at least one optical sensor disposed in the fuel lance dummy.
  • the optical sensor which is designed in particular as a camera, lies directly opposite the first turbine guide vane row.
  • the optical sensor provides by this arrangement images with which the first turbine vane row can be monitored. If the entire area of the first turbine vane row is to be monitored, only a small number of sensors are required for this purpose. Compared to the acoustic system, which can be influenced by other sounds, such a burner with an optical sensor is more reliable.
  • the state of the first turbine guide vane row can thus be optically monitored without the gas turbine resting.
  • the arrangement of the optical sensor in the fuel lance dummy has the additional advantage that the optical sensor is easy to install and remove.
  • the first turbine vane row can be monitored online with the optical sensor.
  • the gas turbine can be shut down in time if the condition of the blades is critical or, for example, foreign bodies are located immediately before the first row of turbine blades.
  • At least two burners are provided, which are arranged in the circumferential direction of a combustion chamber, wherein each burner comprises a burner insert, which attaches each of the burners to the combustion chamber wall, wherein each burner insert has a combustion chamber wall, and wherein the at least two combustion chamber insert walls also in the circumferential direction of the combustion chamber while leaving a gap adjacent to each other and with the optical sensor disposed in the gap between the combustor liner walls.
  • the combustion liner wall adjoins the combustion chamber wall leaving a gap.
  • the optical sensor is disposed in the gap between the combustor liner wall and the combustion chamber wall. In these arrangements, the sensor is located directly opposite the first row of turbine blades and is also particularly easy to attach.
  • images are returned from the optical sensor and foreign objects are automatically detected in the images returned from the optical sensor by means of suitable software.
  • a warning is issued and the gas turbine is brought to a standstill.
  • FIG. 1 A section of a combustion chamber is in FIG. 1 shown in a sectional view.
  • a burner 1 a burner insert 3, which annularly surrounds the burner 1, and to recognize a part of the combustion chamber wall 5.
  • the combustion chamber is arranged in a Brennschplenum 4 and extends annularly around a turbine shaft (not shown).
  • the burner 1 is inserted into a receptacle of the burner insert 3.
  • the burner insert 3 adjoins the combustion chamber wall 5 and closes the combustion chamber from the front side.
  • the burner insert 3 comprises a carrier, which is designed as a grooved ring 7.
  • a burner insert wall 9 which at the same time represents the end wall of the combustion chamber surrounding the burner 1.
  • the front side of the combustion chamber basically consists only of combustion chamber insert walls 9.
  • the burner wall 27 surrounding the burner opening 33 can be seen.
  • a separate burner insert 3 is present for each burner 1.
  • the burner insert walls 9 of adjacent burner inserts 3 adjoin in the circumferential direction while leaving a gap 20 (FIG. FIG. 2 ) to each other.
  • the combustion chamber insert walls 9 also adjoin the combustion chamber wall 5 while leaving a gap 30. Both in the gap 30 and in the gap 20 (FIG. FIG. 2 ) seals (not shown) may be arranged.
  • the burner 1 has a Zumischbrenner with Zumischbrennstof Lanze 23.
  • the burner 1 can be operated with Zumischbrennstoff or without Zumischbrennstoff.
  • the Zumischbrenner is operated with liquid fuel, such as fuel oil. If the burner 1 is operated without liquid fuel, the Zumischbrennstof Lanze 23 is replaced with a dummy fuel dummy (not shown).
  • the combustion chamber wall 5 is provided on its inside with a protective layer of heat shield elements (not shown).
  • FIG. 2 shows the arrangement of an optical sensor according to the invention, which is designed in particular as a security camera 22, in the gap 20 between two combustion chamber insert walls 3.
  • the surveillance camera 22 may also be disposed adjacent to or in other areas of the combustion chamber insert walls 3.
  • the radially outer combustion chamber wall 5 A and the radially inner combustion chamber wall 5 B can be seen, which connect the combustion chamber insert wall 9 with the combustion chamber wall 5.
  • at least two burners 1 during operation of the burner 1 ( FIG. 1 ) with liquid fuel at least one monitoring camera 22 in the gap 20 between the combustion chamber insert walls 3 is arranged.
  • the camera 22 lies directly opposite the first turbine guide vane row (not shown) and thus can overlook as much space as possible.
  • the surveillance camera 22 provides camera images that monitor the area in front of the first turbine nozzle row (not shown).
  • the complete area of the first turbine vane row (not shown) can thus be monitored by a small number of cameras 22, which are arranged in the gap 20 between the circumferentially arranged combustion chamber insert walls 9.
  • the camera 22 may also be disposed in the gap 30 between the combustor liner wall 3 and the radially outer combustion chamber wall 5a and the radially inner combustion chamber wall 5B, respectively.
  • At least one monitoring camera 22 is additionally or alternatively arranged in the Zumischbrennstofflanzengetrappe (not shown), so that here the surveillance camera 22 is installed directly in the burner 1.
  • the monitoring camera 22 is easily installable and removable from outside the combustion chamber (not shown).
  • the surveillance camera 22 returns images that are analyzed with appropriate software and automatically detects foreign objects. At a predetermined size of the foreign body will issue a warning and then brought the gas turbine to a standstill and thus regulated the gas turbine.
  • the status of the first turbine nozzle row (not shown) is monitored online with the returned images.
  • combustion chamber can also be designed as an approximately cylindrical combustion chamber with at least one burner and at least one burner insert on the end face of the cylinder.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Control Of Combustion (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Testing Of Engines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Description

