EP0269824B1 - Kombinierter Diffusions- und Vormischpilotbrenner - Google Patents
Kombinierter Diffusions- und Vormischpilotbrenner Download PDFInfo
- Publication number
- EP0269824B1 EP0269824B1 EP19870115434 EP87115434A EP0269824B1 EP 0269824 B1 EP0269824 B1 EP 0269824B1 EP 19870115434 EP19870115434 EP 19870115434 EP 87115434 A EP87115434 A EP 87115434A EP 0269824 B1 EP0269824 B1 EP 0269824B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- fuel
- premix
- diffusion
- nozzle
- combustor
- 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.)
- Expired
Links
- 239000000446 fuel Substances 0.000 claims description 70
- 238000009792 diffusion process Methods 0.000 claims description 54
- 238000002485 combustion reaction Methods 0.000 claims description 28
- 238000011144 upstream manufacturing Methods 0.000 claims description 7
- 239000000203 mixture Substances 0.000 claims 1
- MWUXSHHQAYIFBG-UHFFFAOYSA-N nitrogen oxide Inorganic materials O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 35
- 239000007789 gas Substances 0.000 description 14
- 230000009977 dual effect Effects 0.000 description 6
- 230000008901 benefit Effects 0.000 description 4
- 230000009467 reduction Effects 0.000 description 2
- 239000000809 air pollutant Substances 0.000 description 1
- 231100001243 air pollutant Toxicity 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000009428 plumbing Methods 0.000 description 1
- VEMKTZHHVJILDY-UHFFFAOYSA-N resmethrin Chemical compound CC1(C)C(C=C(C)C)C1C(=O)OCC1=COC(CC=2C=CC=CC=2)=C1 VEMKTZHHVJILDY-UHFFFAOYSA-N 0.000 description 1
- 230000002459 sustained effect Effects 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23D—BURNERS
- F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
- F23D11/005—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space with combinations of different spraying or vaporising 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
- F23R3/28—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
Definitions
- This invention relates to gas turbine combustors; and, in particular, to improvements in gas turbine combustors for the further diminishment of air pollutants such as nitrogen oxides (NOx).
- NOx nitrogen oxides
- the specific configuration of the present invention includes an annular array of primary nozzles each of which discharges into the primary combustion chamber and a combined diffusion and premix nozzle which discharges into the second combustion chamber.
- These nozzles may all be described as diffusion nozzles in that each nozzle has an axial fuel delivery pipe and is surrounded at its discharge end by an air swirler which provides air for combustion to the fuel nozzle discharge.
- the present inventors have discovered that reduction in the production of NOx can be achieved by using such a combined premix and diffusion nozzle. In operation, a relatively small amount of fuel is used to sustain a diffusion pilot whereas a premix section of the nozzle provides additional fuel for ignition of the main fuel supply from the upstream primary nozzles directed into the primary combustion chamber.
- the present invention is especially applicable to gas turbine combustors of the type which include two combustion chambers separated by a venturi throat region.
- An annular array of primary nozzles discharge fuel into an upstream or primary combustion chamber whereas a single central nozzle discharges fuel into a downstream or second combustion chamber.
- the method of operation dictates that while under base load, the primary nozzles are flamed out whereas the single central combined diffusion and premix nozzle supports combustion of premix fuel from the primary nozzles.
- the single central combined diffusion and premix nozzle reduces the fuel flow to the central diffusion flame from approximately 20 percent of the total fuel flow to about 2 percent of the total fuel flow for the entire combustor.
- the design thus simultaneously minimizes the percentage of total fuel flow in the combuster that burns as a diffusion flame (with high NOx emissions) but allows sufficient heat input to ignite the main premixed flow by using the pilot premixed flow (which has low NOx emissions).
- a combined diffusion and premix nozzle comprising:
- a gas turbine 12 includes a compressor 14, a combustor 16 and a turbine 18 represented by a single blade. Although it is not specifically shown, it is well known that the turbine is drivingly connected to the compressor along a common axis.
- the compressor pressurizes inlet air which is then turned in direction or reversed flowed to the combustor where it is used to cool the combustor and also used to provide air to the combustion process.
- the gas turbine includes a plurality of combustors (one shown) which are located about the periphery of the gas turbine. In one particular gas turbine model there are fourteen such combustors disposed about the periphery of the gas turbine.
- a transition duct 20 connects the outlet end of its particular combustor with the inlet end of the turbine to deliver the hot products of the combustion process to the turbine.
- each combustor comprises a primary or pustream combustion chamber 24 and a second or downstream combustoin chamber 26 separated by a venturi throat region 28.
- the combustor is surrounded by a combustor flow sleeve 30 which channels compressor discharge air flow to the combustor.
- the combustor is further surrounded by an outer casing 31 which is bolted to the turbine casing 32.
