EP2677239A1 - Procédé de commande d'une chambre de combustion à deux étage d'une turbine à gaz - Google Patents
Procédé de commande d'une chambre de combustion à deux étage d'une turbine à gaz Download PDFInfo
- Publication number
- EP2677239A1 EP2677239A1 EP12172629.3A EP12172629A EP2677239A1 EP 2677239 A1 EP2677239 A1 EP 2677239A1 EP 12172629 A EP12172629 A EP 12172629A EP 2677239 A1 EP2677239 A1 EP 2677239A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- temperature
- fuel
- fuel supply
- flame
- combustion chamber
- 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- Withdrawn
Links
Images
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
- F23R3/346—Feeding into different combustion zones for staged combustion
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN A CARRIER GAS OR AIR
- F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
- F23C2900/07002—Premix burners with air inlet slots obtained between offset curved wall surfaces, e.g. double cone burners
Definitions
- the present disclosure relates to a method for operating a combustion device.
- the combustion device is preferably a combustion device of a gas turbine.
- EP 2 434 222 discloses a combustion device having a combustion chamber connected to a plurality of burners.
- the burners are divided in two groups, namely:
- This structure for the combustion device and this operating concept allow a broad operating window for the gas turbine.
- the inventors have found a method for operating a combustion device having the features above described, which permits operation with low NOx emissions.
- An aspect of the disclosure includes providing a method for operating a combustion device generating low NOx emissions.
- the NOx emissions generated while operating the first fuel supply to generate a flame at a first temperature and the second fuel supply to generate a flame at a second temperature are lower than the NOx emissions generated when operating a combustion device with all fuel supplies that generate flames at a temperature being the average of the first and second temperature.
- This combustion device 1 has a combustion chamber 2 with at least a first fuel supply 3 and a second fuel supply 4.
- the first fuel supply 3 can for example include one or more fuel supplies, such as premixed fuel supplies.
- the premixed fuel supplies include conic shells defining substantially conic swirl chambers and slots between adjacent shells. Adjacent to the slots, fuel pipes are provided; these pipes have injectors for the fuel.
- an air stream is introduced into the swirl chambers through the slots and fuel (gas or liquid fuel) is injected into the air stream via the pipes and their injectors.
- the second fuel supply 4 can include one or more fuel supplies, such as premixed fuel supplies.
- the fuel supplies can have conical shells with slots for air and pipes with injectors for fuel, as above described.
- Reference 5 indicates the gas turbine longitudinal axis; as shown, the first fuel supply 3 is axially upstream of the second fuel supply 4 (i.e. the fuel supply 3 is upstream of the second fuel supply 4 along the axis 5).
- the first and second fuel supplies 3, 4 can be arranged in different ways and for example they can be:
- the fuel injected via the first fuel supply 3 generates a flame 7 having a first temperature T1.
- the fuel injected via the second fuel supply 4 generates a flame 8 having a second temperature T2.
- the second temperature is higher than the first temperature.
- This temperature regulation allows a reduction of the NOx emissions when compared to the emissions of a gas turbine operating at a temperature between the first and second temperature and generating the same power output.
- NOx generation in a combustion device largely depends on the flame temperature and residence time within the combustion chamber 2. Namely the higher the flame temperature the higher the NOx generation ( figure 2 ) and likewise the higher the residence time in the combustion chamber the higher the NOx generation (thermal NOx, figure 3 ) .
- Figure 3 also shows the NOx generated by a combustion chamber having all fuel supplies:
- the NOx generated in the first case is smaller than the NOx generated in the second case.
- the flame temperature T2 at the second fuel supply 4 can be reduced, while operating the second fuel supply far from the lean blow off conditions.