Die Erfindung betrifft eine Brenner Gasturbine mit mindestens einem nach dem Oberbegriff des Anspruchs 1, wie aus der US 2006/0088793 A bekannt. Zudem betrifft die Erfindung ein Verfahren zur Regelung einer Gasturbine mit einem solchen Brenner.The invention relates to a burner gas turbine with at least one according to the preamble of claim 1, as from US 2006/0088793 A known. In addition, the invention relates to a method for controlling a gas turbine with such a burner.

Brennkammern sind u. a. Bestandteil von Gasturbinen, die in vielen Bereichen zum Antrieb von Generatoren oder von Arbeitsmaschinen eingesetzt werden. Dabei wird der Energieinhalt eines Brennstoffs zur Erzeugung einer Rotationsbewegung einer Turbinenwelle genutzt. Der Brennstoff wird dazu von Brennern in den ihnen nachgeschalteten Brennkammern verbrannt, wobei von einem Luftverdichter verdichtete Luft zugeführt wird.Combustion chambers are u. a. Component of gas turbines, which are used in many areas to drive generators or work machines. In this case, the energy content of a fuel is used to generate a rotational movement of a turbine shaft. The fuel is burned to burners in their downstream combustion chambers, wherein compressed air is supplied by an air compressor.

Dabei kann jedem Brenner eine separate Brennkammer zugeordnet sein, wobei das aus den Brennkammern abströmende Arbeitsmedium vor oder in der Turbineneinheit zusammengeführt sein kann. Alternativ kann die Brennkammer aber auch in einer so genannten Ringbrennkammer-Bauweise ausgeführt sein, bei der eine Mehrzahl, insbesondere alle, der Brenner in eine gemeinsame, üblicherweise ringförmige Brennkammer münden.In this case, each burner can be assigned a separate combustion chamber, wherein the working medium flowing out of the combustion chambers can be brought together before or in the turbine unit. Alternatively, however, the combustion chamber can also be designed in a so-called annular combustion chamber design, in which a plurality, in particular all, of the burner open into a common, usually annular combustion chamber.

Durch die Verbrennung des Brennstoffs wird ein unter hohem Druck stehendes Arbeitsmedium mit einer hohen Temperatur erzeugt. Dieses Arbeitsmedium entspannt sich in der den Brennkammern nachgeschalteten Turbineneinheit arbeitsleistend. Dazu weist die Turbineneinheit eine Anzahl von mit der Turbinenwelle verbundenen, rotierbaren Turbinenlaufschaufeln auf. Die Turbinenlaufschaufeln sind kranzförmig an der Turbinenwelle angeordnet und bilden somit eine Anzahl von Laufschaufelreihen. Weiterhin umfasst die Turbine eine Anzahl von feststehenden Turbinenleitschaufeln, die ebenfalls kranzförmig unter der Bildung von Leitschaufelreihen an einem Innengehäuse der Turbine befestigt sind. Die Turbinenlaufschaufeln dienen dabei zum Antrieb der Turbinenwelle durch Impulsübertrag vom die Turbine durchströmenden Arbeitsmedium. Die Turbinenleitschaufeln dienen hingegen zur Strömungsführung des Arbeitsmediums zwischen jeweils zwei in Strömungsrichtung des Arbeitsmediums gesehen aufeinanderfolgenden Laufschaufelreihen oder Laufschaufelkränzen. Ein aufeinanderfolgendes Paar aus einem Kranz von Turbinenleitschaufeln oder einer Leitschaufelreihe und aus einem in Strömungsrichtung des Arbeitsmediums nachgeschalteten Kranz von Turbinenlaufschaufeln oder einer Laufschaufelreihe bilden dabei eine Turbinenstufe.The combustion of the fuel produces a high pressure working fluid at a high temperature. This working fluid expands in the combustion chambers downstream turbine unit work. For this purpose, the turbine unit has a number of rotatable turbine blades connected to the turbine shaft. The turbine blades are arranged in a ring on the turbine shaft and thus form a number of blade rows. Furthermore, the turbine comprises a number of fixed turbine vanes, which are also annular with the formation of rows of vanes on an inner casing the turbine are attached. The turbine blades serve to drive the turbine shaft by momentum transfer from the working medium flowing through the turbine. By contrast, the turbine guide vanes serve to guide the flow of the working medium between two respective rows of rotor blades or rotor blade rings viewed in the flow direction of the working medium. A successive pair of a turbine nozzle vane or vane row and a turbine blade ring or blade row downstream of the working medium in the flow direction form a turbine stage.