- Primary nozzles 36 provide fuel delivery to the upstream combustor 24 and are arranged in an annular array around a central secondary nozzle 38.
- each combustor may include six primary nozzles and one secondary nozzle.
- fuel is delivered to the nozzles through plumbing 42 in a manner well known in the art and fully described in the aforementioned patent. Ignition in the primary combustor is caused by spark plug 48 not shown in Figure 2 and in adjacent combustors by means of crossfire tubes 50 also well known in the art.
- a diffusion nozzle 36 includes a fuel delivery nozzle 54 and an annular swirler 56.
- the nozzle 54 delivers only fuel which is then subsequently mixed with swirler air for combustion.
- the secondary nozzle is also a diffusion nozzle as will be explained further.
- the dual stage, dual mode combustor is designed to operate in a premix mode such that all of the primary nozzles are simply mixing fuel and air to be ignited by the diffusion flame supported by the second or central diffusion nozzle.
- this premixing of the primary nozzle fuel and ignition by the secondary diffusion nozzle led to a lower NOx output in the combustor.
- a satisfactory pilot flame for the main premix flow from the upstream premix (primary) nozzles may be sustained by using a minimal diffusion pilot in combination with a central nozzle premix chamber.
- the invention simultaneously minimized the percentage of total fuel in the combustor that burns as a diffusion flame (with high NOx emissions) whilie allowing sufficient heat input to ignite the main premixed flow by using the premixed secondary or pilot flow.
- the combined nozzle includes a diffusion pilot 62 having a fuel delivery pipe 64.
- the fuel delivery pipe has an axial pipe 66 and a plurality of radial, blind ended fuel distribution tubes 68 which extend radially outwardly from the axial pipe.
- the fuel distribution tubes each include a plurality of fuel discharge holes 70 which are directed downstream toward the discharge end of the combined nozzle.
- the fuel distribution holes are sized so as to obtain the desired percentage of fuel flow in to the premix chamber to be hereinafter described.
- the diffusion pilot 62 further includes an air delivery pipe 74 coaxial with and surrounding the fuel delivery axial pipe 66.
- the air input into the air delivery pipe is compressor discharge air which is reverse flowed around the combustor into the volume 76 defined by the flow sleeve 30 and the combustion chamber liner 78.
- the diffusion pilot includes at its discharge end a first swirler annulus or diffusion pilot swirler 82 for the purpose of directing air delivery pipe discharge air to the diffusion pilot flame.
- a premix chamber 84 is defined by a sleeve like truncated cone 85 which surrounds the diffusion pilot and includes a discharge end (see flow arrows) terminating adjacent the diffusion pilot discharge end. Compressor discharge air is also reverse flowed into the premix chamber from volume 76 in a manner similar to the air delivery pipe.
- the plurality of radial fuel distribution tubes 68 extend through the air delivery pipe 74 and into the premix chamber annulus such that the fuel and air are mixed and delivered to a second swirler or premix chamber swirler 86 between the diffusion pilot and the premix chamber truncated cone 85.
- a third swirler or central nozzle swirler 90 is located downstream from the discharge end of the combined diffusion and premix nozzle. This swirler is located between an extension or cup 92 on the discharge end of the pilot and the centerbody wall 95 of the primary combustion chamber. Compressor air is also reverse flowed to this swirler from the volume 76 surrounding the combustion liners. The purpose of this third swirler is to provide stability for the diffusion and premix nozzle flame when combining with the primary premix flow from the primary combustor.
- the required design of the swirlers 82, 86 and 90 would be known to practitioners in the combustion art and therefore requires no further description.
- the premix chamber or truncated cone is formed of any metal suitable to use within the gas turbine environment.
- fuel flow and combustion is initiated in the primary combustor until a predetermined mid-range load. At that time, fuel flow is split between the primary nozzles and the combined diffusion and premix nozzle to reach a desired load whereas ignition of the combined diffusion and premix nozzle is established.
- Fuel flow to the primary nozzles is then terminated to extinguish burning in the primary combustor. Fuel flow then is reestablished in the primary nozzles which then act as main premix chambers for the primary nozzle fuel main premix flow. At this point, according to prior practice, a diffusion flame using approximately twenty percent of the total combustor fuel flow would be left to produce a relatively high NOx output.
