CN102777935A - Burner and method for regulating a gas turbine with such a burner - Google Patents
Burner and method for regulating a gas turbine with such a burner Download PDFInfo
- Publication number
- CN102777935A CN102777935A CN2012101487241A CN201210148724A CN102777935A CN 102777935 A CN102777935 A CN 102777935A CN 2012101487241 A CN2012101487241 A CN 2012101487241A CN 201210148724 A CN201210148724 A CN 201210148724A CN 102777935 A CN102777935 A CN 102777935A
- Authority
- CN
- China
- Prior art keywords
- burner
- combustion chamber
- fuel
- gas turbine
- optical pickocff
- 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.)
- Pending
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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
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- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
- Control Of Combustion (AREA)
- Combustion Of Fluid Fuel (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to a burner (1) of a gas turbine, comprising a combustion chamber, a combustion chamber interior (2), a combustion chamber wall (5) and a turbine blade row arranged at the downstream of the combustion chamber. The turbine blade row possesses a first turbine guiding blade row, and the burner comprises a burner installing member (3) for fixing the burner and the combustion chamber wall. The burner installing member (3) possesses a combustion chamber spile located in the front towards the interior of the combustion chamber. The burner comprises at least one mixed fuel lance supplying mixed fuel when the mixed fuel works and formed as a fuel lance blank at an operation without the fuel. An optical sensor is designed as a monitoring camera (22), arranged adjacent to the insert wall during operation of the burner with the mixed fuel and arranged in the lance blank during operation of the burner without the fuel such that a turbine guide vane row is monitored with an arrangement of the sensor. An independent claim is also included for a method for controlling a gas turbine with such a burner.
Description
Technical field
The present invention relates to a kind of burner that is used for gas turbine.The invention still further relates to the method for this burner control of a kind of usefulness gas turbine in addition.
Background technology
The combustion chamber is the main part of gas turbine, and gas turbine is used to drive generator or machine for doing work in a lot of fields.Utilize the energy content of fuel to produce rotatablely moving of turbine wheel shaft here.For this reason, fuel is being connected the combustion chamber internal combustion in its downstream by burner, meanwhile imports through air compressed from compressor.
Can be for each burner sets independent combustion chamber, wherein, the working medium that flows out from the combustion chamber can accumulate in before the turbine part or within.But also can be different with it, the combustion chamber can be designed as the version of so-called toroidal combustion chamber, and at this moment, a plurality of, especially whole burners import in the common combustion chamber that is generally annular.
Fuel combustion produces the working medium of HTHP.The acting of in the turbine part that is connected the downstream, combustion chamber, expanding of this working medium.For this reason, turbine part has some to be connected with turbine wheel shaft and rotatable moving turbine blade.The moving turbine blade ring-type is laid on the turbine wheel shaft and thereby formation a few thing blade row.In addition, turbine also comprises the turborotor that some are fixing, and their same ring-types are fixed on the interior casing of turbine, constitutes guide vane row.Moving turbine blade flows through the pulse driving turbine wheel shaft of the working medium of turbine here through transmission.Turborotor then is used for per two flow guide that flow to working medium between the working-blade row see in succession or the working-blade ring along working medium.In this case, along in succession a pair of that working medium flows to that the moving turbine blade ring seeing to be linked in sequence or working-blade row form, constitute a stage of turbine by a turborotor ring or guide vane row and one.
In the design parameter of this gas turbine, except the power that can reach, also having a design object usually is extra high efficient.In this respect, based on the thermokinetics principle, can reach through high outlet temperature on the high efficiency principle, working medium flows out from the combustion chamber and the inflow turbine part with this outlet temperature.Therefore this gas turbine is made every effort to and has been reached about 1220 ℃ to 1500 ℃ temperature.
Yet when so high working medium temperature, the parts and the member that meet with this working medium are subjected to high thermic load.In order to guarantee still that however related parts have long service life when reliability is high, related parts, especially the combustion chamber is necessary to adopt heat-resisting especially material usually and cools off.
