CN1582365A - Combustion chamber/venturi cooling apparatus and method for low nox emission combustor - Google Patents
Combustion chamber/venturi cooling apparatus and method for low nox emission combustor Download PDFInfo
- Publication number
- CN1582365A CN1582365A CNA018239404A CN01823940A CN1582365A CN 1582365 A CN1582365 A CN 1582365A CN A018239404 A CNA018239404 A CN A018239404A CN 01823940 A CN01823940 A CN 01823940A CN 1582365 A CN1582365 A CN 1582365A
- Authority
- CN
- China
- Prior art keywords
- wall
- hole
- cooling air
- passage
- venturi tube
- 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.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 115
- 238000002485 combustion reaction Methods 0.000 title claims abstract description 33
- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000010304 firing Methods 0.000 claims description 41
- 239000000446 fuel Substances 0.000 claims description 19
- 239000007789 gas Substances 0.000 claims description 18
- 230000003187 abdominal effect Effects 0.000 claims description 11
- 239000000112 cooling gas Substances 0.000 claims 1
- MWUXSHHQAYIFBG-UHFFFAOYSA-N Nitric oxide Chemical compound O=[N] MWUXSHHQAYIFBG-UHFFFAOYSA-N 0.000 description 36
- 238000011144 upstream manufacturing Methods 0.000 description 17
- 238000007599 discharging Methods 0.000 description 11
- 239000003550 marker Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 208000002925 dental caries Diseases 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000010438 heat treatment Methods 0.000 description 2
- 239000007788 liquid Substances 0.000 description 2
- NUFNQYOELLVIPL-UHFFFAOYSA-N acifluorfen Chemical compound C1=C([N+]([O-])=O)C(C(=O)O)=CC(OC=2C(=CC(=CC=2)C(F)(F)F)Cl)=C1 NUFNQYOELLVIPL-UHFFFAOYSA-N 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000007084 catalytic combustion reaction Methods 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 239000003344 environmental pollutant Substances 0.000 description 1
- 230000005764 inhibitory process Effects 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 231100000719 pollutant Toxicity 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
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- 125000006850 spacer group Chemical group 0.000 description 1
- 210000002105 tongue Anatomy 0.000 description 1
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
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C1/00—Gas-turbine plants characterised by the use of hot gases or unheated pressurised gases, as the working fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02G—HOT GAS OR COMBUSTION-PRODUCT POSITIVE-DISPLACEMENT ENGINE PLANTS; USE OF WASTE HEAT OF COMBUSTION ENGINES; NOT OTHERWISE PROVIDED FOR
- F02G3/00—Combustion-product positive-displacement engine plants
-
- 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
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
Abstract
Description
Claims (9)
- One kind be used for gas turbine engine, through the burner of improved low emission (NOx), this burner comprises:One liner, this liner have one first annular wall; And comprise that one is used for the premixing cavity and the firing chamber in order to burn described fuel and air of fuel combination and air, and described premixing cavity is connected with the firing chamber, and described first annular wall has one first hole at least;One Venturi tube, it has one second annular wall, this second annular wall comprises that a convergent walls, disperses wall, described convergent walls is connected to form the necking down throat of a Venturi tube with the described wall of dispersing, described necking down throat is between described premixing cavity and described firing chamber, one described second annular wall from described first annular wall radially inwardly and have and adjacent tail end or rear end, described at least one first hole, described second annular wall is from described first annular wall radially inwardly and have a rear end adjacent with at least one second hole with described at least one first hole;One passage, be used to make cooling air to flow through described Venturi tube, described passage extends from described at least one first hole to described at least one second hole, described at least one second hole is radially outer at described premixing cavity, described passage comprise one from described first wall radially inwardly with from the radially outer first portion of described second wall and from the radially outer second portion of described second wall, described second portion extends to described at least one second hole from described first portion, and described first hole is radially outer from described first portion;One blocking-up ring, it extends and is connected hermetically with them from the rear end of described second annular wall to described first annular wall, and described blocking-up ring prevents that the cooling air in the first portion of described passage from flowing directly into described firing chamber and not flowing through the second portion of described passage;Wherein, described passage is communicated with described at least one first hole and described at least one second orifice flow body, described passage is connected with described mixing chamber by described at least one second hole, cooling air is in cooling described Venturi tube and after being heated, flow into premixing cavity from described passage, thereby increased the efficient of combustion process and reduced the discharge amount of NOx.