- the foregoing invention produces less NOx while providing an opportunity to add to the fuel flow through the combined diffusion and premix nozzle because of the lower NOx output whereas the turn down ratio or the ability to operate under varying conditions is considerably widened because the diffusion pilot is subject to the premix flow of the pilot rather than the total overall premix flow from the surrounding primary nozzles.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Claims (5)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US93488586A | 1986-11-25 | 1986-11-25 | |
US934885 | 1986-11-25 |
Publications (3)
Publication Number | Publication Date |
---|---|
EP0269824A2 EP0269824A2 (de) | 1988-06-08 |
EP0269824A3 EP0269824A3 (en) | 1988-07-06 |
EP0269824B1 true EP0269824B1 (de) | 1990-12-19 |
Family
ID=25466234
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP19870115434 Expired EP0269824B1 (de) | 1986-11-25 | 1987-10-21 | Kombinierter Diffusions- und Vormischpilotbrenner |
Country Status (4)
Country | Link |
---|---|
EP (1) | EP0269824B1 (de) |
JP (1) | JP2831641B2 (de) |
DE (1) | DE3766807D1 (de) |
NO (1) | NO166340C (de) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130008167A1 (en) * | 2011-07-07 | 2013-01-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5193346A (en) * | 1986-11-25 | 1993-03-16 | General Electric Company | Premixed secondary fuel nozzle with integral swirler |
DE68923413T2 (de) * | 1988-09-07 | 1996-04-04 | Hitachi Ltd | Kraftstoff-Luftvormischvorrichtung für eine Gasturbine. |
JPH0772616B2 (ja) * | 1989-05-24 | 1995-08-02 | 株式会社日立製作所 | 燃焼器及びその運転方法 |
US5125227A (en) * | 1990-07-10 | 1992-06-30 | General Electric Company | Movable combustion system for a gas turbine |
EP0488556B1 (de) * | 1990-11-27 | 1997-07-16 | General Electric Company | Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung |
US5435139A (en) * | 1991-03-22 | 1995-07-25 | Rolls-Royce Plc | Removable combustor liner for gas turbine engine combustor |
US5318436A (en) * | 1991-11-14 | 1994-06-07 | United Technologies Corporation | Low NOx combustion piloted by low NOx pilots |
RU2031229C1 (ru) * | 1992-03-09 | 1995-03-20 | Анатолий Михайлович Рахмаилов | Способ преобразования тепловой энергии в механическую в газотурбинном двигателе и газотурбинный двигатель |
US5267851A (en) * | 1992-03-16 | 1993-12-07 | General Electric Company | Swirl gutters for isolating flow fields for combustion enhancement at non-baseload operating conditions |
US5259184A (en) * | 1992-03-30 | 1993-11-09 | General Electric Company | Dry low NOx single stage dual mode combustor construction for a gas turbine |
IT1255613B (it) * | 1992-09-24 | 1995-11-09 | Eniricerche Spa | Sistema di combustione a basse emissioni inquinanti per turbine a gas |
US5410884A (en) * | 1992-10-19 | 1995-05-02 | Mitsubishi Jukogyo Kabushiki Kaisha | Combustor for gas turbines with diverging pilot nozzle cone |
US5435126A (en) * | 1994-03-14 | 1995-07-25 | General Electric Company | Fuel nozzle for a turbine having dual capability for diffusion and premix combustion and methods of operation |
JP3183053B2 (ja) * | 1994-07-20 | 2001-07-03 | 株式会社日立製作所 | ガスタービン燃焼器及びガスタービン |
DE19542644B4 (de) * | 1995-11-17 | 2008-12-11 | Alstom | Vormischverbrennung |
US6539721B2 (en) | 2001-07-10 | 2003-04-01 | Pratt & Whitney Canada Corp. | Gas-liquid premixer |
US8156743B2 (en) * | 2006-05-04 | 2012-04-17 | General Electric Company | Method and arrangement for expanding a primary and secondary flame in a combustor |
JP5193088B2 (ja) * | 2009-02-20 | 2013-05-08 | 三菱重工業株式会社 | 燃焼器及びガスタービン |
US8919673B2 (en) * | 2010-04-14 | 2014-12-30 | General Electric Company | Apparatus and method for a fuel nozzle |
US9016039B2 (en) * | 2012-04-05 | 2015-04-28 | General Electric Company | Combustor and method for supplying fuel to a combustor |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3648457A (en) * | 1970-04-30 | 1972-03-14 | Gen Electric | Combustion apparatus |
US3886728A (en) * | 1974-05-01 | 1975-06-03 | Gen Motors Corp | Combustor prechamber |
US3958416A (en) * | 1974-12-12 | 1976-05-25 | General Motors Corporation | Combustion apparatus |
JPS51123413A (en) * | 1975-04-19 | 1976-10-28 | Nissan Motor Co Ltd | Combustion system of gas turbine |
US4292801A (en) * | 1979-07-11 | 1981-10-06 | General Electric Company | Dual stage-dual mode low nox combustor |
US4389848A (en) * | 1981-01-12 | 1983-06-28 | United Technologies Corporation | Burner construction for gas turbines |
DE3361535D1 (en) * | 1982-05-28 | 1986-01-30 | Bbc Brown Boveri & Cie | Gas turbine combustion chamber and method of operating it |