Bei der Auslegung derartiger Gasturbinen ist zusätzlich zur erreichbaren Leistung üblicherweise ein besonders hoher Wirkungsgrad ein Auslegungsziel. Eine Erhöhung des Wirkungsgrades lässt sich dabei aus thermodynamischen Gründen grundsätzlich durch eine Erhöhung der Austrittstemperatur erreichen, mit der das Arbeitsmedium von der Brennkammer ab- und in die Turbineneinheit einströmt. Daher werden Temperaturen von etwa 1220 °C bis 1500 °C für derartige Gasturbinen angestrebt und auch erreicht.In the design of such gas turbines in addition to the achievable power usually a particularly high efficiency is a design target. An increase in the efficiency can be achieved for thermodynamic reasons basically by increasing the outlet temperature at which the working fluid from the combustion chamber and flows into the turbine unit. Therefore, temperatures of about 1220 ° C to 1500 ° C are sought for such gas turbines and also achieved.

Bei derartig hohen Temperaturen des Arbeitsmediums sind jedoch die diesem Medium ausgesetzten Komponenten und Bauteile hohen thermischen Belastungen ausgesetzt. Um dennoch bei hoher Zuverlässigkeit eine vergleichsweise lange Lebensdauer der betroffenen Komponenten zu gewährleisten, ist üblicherweise eine Ausgestaltung mit besonders hitzebeständigen Materialien und eine Kühlung der betroffenen Komponenten, insbesondere der Brennkammer, nötig.At such high temperatures of the working medium, however, exposed to this medium components and components are exposed to high thermal loads. In order nevertheless to ensure a comparatively long service life of the affected components with high reliability, a design with particularly heat-resistant materials and cooling of the affected components, in particular the combustion chamber, is usually necessary.

Die Brennkammerwand ist dazu in der Regel auf ihrer Innenseite mit einer aus Hitzeschildelementen bestehenden Innenauskleidung versehen, die mit besonders hitzebeständigen Schutzschichten versehen werden können, und die durch die eigentliche Brennkammerwand hindurch gekühlt werden.The combustion chamber wall is usually provided on its inner side with an existing of heat shield elements inner lining, which can be provided with particularly heat-resistant protective layers, and which are cooled by the actual combustion chamber wall through.

Durch die hohe thermische und dynamische Beanspruchung der Hitzeschildelemente in der Brennkammer kann es im Betrieb in seltenen Fällen durch Rissbildung im Grundmaterial zum Herausfallen von Hitzeschildelementteilen oder von gesamten Hitzeschildelementen kommen. In diesem Fall ist das Gehäuse nicht mehr gegen die hohen Temperaturen, die in der Brennkammer herrschen, geschützt. Dadurch kommt es zu Verzunderungen. Zudem können die Hitzeschildelementteile, wenn sie nach Herausbrechen vor dem Turbineneintritt liegen, massiv die dahinterliegenden Turbinenschaufeln beschädigen und einen schweren Gasturbinenschaden verursachen. Die größte Gefahr für die Turbine besteht, wenn Bruchstücke der Hitzeschildelemente in der Brennkammer direkt vor dem Turbineneintritt, also vor oder in den Turbinenleitschaufeln, liegen. Die Turbinenlaufschaufeln werden dann durch die Abschirmung gegen die Strömung unterschiedlich thermisch belastet. Daraus folgt eine Anregung der Schaufeln, die im schlimmsten Fall zur Resonanzkatastrophe durch Anregung in Eigenfrequenz führt. In der Regel vergehen im Falle eines Hitzeschildverlustes zwischen dem sich Lösen eines Hitzeschildelementes an der Brennkammerwand und dem ersten Abreißen von Turbinenlaufschaufeln, welche durch Turbulenzen durch verklemmte Hitzeschildelemente ausgelöst werden, einige Minuten. Bei einer Beschädigung der Turbineneinheit fallen neben den Reparaturkosten insbesondere auch Produktionsausfallskosten der Gasturbine an, so dass insgesamt sehr hohe Gesamtkosten anfallen können. Brenner nach dem Stand der Technik erfassen Hitzeschildverluste durch Beschleunigungssensoren, welche am Brennkammergehäuse befestigt sind. Diese erfassen die charakteristische Schwingung eines Aufschlags eines Hitzeschildes in der Brennkammer und lösen nach Abgleich mit weiteren Parametern eine Warnung aus. Dieses System ist jedoch sehr störanfällig.Due to the high thermal and dynamic stress of the heat shield elements in the combustion chamber can occur in operation in rare cases by cracking in the base material from falling out of heat shield element parts or entire heat shield elements. In this case, the housing is no longer protected against the high temperatures prevailing in the combustion chamber. This leads to scaling. In addition, the heat shield element parts, if they lie after breaking out of the turbine entrance, massively damage the underlying turbine blades and cause a serious gas turbine damage. The greatest danger to the turbine exists if fragments of the heat shield elements in the combustion chamber are located directly in front of the turbine inlet, ie in front of or in the turbine guide vanes. The turbine blades are then thermally stressed differently by the shield against the flow. This results in an excitation of the blades, which leads in the worst case to the resonance catastrophe by excitation in natural frequency. Typically, in the event of heat shield loss, a few minutes passes between the dissolution of a heat shield element on the combustion chamber wall and the first tearing off of turbine blades, which are triggered by turbulence from jammed heat shield elements. In case of damage to the turbine unit fall in addition to the repair costs in particular also production downtime costs of the gas turbine, so that in total can incur very high overall costs. Prior art burners detect heat shield losses by acceleration sensors attached to the combustor housing. These detect the characteristic oscillation of an impact of a heat shield in the combustion chamber and trigger a warning after comparison with other parameters. However, this system is very prone to failure.