The common side within it of chamber wall is provided with the liner that the heat shielding element is formed for this reason, and they can provide heat-resisting especially protective layer, and they cool off through chamber wall originally.
Because internal heat shield element high thermic load and living load in combustion chamber possibly cause portion of hot screen member or whole heat shielding element to come off because form crackle in the stock under rare situation in the work.Shell is no longer defendd the high temperature of existence in the combustion chamber in this case.Cause scaling thus.Come off when occurring in before the turbine inlet when the portion of hot screen member is cracked in addition, can destroy rambunctiously the turbo blade of they back with cause the badly damaged of gas turbine.The greatest danger of turbine appears at, before the fragment of combustion chamber internal heat shield element directly is in turbine inlet, that is before turborotor or in.This moment is because blocks flow makes moving turbine blade receive different thermic loads.Consequently encourage blade, under serious situation because the excitation intrinsic frequency causes the calamity of blade resonance.Under the situation of heat shielding disappearance, heat shielding element on the chamber wall come off and moving turbine blade because the stuck initiation turbulent flow of heat shielding element causes for the first time between the fracture, generally to pass through a few minutes.When turbine part damages, except the cost of repairs, especially also produce gas turbine simultaneously and produce outage cost, thereby can cause very high total cost on the whole.Burner by prior art detects the heat shielding disappearance through the acceleration transducer that is fixed on the combustor outer casing.They detect the vibration of the characteristic of internal heat shield collision in the combustion chamber, and after with other parametric calibrations, give the alarm.Yet this system easy break-down.
Summary of the invention
So the technical problem that the present invention will solve is that a kind of improved burner that is used for gas turbine is provided.Another technical problem of the present invention provides the method for this burner control of a kind of usefulness gas turbine.
The technical problem of relevant burner is able to solve through a kind of burner that is used for gas turbine.The technical problem that relates to method is able to solve through the method for described burner of a kind of usefulness and optical pickocff control gas turbine.
Here, the turbo blade row that burner comprises combustion chamber, inside, combustion chamber and chamber wall and is located at the downstream, combustion chamber, it has first turborotor row.In addition, burner also comprises the burner installed part of fixed combustion device and chamber wall.Burner installed part combuster plate.Inner direction is positioned at the front to the combustion chamber plate towards the combustion chamber.Burner comprises at least one fuel combination conduit, and it supplies with fuel combination when fuel combination is worked, and it is designed to fuel interception pipe (Brennstofflanzenattrape) when working without fuel combination.By the present invention, when burner is worked with fuel combination, on the plate of combustion chamber or near it, establish at least one optical pickocff.In addition or with it different, when burner is worked without fuel combination, in fuel interception pipe, establish at least one optical pickocff by the present invention.Especially the optical pickocff that is designed to video camera is directly mutually opposed with first turborotor row.Optical pickocff can be monitored first turborotor row's big as far as possible zone and directly in its region in front thus.Optical pickocff provides image through said configuration, can monitor first turborotor row by image.If should monitor first turborotor row's whole zone, then be this needs small number of sensors.Participant is compared by the sound system of other influence of noises, and this burner with optical pickocff is more reliable.Especially can also under gas turbine situation not out of service, detect first turborotor row's state optically thus.It is that optical pickocff can pack into and remove easily that optical pickocff is arranged on another advantage of bringing in the fuel interception pipe.
Preferably, first turborotor row can be by the optical pickocff on-line monitoring.Therefore in the hole or for example have foreign matter directly to be in first turborotor row when preceding when blade, can in time close gas turbine.
Preferably, establish at least two burners, they are circumferentially laid along the combustion chamber; Wherein, each burner comprises one with each burner and the fixing burner installed part of chamber wall, wherein; Each burner installed part combuster plate, and, said at least two combustion chamber plates along the combustion chamber circumferentially reserve under the situation in gap adjacent one another are; And here, optical sensor arrangement is in the gap.
The combustion chamber plate reserve under the situation in space adjacent with chamber wall.Different with it or in addition, in the space of optical sensor arrangement between combustion chamber plate and chamber wall.By said configuration, sensor is directly mutually opposed with first turborotor row, and can fix especially simply.