- 2. the burner of low emission as claimed in claim 1 (NOx), it is characterized in that, it also comprises one from the radially outer ringwise basically annular abdominal belt wall of first annular wall and at least one the 3rd hole described first annular wall, the first portion of described passage is connected with the second portion of described passage by described the 3rd hole, wherein, described abdominal belt wall forms the radially external boundary of the second portion of a described passage.
- 3. the burner of low emission as claimed in claim 2 (NOx), it is characterized in that, described at least one first hole comprises a plurality of along circumferentially spaced a plurality of first holes of first annular wall, and each described first hole in the footpath of the first portion of passage to the outside.
- 4. the burner of low emission as claimed in claim 3 (NOx) is characterized in that, described at least one second hole comprises around circumferentially spaced a plurality of second holes of first annular wall, and the footpath that each described second hole is in premixing cavity to the outside.
- 5. the burner of low emission as claimed in claim 4 (NOx) is characterized in that, this at least one the 3rd hole comprises around circumferentially spaced a plurality of the 3rd holes of first annular wall, and each the 3rd hole is in the Venturi tube footpath to the outside.
- 6. the method for the Venturi tube in the cooling gas turbine engine combustors is characterized in that this method comprises:One burner liner is provided, this liner has one first annular wall, and comprising that one is used for the firing chamber of premixing cavity and the described fuel of burning and the air of fuel combination and air, described premixing cavity is communicated with described firing chamber, and this first annular wall has one first hole at least;One Venturi tube is provided, this Venturi tube comprises one second annular wall, this second annular wall comprises that a convergent walls and disperses wall, thereby described convergent walls links to each other and forms the throat of this Venturi tube with the described wall of dispersing, described throat is between premixing cavity and firing chamber, and described second annular wall from first annular wall radially inwardly and have adjacent rear portion (afterbody), at least one first hole with this;Provide a passage so that cooling air flows through described Venturi tube, described passage extends at least one second hole from this first hole, this at least one second hole is positioned at the radially outward place of premixing cavity and is connected with it, described passage comprises that one radially inwardly and from this second wall radially outward and along described disperses the first portion that wall and convergent walls are extended from first wall, an and second portion, this second portion is from described premixing cavity radially outward, and described second portion extends to this at least one second hole from described first portion;Make cooling air go into the first portion of described passage by described at least one first orifice flow;Heat is passed to cooling air from described second wall, thereby cool off this second wall and cooling air itself is heated;Make cooling air flow into the second portion of described passage from the first portion of described passage;Make cooling air flow through described at least one second hole and enter described premixing cavity from the second portion of described passage;
- 7. method as claimed in claim 6 is characterized in that, the step that heat is passed to this cooling air from described second wall comprises to be passed to heat described cooling air and heat is passed to described cooling air from described convergent walls from dispersing wall.
- 8. one produce the method for low NOx drainage, it is characterized in that this method comprises from the gas turbine engine burner:One burner liner is provided in burner, described liner has one first annular wall, and comprise the firing chamber of a premixing cavity in order to fuel combination and air feed and described fuel of burning and air, described premixing cavity is connected with described firing chamber, and described first annular wall has at least one first hole;One Venturi tube that comprises one second annular wall is provided, this Venturi tube second annular wall comprises that a convergent walls and disperses wall, described convergent walls links to each other with the described wall of dispersing, thereby form a throat of Venturi tube, described throat is between premixing cavity and firing chamber, described second annular wall is radially inside from described first annular wall, and has and rearward end that this at least one first hole is contiguous;The passage that makes cooling air flow through Venturi tube is provided, described passage extends at least one second hole from described first hole, this at least one second hole is positioned at the premixing cavity radially outward, and be communicated with the latter, described passage comprises that one radially inwardly reaches from the described second wall radially outward and along described from described first wall and to disperse the first portion that wall and convergent walls are extended;And one from the radially outer second portion of premixing, and described second portion extends to described at least one second hole from described first portion;Make cooling air go into the first portion of passage by described at least one first orifice flow;Thereby heat is passed to described cooling air from second wall cool off this second wall and described cooling air itself is heated;Make cooling air flow into the second portion of described passage from the first portion of described passage;Make described cooling air flow through at least one second orifice flow and go into premixing cavity from the second portion of described passage; And,With the fuel mix in heated cooling air and the premixing cavity and burn described cooling air and described fuel.