Der Erfindung liegt daher die Aufgabe zugrunde, einen verbesserten Brenner in einer Gasturbine anzugeben. Eine weitere Aufgabe ist die Angabe eines Verfahrens zur Regelung einer Gasturbine mit diesem Brenner.The invention is therefore based on the object of specifying an improved burner in a gas turbine. Another object is to specify a method for controlling a gas turbine with this burner.

Die auf den Brenner bezogene Aufgabe wird gelöst durch die Angabe eines Brenners nach Anspruch 1. Die auf das Verfahren bezogene Aufgabe wird gelöst durch die Angabe eines Verfahrens nach Anspruch 5.The object related to the burner is achieved by the specification of a burner according to claim 1. The object related to the method is achieved by the specification of a method according to claim 5.

Dabei umfasst der Brenner eine Brennkammer, einem Brennkammerinneren und eine Brennerkammerwand sowie eine Reihe von stromabwärts der Brennkammer angeordnete Turbinenschaufeln mit einer ersten Turbinenleitschaufelreihe. Zudem umfasst der Brenner einen Brennereinsatz, welcher den Brenner mit der Brennkammerwand befestigt. Der Brennereinsatz weist eine Brennkammereinsatzwand auf. Die Brennkammereinsatzwand ist zum Brennkammerinneren hin vorgelagert. Der Brenner umfasst zumindest eine Zumischbrennstofflanze, welche im Zumischbrennstoffbetrieb mit Zumischbrennstoff versorgt wird und im Betrieb ohne Zumischbrennstoff als Brennstofflanzenattrappe ausgebildet ist. Erfindungsgemäß ist bei einem Betrieb des Brenners mit Zumischbrennstoff zumindest ein optischer Sensor auf oder an der Brennkammereinsatzwand angrenzend angeordnet. Zusätzlich oder alternativ ist im Betrieb ohne Zumischbrennstoff erfindungsgemäß zumindest ein optischer Sensor in der Brennstofflanzenattrappe angeordnet. Der optische Sensor, der insbesondere als Kamera ausgebildet ist, liegt direkt gegenüber der ersten Turbinenleitschaufelreihe. Somit kann der optische Sensor einen möglichst großen Bereich der ersten Turbinenleitschaufelreihe und den unmittelbar davor liegenden Bereich überwachen. Der optische Sensor liefert durch diese Anordnung Bilder, mit denen die erste Turbinenleitschaufelreihe überwachbar ist. Soll der gesamte Bereich der ersten Turbinenleitschaufelreihe überwacht werden, ist hierfür nur eine geringe Anzahl von Sensoren notwendig. Im Vergleich zum akustischen System, welches durch andere Geräusche beeinflusst werden kann, ist ein solcher Brenner mit einem optischen Sensor zuverlässiger. Auch kann somit insbesondere der Zustand der ersten Turbinenleitschaufelreihe optisch überwacht werden, ohne dass die Gasturbine stillsteht. Die Anordnung des optischen Sensors in der Brennstofflanzenattrappe hat zusätzlich den Vorteil, dass der optische Sensor leicht ein- sowie ausbaubar ist.In this case, the burner comprises a combustion chamber, a combustion chamber interior and a burner chamber wall and a number of downstream of the combustion chamber arranged turbine blades with a first row of turbine blades. In addition, the burner comprises a burner insert which secures the burner to the combustion chamber wall. The burner insert has a combustion chamber insert wall. The combustion chamber insert wall is upstream of the combustion chamber interior. The burner comprises at least one Zumischbrennstofflanze, which is supplied in the Zumischbrunstoffbetrieb with Zumischbrennstoff and is formed during operation without Zumischbrennstoff as a fuel lance dummy. According to the invention, at least one optical sensor is arranged on or adjacent to the combustion chamber insert wall during operation of the burner with admixed fuel. Additionally or alternatively, in operation without Zumischbrennstoff invention, at least one optical sensor disposed in the fuel lance dummy. The optical sensor, which is designed in particular as a camera, lies directly opposite the first turbine guide vane row. Thus, the optical sensor can monitor the largest possible area of the first row of turbine blades and the area immediately ahead. The optical sensor provides by this arrangement images with which the first turbine vane row can be monitored. If the entire area of the first turbine vane row is to be monitored, only a small number of sensors are required for this purpose. Compared to the acoustic system, which can be influenced by other sounds, such a burner with an optical sensor is more reliable. Thus, in particular, the state of the first turbine guide vane row can thus be optically monitored without the gas turbine resting. The arrangement of the optical sensor in the fuel lance dummy has the additional advantage that the optical sensor is easy to install and remove.