- the load can be increased by increasing the flame temperature T1 at the first fuel supply 3; in this case regulation brings the first fuel supply 3 farther from the lean blow off conditions.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12172629.3A EP2677239A1 (fr) | 2012-06-19 | 2012-06-19 | Procédé de commande d'une chambre de combustion à deux étage d'une turbine à gaz |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12172629.3A EP2677239A1 (fr) | 2012-06-19 | 2012-06-19 | Procédé de commande d'une chambre de combustion à deux étage d'une turbine à gaz |
Publications (1)
Publication Number | Publication Date |
---|---|
EP2677239A1 true EP2677239A1 (fr) | 2013-12-25 |
Family
ID=46319015
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12172629.3A Withdrawn EP2677239A1 (fr) | 2012-06-19 | 2012-06-19 | Procédé de commande d'une chambre de combustion à deux étage d'une turbine à gaz |
Country Status (1)
Country | Link |
---|---|
EP (1) | EP2677239A1 (fr) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105952542A (zh) * | 2015-03-09 | 2016-09-21 | 安萨尔多能源英国知识产权有限公司 | 用于操作燃气轮机的方法 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2003554A (en) * | 1977-09-02 | 1979-03-14 | Snecma | Gas turbine combustion chambers |
GB2010408A (en) * | 1977-12-15 | 1979-06-27 | Gen Electric | Double annular combustor configuration |
WO1996027766A1 (fr) * | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Chambre de combustion a anneau double et etagement axial pour une turbine a gaz |
EP2434222A1 (fr) | 2010-09-24 | 2012-03-28 | Alstom Technology Ltd | Chambre de combustion et procédé de fonctionnement d'une chambre de combustion |
-
2012
- 2012-06-19 EP EP12172629.3A patent/EP2677239A1/fr not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2003554A (en) * | 1977-09-02 | 1979-03-14 | Snecma | Gas turbine combustion chambers |
GB2010408A (en) * | 1977-12-15 | 1979-06-27 | Gen Electric | Double annular combustor configuration |
WO1996027766A1 (fr) * | 1995-03-08 | 1996-09-12 | Bmw Rolls-Royce Gmbh | Chambre de combustion a anneau double et etagement axial pour une turbine a gaz |
EP2434222A1 (fr) | 2010-09-24 | 2012-03-28 | Alstom Technology Ltd | Chambre de combustion et procédé de fonctionnement d'une chambre de combustion |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN105952542A (zh) * | 2015-03-09 | 2016-09-21 | 安萨尔多能源英国知识产权有限公司 | 用于操作燃气轮机的方法 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN106796031B (zh) | 火炬式点火器 | |
EP2626635B1 (fr) | Ensemble de chambre de combustion avec cavité de vortex immobilisée | |
EP2573469B1 (fr) | Chambre de combustion pour fournir du carburant à une chambre de combustion | |
JP6161949B2 (ja) | 燃焼器に作動流体を供給するためのシステム | |
EP2639508A2 (fr) | Système pour fournir un fluide de travail à une chambre de combustion | |
EP2733425B1 (fr) | Turbomachine et système de combustion étagé d'une turbomachine | |
EP2479498A2 (fr) | Chambre de combustion de turbine à gaz et procédé de fonctionnement | |
EP2837889B1 (fr) | Combustion séquentielle avec un mélangeur de gaz de dilution | |
EP2400216A1 (fr) | Lance de brûleur post-combustion | |
EP2754963A1 (fr) | Chambre de combustion de turbine à gaz | |
EP2458283A1 (fr) | Chambre de combustion pour turbine à gaz et procédé d'approvisionnement de combustible | |
CN102444911A (zh) | 具有贫预喷喷嘴燃料喷射***的燃烧器 | |
EP2434222B1 (fr) | Méthode d'opération d'une chambre de combustion | |
JP2010085087A5 (fr) | ||
JP2013142531A (ja) | 作動流体を燃焼器に供給するためのシステムおよび方法 | |
US8745986B2 (en) | System and method of supplying fuel to a gas turbine | |
EP2420731B1 (fr) | Brûleur post-combustion | |
KR20100074102A (ko) | 가스 터빈의 연료 제어 방법 및 연료 제어 장치, 및 가스 터빈 | |
JP2014122784A (ja) | 燃焼器に燃料を供給するためのシステム | |
US20180187563A1 (en) | Gas turbine transition duct with late lean injection having reduced combustion residence time | |
EP2664854B1 (fr) | Système de combustion secondaire | |
US8893501B2 (en) | Combustor crossfire tube | |
JP2015105766A (ja) | ノズル、燃焼器、及びガスタービン | |
JP2013145109A (ja) | 燃焼器に作動流体を供給するためのシステムおよび方法 | |
JP2016023916A (ja) | ガスタービン燃焼器 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR |
|
AX | Request for extension of the european patent |
Extension state: BA ME |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 20140626 |