CA2537949A1 - Device for stabilizing combustion in gas turbine engines - Google Patents

Device for stabilizing combustion in gas turbine engines Download PDF

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Publication number
CA2537949A1
CA2537949A1 CA002537949A CA2537949A CA2537949A1 CA 2537949 A1 CA2537949 A1 CA 2537949A1 CA 002537949 A CA002537949 A CA 002537949A CA 2537949 A CA2537949 A CA 2537949A CA 2537949 A1 CA2537949 A1 CA 2537949A1
Authority
CA
Canada
Prior art keywords
burner
mixing chamber
main body
recited
flame holder
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
Application number
CA002537949A
Other languages
French (fr)
Other versions
CA2537949C (en
Inventor
Michael Cornwell
Vladimir D. Milosavljevic
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
Collins Engine Nozzles Inc
Original Assignee
Individual
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 Individual filed Critical Individual
Publication of CA2537949A1 publication Critical patent/CA2537949A1/en
Application granted granted Critical
Publication of CA2537949C publication Critical patent/CA2537949C/en
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

Links

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
    • 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
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/74—Preventing flame lift-off
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2209/00—Safety arrangements
    • F23D2209/20—Flame lift-off / stability

Abstract

A burner (100) for a gas turbine combustor that uses a central bluff body flame holder (20)and a quarl (80) to shape the recirculation zone in order to stabilize the combustion process. The burner includes, among other elements, a cylindrical main body (50) and a flame holder. The flame holder is disposed within a fuel-air mixing chamber (60) and includes a base portion (22) and an elongated bluff body (24). The base portion engages with the main body of the burner in a supporting manner and the elongated bluff body extends in an axially downstream direction from the base portion through the internal mixing chamber so as to position a combustion ignition point downstream of the internal mixing chamber. The quarl device defines an interior recirculation chamber (82) and a burner exit (84).

Claims (20)