Bevorzugt ist die erste Turbinenleitschaufelreihe mit dem optischen Sensor online überwachbar. Somit kann die Gasturbine rechtzeitig abgeschaltet werden, wenn der Zustand der Schaufeln kritisch ist oder sich beispielsweise Fremdkörper unmittelbar vor der ersten Turbinenleitschaufelreihe befinden.Preferably, the first turbine vane row can be monitored online with the optical sensor. Thus, the gas turbine can be shut down in time if the condition of the blades is critical or, for example, foreign bodies are located immediately before the first row of turbine blades.

Bevorzugt sind zumindest zwei Brenner vorgesehen, welche in Umfangsrichtung einer Brennkammer angeordnet sind, wobei jeder Brenner einen Brennereinsatz, welcher jeden der Brenner mit der Brennkammerwand befestigt, umfasst, wobei jeder Brennereinsatz eine Brennkammereinsatzwand aufweist, und wobei die zumindest zwei Brennkammereinsatzwände zudem in Umfangsrichtung der Brennkammer unter Belassung eines Spalts aneinandergrenzen und wobei der optische Sensor im Spalt zwischen den Brennkammereinsatzwänden angeordnet ist.Preferably, at least two burners are provided, which are arranged in the circumferential direction of a combustion chamber, wherein each burner comprises a burner insert, which attaches each of the burners to the combustion chamber wall, wherein each burner insert has a combustion chamber wall, and wherein the at least two combustion chamber insert walls also in the circumferential direction of the combustion chamber while leaving a gap adjacent to each other and with the optical sensor disposed in the gap between the combustor liner walls.

Die Brennkammereinsatzwand grenzt an die Brennkammerwand unter Belassung einer Lücke an. Alternativ oder zusätzlich ist der optische Sensor in der Lücke zwischen der Brennkammereinsatzwand und der Brennkammerwand angeordnet. In diesen Anordnungen liegt der Sensor direkt gegenüber der ersten Turbineleitschaufelreihe und ist zudem besonders einfach zu befestigen.The combustion liner wall adjoins the combustion chamber wall leaving a gap. Alternatively or additionally, the optical sensor is disposed in the gap between the combustor liner wall and the combustion chamber wall. In these arrangements, the sensor is located directly opposite the first row of turbine blades and is also particularly easy to attach.

Beim Verfahren zur Regelung einer Gasturbine mit einem Brenner werden von dem optischen Sensor Bilder zurückliefert und in denen von dem optischen Sensor zurückgelieferten Bildern mittels einer geeigneten Software automatisch Fremdkörper erkannt. Bei einer vorab festgelegten Größe des Fremdkörpers wird eine Warnung ausgegeben und die Gasturbine zum Stillstand gebracht.In the method for controlling a gas turbine with a burner, images are returned from the optical sensor and foreign objects are automatically detected in the images returned from the optical sensor by means of suitable software. At a predetermined size of the foreign body, a warning is issued and the gas turbine is brought to a standstill.

Somit können Maschinenschäden wie Schaufelabriss oder Verzunderung der Tragstruktur verhindert werden.Thus, machine damage such as blade separation or scaling of the support structure can be prevented.

Weitere Merkmale, Eigenschaften und Vorteile der vorliegenden Erfindung ergeben sich aus der nachfolgenden Beschreibung unter Bezugnahme auf die beiliegenden Figuren 1-2.