- 9. method as claimed in claim 8 is characterized in that, the step that heat is passed to cooling air from described second wall comprises heat is passed to described cooling air from the described wall of dispersing, and subsequently heat passed to cooling air from convergent walls.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
PCT/US2001/045097 WO2003093664A1 (en) | 2000-06-28 | 2001-11-30 | Combustion chamber/venturi cooling for a low nox emission combustor |
Publications (2)
Publication Number | Publication Date |
---|---|
CN1582365A true CN1582365A (en) | 2005-02-16 |
CN100368664C CN100368664C (en) | 2008-02-13 |
Family
ID=32769576
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CNB018239404A Expired - Fee Related CN100368664C (en) | 2001-11-30 | 2001-11-30 | Combustion chamber/venturi cooling apparatus and method for low nox emission combustor |
Country Status (8)
Country | Link |
---|---|
EP (1) | EP1461520A4 (en) |
JP (1) | JP4121998B2 (en) |
KR (1) | KR100831772B1 (en) |
CN (1) | CN100368664C (en) |
AU (1) | AU2002219991A1 (en) |
BR (1) | BR0117192B1 (en) |
CA (1) | CA2468646C (en) |
MX (1) | MXPA04005182A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101598337A (en) * | 2008-06-05 | 2009-12-09 | 通用电气公司 | The Coanda pilot nozzle that is used for low emission combustor |
CN101105293B (en) * | 2006-07-14 | 2011-06-08 | 通用电气公司 | Method and apparatus to facilitate reducing NOx emissions in turbine engines |
CN103090411A (en) * | 2011-11-04 | 2013-05-08 | 通用电气公司 | Combustion system having a venturi for reducing wakes in an airflow |
CN104807042A (en) * | 2015-05-15 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
CN106969379A (en) * | 2015-09-23 | 2017-07-21 | 通用电气公司 | Premix fuel nozzle assembly cylinder |
CN108518290A (en) * | 2018-02-24 | 2018-09-11 | 陕西航天机电环境工程设计院有限责任公司 | A kind of array self-impacting water mist cooling apparatus |
CN115371084A (en) * | 2021-05-18 | 2022-11-22 | 通用电气公司 | Swirler with rifled venturi for dynamics mitigation |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
KR100890823B1 (en) * | 2007-11-13 | 2009-03-30 | 한국기계연구원 | Gas turbine system |
KR100862374B1 (en) * | 2007-11-13 | 2008-10-13 | 한국기계연구원 | Overheating preventing gas turbine system |
US20100192580A1 (en) * | 2009-02-03 | 2010-08-05 | Derrick Walter Simons | Combustion System Burner Tube |
US8646277B2 (en) * | 2010-02-19 | 2014-02-11 | General Electric Company | Combustor liner for a turbine engine with venturi and air deflector |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4982570A (en) | 1986-11-25 | 1991-01-08 | General Electric Company | Premixed pilot nozzle for dry low Nox combustor |
US4984429A (en) * | 1986-11-25 | 1991-01-15 | General Electric Company | Impingement cooled liner for dry low NOx venturi combustor |
US5127221A (en) * | 1990-05-03 | 1992-07-07 | General Electric Company | Transpiration cooled throat section for low nox combustor and related process |
DE19751299C2 (en) | 1997-11-19 | 1999-09-09 | Siemens Ag | Combustion chamber and method for steam cooling a combustion chamber |
US6427446B1 (en) * | 2000-09-19 | 2002-08-06 | Power Systems Mfg., Llc | Low NOx emission combustion liner with circumferentially angled film cooling holes |
US6430932B1 (en) * | 2001-07-19 | 2002-08-13 | Power Systems Mfg., Llc | Low NOx combustion liner with cooling air plenum recesses |
-
2001
- 2001-11-30 BR BRPI0117192-5A patent/BR0117192B1/en not_active IP Right Cessation
- 2001-11-30 MX MXPA04005182A patent/MXPA04005182A/en active IP Right Grant
- 2001-11-30 JP JP2004501791A patent/JP4121998B2/en not_active Expired - Fee Related
- 2001-11-30 EP EP01275164A patent/EP1461520A4/en not_active Withdrawn
- 2001-11-30 CN CNB018239404A patent/CN100368664C/en not_active Expired - Fee Related
- 2001-11-30 AU AU2002219991A patent/AU2002219991A1/en not_active Abandoned
- 2001-11-30 CA CA002468646A patent/CA2468646C/en not_active Expired - Fee Related