In method, image is provided and in the image that provides by optical pickocff, can discerns foreign matter automatically by the software that is suitable for by optical pickocff with burner control gas turbine.When the foreign matter of prior prescribed level, give the alarm and make gas turbine out of service.
Can prevent machine breakdown thus, such as leaf destruction or supporting structure scaling.
Description of drawings
By other characteristics of the present invention, character and advantage are provided in the explanation referring to accompanying drawing 1-2.
Fig. 1 representes to have by prior art a part of the combustion chamber of burner and burner installed part.
Fig. 2 representes to have by the present invention the burner of optical camera.
The specific embodiment
Fig. 1 representes a part of combustion chamber with cutaway view.Center on the burner installed part 3 and the partial combustion locular wall 5 of burner 1 by the visible burner 1 of figure, annular.The combustion chamber is arranged in the combustion chamber inflatable chamber 4 and circlewise extends around the turbine wheel shaft (not shown).Burner 1 is packed in the bearing of burner installed part 3.Burner installed part 3 and chamber wall 5 are adjacent and in distolateral closed chamber.
Burner installed part 3 comprises a support that is designed to flute profile ring 7.There is burner plate 9 in front in flute profile ring 7 inner 2 directions towards the combustion chamber, and it becomes the dividing plate around burner 1 of combustion chamber simultaneously.Therefore the distolateral of combustion chamber only is made up of burner card 9 to a certain extent.Can see the burner wall 27 that centers on burner aperture 33 at the center of burner installed part 3.In the present embodiment, for each burner 1, all there is oneself a burner installed part 3.The burner plate 9 of adjacent burner installed part 3 is along circumferentially under the situation of reserving gap 20 (Fig. 2), adjoining mutually.In addition, burner card 9 is adjacent with chamber wall 5 under the situation of reserving space 30.Not only in space 30 but also in gap 20 (Fig. 2), all the seal (not shown) can be set.
Burner 1 has the mixing burner that comprises fuel combination conduit 23.Here, burner 1 can be with fuel combination or without fuel combination work.Preferably, mixing burner is with for example fuel oil work of liquid fuel.If burner 1 is without liquid fuel work, then fuel combination conduit 23 usefulness fuel interception pipe (not shown) is replaced.
Chamber wall 5 side within it is provided with the protective layer that heat shielding element (not shown) is formed.
The optical pickocff that Fig. 2 representes especially to be designed to monitor by the present invention video camera 22 is configured in two gaps 20 between the combustion chamber plate 39.Yet monitoring video camera 22 can also be adjacent to be arranged in other zones of combustion chamber plate 9.Among this external Fig. 2 also visible radially externally chamber wall 5a and radially at the chamber wall 5b of inside, they make combustion chamber plate 9 be connected with chamber wall 5.Now by the present invention under the situation of at least two burners 1 (Fig. 1), when burner 1 (Fig. 1) when working, establish at least one monitoring video camera 22 in the gap 20 between combustion chamber plate 9 with liquid fuel.Adopt this configuration, make video camera 22 directly arrange mutually opposedly, and thereby can combine and look at space as much as possible with (unshowned) first turborotor.Therefore (unshowned) first turborotor row's complete zone can be passed through monitoring along a small amount of video camera that is provided with in the gap 20 between the combustion chamber plate 9 of circumferential array 22.Video camera 22 also can be configured in combustion chamber plate 9 and radially externally chamber wall 5A or radially in the space 30 between the chamber wall 5B of inside.
When working without liquid fuel, in (unshowned) fuel combination interception pipe, establish at least one monitoring video camera 22 as additional or alternative, directly be structured in the burner 1 thereby monitor video camera 22 here.Monitoring video camera 22 in this case can pack into from (unshowned) outside, combustion chamber and remove easily.Monitoring video camera 22 provides image, and image is by software analysis that is suitable for and automatic identification foreign matter.When the foreign matter of prior prescribed level, give the alarm and then make gas turbine out of service, and control gas turbine thus.In addition, the state of arranging with image on-line monitoring (unshowned) first turborotor that provides.