FIG 1
zeigt einen Ausschnitt aus einer Brennkammer nach dem Stand der Technik mit einem Brenner und einem Brennereinsatz.
FIG 2
zeigt einen erfindungsgemäßen Brenner mit optischer Kamera.
Other features, characteristics and advantages of the present invention will become apparent from the following description with reference to the accompanying drawings Figures 1-2 ,
FIG. 1
shows a section of a combustion chamber according to the prior art with a burner and a burner insert.
FIG. 2
shows a burner according to the invention with optical camera.

Ein Ausschnitt aus einer Brennkammer ist in FIG 1 in einer Schnittansicht gezeigt. Es sind ein Brenner 1, ein Brennereinsatz 3, welcher den Brenner 1 ringförmig umgibt, und ein Teil der Brennkammerwand 5 zu erkennen. Die Brennkammer ist in einem Brennkammerplenum 4 angeordnet und erstreckt sich ringförmig um eine Turbinenwelle (nicht dargestellt). Der Brenner 1 ist in eine Aufnahme des Brennereinsatzes 3 eingesetzt. Der Brennereinsatz 3 grenzt an die Brennkammerwand 5 an und schließt die Brennkammer stirnseitig ab.A section of a combustion chamber is in FIG. 1 shown in a sectional view. There are a burner 1, a burner insert 3, which annularly surrounds the burner 1, and to recognize a part of the combustion chamber wall 5. The combustion chamber is arranged in a Brennkammerplenum 4 and extends annularly around a turbine shaft (not shown). The burner 1 is inserted into a receptacle of the burner insert 3. The burner insert 3 adjoins the combustion chamber wall 5 and closes the combustion chamber from the front side.

Der Brennereinsatz 3 umfasst einen Träger, der als Nutring 7 ausgebildet ist. Dem Nutring 7 zu einem Brennkammerinneren 2 hin vorgelagert ist eine Brennereinsatzwand 9 vorhanden, welche gleichzeitig die den Brenner 1 umgebende Abschlusswand der Brennkammer darstellt. Die Stirnseite der Brennkammer besteht quasi somit lediglich aus Brennkammereinsatzwänden 9. Im Zentrum des Brennereinsatzes 3 ist die die Brenneröffnung 33 umgebende Brennerwand 27 zu erkennen. Im vorliegenden Ausführungsbeispiel ist für jeden Brenner 1 ein eigener Brennereinsatz 3 vorhanden. Die Brennereinsatzwände 9 benachbarter Brennereinsätze 3 grenzen in Umfangsrichtung unter Belassung eines Spalts 20 (FIG 2) aneinander. Die Brennkammereinsatzwände 9 grenzen zudem an die Brennkammerwand 5 unter Belassung einer Lücke 30 an. Sowohl in der Lücke 30 als auch im Spalt 20 (FIG 2) können Dichtungen (nicht gezeigt) angeordnet sein.The burner insert 3 comprises a carrier, which is designed as a grooved ring 7. In front of the grooved ring 7 toward a combustion chamber interior 2, there is a burner insert wall 9, which at the same time represents the end wall of the combustion chamber surrounding the burner 1. Thus, the front side of the combustion chamber basically consists only of combustion chamber insert walls 9. In the center of the burner insert 3, the burner wall 27 surrounding the burner opening 33 can be seen. In the present embodiment, a separate burner insert 3 is present for each burner 1. The burner insert walls 9 of adjacent burner inserts 3 adjoin in the circumferential direction while leaving a gap 20 (FIG. FIG. 2 ) to each other. The combustion chamber insert walls 9 also adjoin the combustion chamber wall 5 while leaving a gap 30. Both in the gap 30 and in the gap 20 (FIG. FIG. 2 ) seals (not shown) may be arranged.

Der Brenner 1 weist einen Zumischbrenner mit Zumischbrennstofflanze 23 auf. Der Brenners 1 kann dabei mit Zumischbrennstoff oder ohne Zumischbrennstoff betrieben werden. Vorzugsweise wird der Zumischbrenner mit Flüssigbrennstoff, beispielsweise Heizöl betrieben. Wird der Brenner 1 ohne Flüssigbrennstoff betrieben, so wird die Zumischbrennstofflanze 23 gegen eine Brennstofflanzenattrappe (nicht gezeigt) ausgetauscht.The burner 1 has a Zumischbrenner with Zumischbrennstof Lanze 23. The burner 1 can be operated with Zumischbrennstoff or without Zumischbrennstoff. Preferably, the Zumischbrenner is operated with liquid fuel, such as fuel oil. If the burner 1 is operated without liquid fuel, the Zumischbrennstof Lanze 23 is replaced with a dummy fuel dummy (not shown).