1. A burner for a gas turbine combustor comprising:
a) a cylindrical main body having axially opposed upstream and downstream end portions, the main body having at least one fuel inlet passage and at least one air inlet passage formed therein which are adapted to supply fuel and air respectively to a mixing chamber defined in the downstream end portion of the main body, the mixing chamber configured to swirl and mix the fuel and air supplied to the mixing chamber; and b) a flame holder disposed within the mixing chamber and including a base portion engaged with the main body of the burner and an elongated bluff body extending in an axially downstream direction from the base portion through the internal mixing chamber so as to control the position of a combustion ignition point downstream of the internal mixing chamber.
2. A burner as recited in Claim 1, further comprising a quarl device disposed adjacent to the downstream end portion of the burner main body, the quad device defining an interior recirculation chamber and a burner exit, the interior recirculation chamber adapted for receiving precombustion gases from the mixing chamber and for recirculating a portion of the combustion product gases in an upstream direction so as to aid in stabilizing combustion.
3. A burner as recited in Claim 1, wherein the bluff body of the flame holder is axially centered within the mixing chamber.
4. A burner as recited in Claim 1, wherein the flame holder bluff body has a tapered region.
5. A burner as recited in Claim 1, wherein the flame holder bluff body has a radially enlarged tip region.
6. A burner as recited in Claim 1, wherein the flame holder has an axial length, which is adapted for achieving a swirl number of greater than about 0.6.
7. A burner as recited in Claim 1, wherein the at least one air inlet passage is formed in a substantially radially inward direction.
8. A burner as recited in Claim 1, wherein fuel enters the mixing chamber of the main body in a substantially axial direction.
9. A burner as recited in Claim 1, wherein the at least one fuel inlet passage formed in the main body of the burner includes a helical portion for imparting an angular momentum to the fuel.
10. A burner as recited in Claim 1, wherein the flame holder bluff body has a plurality of axially extending flutes formed in an outer surface thereof.
11. A burner for a gas turbine combustor comprising:
a) a cylindrical main body having axially opposed upstream and downstream end portions, the main body having at least one fuel inlet passage and at least one air inlet passage formed therein which are adapted to supply fuel and air respectively to a mixing chamber defined in the downstream end portion of the main body, the mixing chamber configured to swirl and mix the fuel and air supplied to the mixing chamber;
b) a flame holder disposed within the mixing chamber and including a base portion engaged with the main body of the burner and an elongated bluff body extending in an axially downstream direction from the base portion through the internal mixing chamber so as control the position of a combustion ignition point downstream of the internal mixing chamber; and c) a quarl device disposed adjacent to the downstream end portion of the burner main body, the quarl device defining an interior recirculation chamber and a burner exit, the interior recirculation chamber adapted for receiving precombustion gases from the mixing chamber and for recirculating a portion of the combustion products gases in an upstream direction so as to aid in stabilizing combustion.
12. A burner as recited in Claim 11, wherein the bluff body of the flame holder is axially centered within the mixing chamber.
13. A burner as recited in Claim 11, wherein the flame holder bluff body has a tapered region.
14. A burner as recited in Claim 11 wherein the flame holder bluff body has radially enlarged tip region.
15. A burner as recited in Claim 11, wherein the flame holder has an axial length, which is adapted for anchoring a main recirculation with a swirl number in the range of between about 0.6 and about 2Ø
16. A burner as recited in Claim 11 wherein the at least one air inlet passage is formed in a substantially radially inward direction.
17. A burner as recited in Claim 11, wherein fuel enters the mixing chamber of the main body in a substantially axial direction.
18. A burner as recited in Claim 11, wherein the at least one fuel inlet passage formed in the main body of the burner includes a helical portion for imparting an angular momentum to the fuel.
19. A burner as recited in Claim 11, wherein the flame holder bluff body has a plurality of axially extending flutes formed in an outer surface thereof.
20. A burner for a gas turbine combustor comprising:
a) a cylindrical main body having axially opposed upstream and downstream end portions, the main body having at least one fuel inlet passage and at least one air inlet passage formed therein which are adapted to supply fuel and air respectively to a mixing chamber defined in the downstream end portion of the main body, the mixing chamber configured to swirl and mix the fuel and air supplied to the mixing chamber; and b) means disposed within the mixing chamber for controlling the position of a combustion ignition point downstream of the internal mixing.
CA2537949A 2003-09-05 2004-09-03 Device for stabilizing combustion in gas turbine engines Expired - Fee Related CA2537949C (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US50051703P 2003-09-05 2003-09-05
US60/500,517 2003-09-05
PCT/US2004/028768 WO2005040682A2 (en) 2003-09-05 2004-09-03 Device for stabilizing combustion in gas turbine engines

Publications (2)

Publication Number Publication Date
CA2537949A1 true CA2537949A1 (en) 2005-05-06
CA2537949C CA2537949C (en) 2011-01-11

Family

ID=34519984

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2537949A Expired - Fee Related CA2537949C (en) 2003-09-05 2004-09-03 Device for stabilizing combustion in gas turbine engines

Country Status (9)

Country Link
US (1) US20050106520A1 (en)
EP (1) EP1668295A2 (en)
JP (1) JP4767851B2 (en)
KR (1) KR101178195B1 (en)
CN (1) CN1878986B (en)
BR (1) BRPI0413966A (en)
CA (1) CA2537949C (en)
RU (1) RU2407950C2 (en)
WO (1) WO2005040682A2 (en)

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Also Published As

Publication number Publication date
JP4767851B2 (en) 2011-09-07
CA2537949C (en) 2011-01-11
US20050106520A1 (en) 2005-05-19
BRPI0413966A (en) 2006-10-31
EP1668295A2 (en) 2006-06-14
RU2407950C2 (en) 2010-12-27
KR101178195B1 (en) 2012-08-30
WO2005040682A2 (en) 2005-05-06
RU2006110986A (en) 2006-07-27
KR20060086358A (en) 2006-07-31
CN1878986B (en) 2010-04-28
CN1878986A (en) 2006-12-13
JP2007504429A (en) 2007-03-01
WO2005040682A3 (en) 2005-08-11

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Effective date: 20160906