Although by toroidal combustion chamber explanation the present invention, the combustion chamber also can be designed as the combustion chamber of general cylindrical, is included at least one distolateral burner of cylinder and at least one burner installed part.
Claims (5)
1. a burner (1) that is used for gas turbine comprises combustion chamber, combustion chamber inner (2) and chamber wall (5) and the turbo blade row who is located at the downstream, combustion chamber, and it has first turborotor row; Wherein, burner (1) comprises the burner installed part (3) of fixed combustion device (1) and chamber wall (5), wherein; Burner installed part (3) has combustion chamber plate (9), and wherein, combustion chamber plate (9) is positioned at the front towards the direction of inside, combustion chamber (2); And wherein; Burner (1) comprises at least one fuel combination conduit (23), and this fuel combination conduit is supplied with fuel combination when fuel combination is worked, and it is designed to fuel interception pipe when working without fuel combination; It is characterized by: at burner (1) when working with fuel combination; Lay at least one optical pickocff on combustion chamber plate (9) or near it, and/or, when burner (1) is worked without fuel combination; In fuel interception pipe, lay at least one optical pickocff, thereby can monitor first turborotor row through optical pickocff is set.
2. according to the described burner of claim 1 (1), it is characterized by, said first turborotor row can be by the optical pickocff on-line monitoring.
3. according to claim 1 or 2 described burners (1), it is characterized by, be provided with at least two burners (1); They are circumferentially laid along the combustion chamber, and wherein, each burner (1) comprises one with each burner (1) and the fixing burner installed part (3) of chamber wall (5); Wherein, Each burner installed part (3) has combustion chamber plate (9), and said at least two combustion chamber plates (9) are circumferentially adjacent one another are under the situation of reserving gap (20) along the combustion chamber; And here, optical sensor arrangement is in said gap (20).
4. according to each described burner (1) in the claim 1 to 3, it is characterized by, combustion chamber plate (9) is adjacent with chamber wall (5) under the situation of reserving space (30), and wherein, optical sensor arrangement is in said space (30).
5. one kind with the method for controlling gas turbine according to one of all claims in prostatitis described burner (1) and optical pickocff; It is characterized by: optical pickocff provides image and in the image that is provided by optical pickocff, can discern foreign matter automatically by the software that is suitable for, and when the foreign matter of prior prescribed level, gives the alarm and make gas turbine out of service.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
| EP11165818.3 | 2011-05-12 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN102777935A true CN102777935A (en) | 2012-11-14 |
Family
ID=44582059
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012101487241A Pending CN102777935A (en) | 2011-05-12 | 2012-05-14 | Burner and method for regulating a gas turbine with such a burner |
Country Status (3)
| Country | Link |
|---|---|
| EP (1) | EP2522909B1 (en) |
| CN (1) | CN102777935A (en) |
| RU (1) | RU2012119495A (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102019217983A1 (en) * | 2019-11-21 | 2021-05-27 | Siemens Aktiengesellschaft | Burner insert, process for its production and use of such a burner insert |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1293754A1 (en) * | 2001-09-18 | 2003-03-19 | N.V. Kema | Method and device for examining the strain 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 |
| 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 |
| US20090133378A1 (en) * | 2005-09-27 | 2009-05-28 | Uwe Gruschka | Combustion Chamber and Gas Turbine Installation |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
-
2011
- 2011-05-12 EP EP11165818.3A patent/EP2522909B1/en not_active Not-in-force
-
2012
- 2012-05-11 RU RU2012119495/06A patent/RU2012119495A/en not_active Application Discontinuation
- 2012-05-14 CN CN2012101487241A patent/CN102777935A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1293754A1 (en) * | 2001-09-18 | 2003-03-19 | N.V. Kema | Method and device for examining the strain 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 |
| US20090133378A1 (en) * | 2005-09-27 | 2009-05-28 | Uwe Gruschka | Combustion Chamber and Gas Turbine Installation |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| EP2522909A1 (en) | 2012-11-14 |
| EP2522909B1 (en) | 2015-04-08 |
| RU2012119495A (en) | 2013-11-20 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20121114 |