Die Brennkammerwand 5 ist auf ihrer Innenseite mit einer Schutzschicht aus Hitzeschildelementen (nicht gezeigt) versehen.The combustion chamber wall 5 is provided on its inside with a protective layer of heat shield elements (not shown).

FIG 2 zeigt die Anordnung eines erfindungsgemäßen optischen Sensors, der insbesondere als Überwachungskamera 22 ausgebildet ist, im Spalt 20 zwischen zwei Brennkammereinsatzwänden 3. Die Überwachungskamera 22 kann jedoch auch auf oder in anderen Bereichen der Brennkammereinsatzwände 3 angrenzend angeordnet sein. In der FIG 2 sind zudem die radial äußere Brennkammerwand 5A und die radial innere Brennkammerwand 5B zu erkennen, die die Brennkammereinsatzwand 9 mit der Brennkammerwand 5 verbinden. Erfindungsgemäß ist nun bei zumindest zwei Brennern 1 (FIG 1) bei einem Betrieb des Brenners 1 (FIG 1) mit Flüssigbrennstoff zumindest eine Überwachungskamera 22 im Spalt 20 zwischen den Brennkammereinsatzwänden 3 angeordnet. Die Kamera 22 liegt durch eine solche Anordnung direkt gegenüber der ersten Turbinenleitschaufelreihe (nicht gezeigt) und kann somit möglichst viel Raum überblicken. Die Überwachungskamera 22 liefert Kamerabilder, mit denen der Bereich vor der ersten Turbinenleitschaufelreihe (nicht gezeigt) überwacht wird. Der komplette Bereich der ersten Turbinenleitschaufelreihe (nicht gezeigt) kann somit durch eine geringe Anzahl von Kameras 22, welche im Spalt 20 zwischen den in Umfangsrichtung angeordneten Brennkammereinsätzwänden 9 angeordnet sind, überwacht werden. Die Kamera 22 kann auch in der Lücke 30 zwischen der Brennkammereinsatzwand 3 und der radial äußeren Brennkammerwand 5a bzw. der radial inneren Brennkammerwand 5B angeordnet werden. FIG. 2 shows the arrangement of an optical sensor according to the invention, which is designed in particular as a security camera 22, in the gap 20 between two combustion chamber insert walls 3. However, the surveillance camera 22 may also be disposed adjacent to or in other areas of the combustion chamber insert walls 3. In the FIG. 2 In addition, the radially outer combustion chamber wall 5 A and the radially inner combustion chamber wall 5 B can be seen, which connect the combustion chamber insert wall 9 with the combustion chamber wall 5. According to the invention, at least two burners 1 (FIG. FIG. 1 ) during operation of the burner 1 ( FIG. 1 ) with liquid fuel at least one monitoring camera 22 in the gap 20 between the combustion chamber insert walls 3 is arranged. By such an arrangement, the camera 22 lies directly opposite the first turbine guide vane row (not shown) and thus can overlook as much space as possible. The surveillance camera 22 provides camera images that monitor the area in front of the first turbine nozzle row (not shown). The complete area of the first turbine vane row (not shown) can thus be monitored by a small number of cameras 22, which are arranged in the gap 20 between the circumferentially arranged combustion chamber insert walls 9. The camera 22 may also be disposed in the gap 30 between the combustor liner wall 3 and the radially outer combustion chamber wall 5a and the radially inner combustion chamber wall 5B, respectively.

Im Betrieb ohne Flüssigbrennstoff ist zumindest eine Überwachungskamera 22 zusätzlich oder alternativ in der Zumischbrennstofflanzenattrappe (nicht gezeigt) angeordnet, so dass hier die Überwachungskamera 22 direkt im Brenner 1 verbaut ist. In diesem Fall ist die Überwachungskamera 22 einfach von außerhalb der Brennkammer (nicht gezeigt) ein- und ausbaubar. Die Überwachungskamera 22 liefert Bilder zurück, die mit einer geeigneten Software analysiert wird und automatisch Fremdkörper erkennt. Bei einer vorab festgelegten Größe des Fremdkörpers wird eine Warnung ausgeben und anschließend die Gasturbine zum Stillstand gebracht und somit die Gasturbine geregelt. Zusätzlich wird mit den zurückgelieferten Bildern online der Zustand der ersten Turbinenleitschaufelreihe (nicht gezeigt) überwacht.In operation without liquid fuel at least one monitoring camera 22 is additionally or alternatively arranged in the Zumischbrennstofflanzengetrappe (not shown), so that here the surveillance camera 22 is installed directly in the burner 1. In this case, the monitoring camera 22 is easily installable and removable from outside the combustion chamber (not shown). The surveillance camera 22 returns images that are analyzed with appropriate software and automatically detects foreign objects. At a predetermined size of the foreign body will issue a warning and then brought the gas turbine to a standstill and thus regulated the gas turbine. In addition, the status of the first turbine nozzle row (not shown) is monitored online with the returned images.