DE3241162A1 (de) * | 1982-11-08 | 1984-05-10 | Kraftwerk Union AG, 4330 Mülheim | Vormischbrenner mit integriertem diffusionsbrenner |
JPS59202324A (ja) * | 1983-05-04 | 1984-11-16 | Hitachi Ltd | ガスタ−ビン低NOx燃焼器 |
-
1987
- 1987-10-21 EP EP19870115434 patent/EP0269824B1/de not_active Expired
- 1987-10-21 DE DE8787115434T patent/DE3766807D1/de not_active Expired - Lifetime
- 1987-11-13 JP JP62285662A patent/JP2831641B2/ja not_active Expired - Lifetime
- 1987-11-24 NO NO874893A patent/NO166340C/no not_active IP Right Cessation
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US20130008167A1 (en) * | 2011-07-07 | 2013-01-10 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US9003800B2 (en) * | 2011-07-07 | 2015-04-14 | Mitsubishi Heavy Industries, Ltd. | Gas turbine combustor |
US10197284B2 (en) | 2011-07-07 | 2019-02-05 | Mitsubishi Hitachi Power Systems, Ltd. | Gas turbine combustor |
Also Published As
Publication number | Publication date |
---|---|
EP0269824A3 (en) | 1988-07-06 |
JP2831641B2 (ja) | 1998-12-02 |
EP0269824A2 (de) | 1988-06-08 |
NO874893D0 (no) | 1987-11-24 |
DE3766807D1 (de) | 1991-01-31 |
NO166340B (no) | 1991-03-25 |
NO874893L (no) | 1988-05-26 |
JPH01137117A (ja) | 1989-05-30 |
NO166340C (no) | 1991-07-03 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US4982570A (en) | Premixed pilot nozzle for dry low Nox combustor | |
US5193346A (en) | Premixed secondary fuel nozzle with integral swirler | |
EP0269824B1 (de) | Kombinierter Diffusions- und Vormischpilotbrenner | |
US6968693B2 (en) | Method and apparatus for reducing gas turbine engine emissions | |
EP0602901B1 (de) | Tertiarebrennstoff Einspritzsystem für Brenner mit niedriger NOx-Ausstoss | |
US5289685A (en) | Fuel supply system for a gas turbine engine | |
EP0620402B1 (de) | Vormischbrennkammer mit konzentrischen Ringkanälen | |
JP5400936B2 (ja) | ガスタービンエンジン内で燃料を燃焼させるための方法及び装置 | |
KR100247097B1 (ko) | 가스터어빈용 이중방식 연소기 | |
US5199265A (en) | Two stage (premixed/diffusion) gas only secondary fuel nozzle | |
EP0488556B1 (de) | Sekundäre Vormischbrennstoffdüse mit integrierter Verwirbelungsvorrichtung | |
US5303542A (en) | Fuel supply control method for a gas turbine engine | |
EP0491478B1 (de) | Zwillingsbrennkammer und ihre Funktion | |
US20080016876A1 (en) | Method and apparatus for reducing gas turbine engine emissions | |
EP2407720A2 (de) | Flammentolerante Sekundärbrennstoffdüse | |
US20050223713A1 (en) | Reduced center burner in multi-burner combustor and method for operating the combustor |
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 |
|
PUAL | Search report despatched |
Free format text: ORIGINAL CODE: 0009013 |
|
AK | Designated contracting states |
Kind code of ref document: A2 Designated state(s): CH DE FR GB IT LI NL |
|
AK | Designated contracting states |
Kind code of ref document: A3 Designated state(s): CH DE FR GB IT LI NL |
|
17P | Request for examination filed |
Effective date: 19881221 |
|
17Q | First examination report despatched |
Effective date: 19890420 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): CH DE FR GB IT LI NL |
|
ET | Fr: translation filed | ||
REF | Corresponds to: |
Ref document number: 3766807 Country of ref document: DE Date of ref document: 19910131 |
|
ITF | It: translation for a ep patent filed | ||
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed | ||
ITTA | It: last paid annual fee | ||
REG | Reference to a national code |
Ref country code: GB Ref legal event code: IF02 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: NL Payment date: 20061024 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: GB Payment date: 20061025 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: CH Payment date: 20061027 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: IT Payment date: 20061031 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: DE Payment date: 20061130 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: GB Ref legal event code: PE20 |
|
REG | Reference to a national code |
Ref country code: CH Ref legal event code: PL |
|
NLV7 | Nl: ceased due to reaching the maximum lifetime of a patent |
Effective date: 20071021 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: NL Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20071021 |
|
PG25 | Lapsed in a contracting state [announced via postgrant information from national office to epo] |
Ref country code: GB Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION Effective date: 20071020 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20061017 Year of fee payment: 20 |