- 2001-11-30 KR KR1020047008187A patent/KR100831772B1/en not_active IP Right Cessation
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN101105293B (en) * | 2006-07-14 | 2011-06-08 | 通用电气公司 | Method and apparatus to facilitate reducing NOx emissions in turbine engines |
CN101598337A (en) * | 2008-06-05 | 2009-12-09 | 通用电气公司 | The Coanda pilot nozzle that is used for low emission combustor |
CN103090411A (en) * | 2011-11-04 | 2013-05-08 | 通用电气公司 | Combustion system having a venturi for reducing wakes in an airflow |
US9267687B2 (en) | 2011-11-04 | 2016-02-23 | General Electric Company | Combustion system having a venturi for reducing wakes in an airflow |
CN103090411B (en) * | 2011-11-04 | 2016-05-18 | 通用电气公司 | Have for reducing the combustion system in the Venturi tube of the wake flow of air stream |
CN104807042A (en) * | 2015-05-15 | 2015-07-29 | 中国航空工业集团公司沈阳发动机设计研究所 | Combustion chamber |
CN106969379A (en) * | 2015-09-23 | 2017-07-21 | 通用电气公司 | Premix fuel nozzle assembly cylinder |
CN106969379B (en) * | 2015-09-23 | 2021-08-10 | 通用电气公司 | Premix fuel nozzle assembly cartridge |
CN108518290A (en) * | 2018-02-24 | 2018-09-11 | 陕西航天机电环境工程设计院有限责任公司 | A kind of array self-impacting water mist cooling apparatus |
CN115371084A (en) * | 2021-05-18 | 2022-11-22 | 通用电气公司 | Swirler with rifled venturi for dynamics mitigation |
Also Published As
Publication number | Publication date |
---|---|
MXPA04005182A (en) | 2005-02-17 |
CA2468646C (en) | 2009-09-29 |
CA2468646A1 (en) | 2003-11-13 |
JP2005520120A (en) | 2005-07-07 |
BR0117192A (en) | 2004-11-09 |
EP1461520A4 (en) | 2010-04-14 |
KR100831772B1 (en) | 2008-05-27 |
CN100368664C (en) | 2008-02-13 |
AU2002219991A1 (en) | 2003-11-17 |
KR20040058351A (en) | 2004-07-03 |
BR0117192B1 (en) | 2010-12-14 |
EP1461520A1 (en) | 2004-09-29 |
JP4121998B2 (en) | 2008-07-23 |
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Legal Events
Date | Code | Title | Description |
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C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C41 | Transfer of patent application or patent right or utility model | ||
TA01 | Transfer of patent application right |
Effective date of registration: 20070914 Address after: American Connecticut Applicant after: Power System Mfg. LLC Address before: American Florida Applicant before: Power System Mfg. LLC |
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C14 | Grant of patent or utility model | ||
GR01 | Patent grant | ||
ASS | Succession or assignment of patent right |
Owner name: ALSTOM TECHNOLOGY LTD. Free format text: FORMER OWNER: POWER SYSTEM MFG. LLC Effective date: 20121220 |
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C41 | Transfer of patent application or patent right or utility model | ||
TR01 | Transfer of patent right |
Effective date of registration: 20121220 Address after: Baden, Switzerland Patentee after: Alstom Technology Ltd. Address before: American Connecticut Patentee before: Power System Mfg. LLC |
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C56 | Change in the name or address of the patentee | ||
CP01 | Change in the name or title of a patent holder |
Address after: Baden, Switzerland Patentee after: ALSTOM TECHNOLOGY LTD Address before: Baden, Switzerland Patentee before: Alstom Technology Ltd. |
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TR01 | Transfer of patent right |
Effective date of registration: 20171130 Address after: Baden, Switzerland Patentee after: Energy resources Switzerland AG Address before: Baden, Switzerland Patentee before: ALSTOM TECHNOLOGY LTD |
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TR01 | Transfer of patent right | ||
CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080213 Termination date: 20171130 |
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CF01 | Termination of patent right due to non-payment of annual fee |