Zwar wurde die Erfindung anhand einer Ringbrennkammer erläutert, jedoch kann die Brennkammer auch als in etwa zylindrische Brennkammer mit wenigstens einem Brenner und wenigstens einem Brennereinsatz an der Stirnseite des Zylinders ausgestaltet sein.Although the invention has been explained with reference to an annular combustion chamber, the combustion chamber can also be designed as an approximately cylindrical combustion chamber with at least one burner and at least one burner insert on the end face of the cylinder.

Claims (5)

  1. Gas turbine with at least one burner (1), with a combustion chamber, a combustion chamber internal space (2) and a combustion chamber wall (5) and a row of turbine blades, arranged downstream of the combustion chamber, with a first turbine guide vane row, wherein the burner (1) comprises a burner insert (3) which attaches the burner to the combustion chamber wall (5), wherein the burner insert (3) has a combustion chamber insert wall (9) and wherein the combustion chamber insert wall (9) is mounted upstream of the combustion chamber internal space (2), and wherein the burner (1) comprises at least one admixed fuel lance (23) which is supplied with admixed fuel during admixed fuel operation and which, in operation without admixed fuel, is formed as a dummy fuel lance,
    characterized in that
    when the burner (1) is operated with admixed fuel, at least one optical sensor (22) is arranged on or adjacent to the combustion chamber insert wall (9), and/or during operation without admixed fuel at least one optical sensor (22) is arranged in the dummy fuel lance,
    such that, by virtue of the arrangement of the optical sensor, the first turbine guide vane row can be monitored.
  2. Gas turbine according to Claim 1,
    characterized in that the first turbine guide vane row can be monitored online by means of the optical sensor.
  3. Gas turbine according to either of Claims 1 and 2, characterized in that at least two burners (1) are provided, arranged in the circumferential direction of a combustion chamber, wherein each burner (1) comprises a burner insert (3) which attaches each of the burners (1) to the combustion chamber wall (5), wherein each burner insert (3) has a combustion chamber insert wall (9) and wherein the at least two combustion chamber insert walls (9) are adjacent to each other in the circumferential direction of the combustion chamber, leaving a gap (20) between them, and wherein the optical sensor is arranged in the gap (20).
  4. Gas turbine according to one of Claims 1 to 3, characterized in that the combustion chamber insert wall (9) adjoins the combustion chamber wall (5) leaving an interstice (30), and wherein the optical sensor is arranged in the interstice (30).
  5. Method for controlling the gas turbine with at least one burner and an optical sensor according to one of the preceding claims,
    characterized in that the optical sensor returns pictures and foreign bodies can be recognised automatically, by means of suitable software, in the pictures returned by the optical sensor and, in the event of the foreign body being a preestablished size, a warning is emitted and the gas turbine is brought to a halt.
EP11165818.3A 2011-05-12 2011-05-12 Gas turbine with burner and method for regulating a gas turbine with such a burner Not-in-force EP2522909B1 (en)

Priority Applications (3)

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EP11165818.3A EP2522909B1 (en) 2011-05-12 2011-05-12 Gas turbine with burner and method for regulating a gas turbine with such a burner
RU2012119495/06A RU2012119495A (en) 2011-05-12 2012-05-11 BURNER AND METHOD FOR REGULATING A GAS TURBINE WITH THE INDICATED BURNER
CN2012101487241A CN102777935A (en) 2011-05-12 2012-05-14 Burner and method for regulating a gas turbine with such a burner

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EP2522909B1 true EP2522909B1 (en) 2015-04-08

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DE102019217983A1 (en) 2019-11-21 2021-05-27 Siemens Aktiengesellschaft Burner insert, process for its production and use of such a burner insert

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NL1018974C2 (en) * 2001-09-18 2003-04-04 Kema Nv Method and device for examining the elongation of elongated bodies.
US20060088793A1 (en) * 2004-10-22 2006-04-27 Siemens Westinghouse Power Corporation Optical viewing system for monitoring a wide angle area of interest exposed to high temperature
EP1767855A1 (en) * 2005-09-27 2007-03-28 Siemens Aktiengesellschaft Combustion Chamber and Gas Turbine Plant
US7432505B2 (en) * 2006-05-04 2008-10-07 Siemens Power Generation, Inc. Infrared-based method and apparatus for online detection of cracks in steam turbine components
EP2040062A1 (en) * 2007-09-18 2009-03-25 Siemens Aktiengesellschaft Inspection of high temperature chambers
US7853433B2 (en) * 2008-09-24 2010-12-14 Siemens Energy, Inc. Combustion anomaly detection via wavelet analysis of dynamic sensor signals

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