IL45684A - Swirl combustor with vortex burning and mixing - Google Patents

Swirl combustor with vortex burning and mixing

Info

Publication number
IL45684A
IL45684A IL45684A IL4568474A IL45684A IL 45684 A IL45684 A IL 45684A IL 45684 A IL45684 A IL 45684A IL 4568474 A IL4568474 A IL 4568474A IL 45684 A IL45684 A IL 45684A
Authority
IL
Israel
Prior art keywords
combustion chamber
set forth
directing
main combustion
combination
Prior art date
Application number
IL45684A
Other versions
IL45684A0 (en
Original Assignee
United Aircraft Corp
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 United Aircraft Corp filed Critical United Aircraft Corp
Publication of IL45684A0 publication Critical patent/IL45684A0/en
Publication of IL45684A publication Critical patent/IL45684A/en

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
    • 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
    • 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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Of Fluid Fuel (AREA)
  • Incineration Of Waste (AREA)
  • Gasification And Melting Of Waste (AREA)
  • Gas Burners (AREA)
  • Regulation And Control Of Combustion (AREA)
  • Control Of Combustion (AREA)

Claims (18)

What we cla im is :
1. A method of carrying out a combustion process comprising the steps of: (1) directing hot gases into a combustion chamber at a desired temperature, (2) directing swirling colums of an oxidizer into said hot gases, (3) introducing a fuel in the mixed ho gases and oxidizer which is ignitable by the resulting temperature of the mixture.
2. A method as set forth in claim 1 wherein said oxidizer is air.
3. A method as set forth in claim 1 wherein the fuel is introduced in step 3 along with the hot ga:3es of step 1.
4. A method as set forth in claim 1 wherein the fuel is introduced in step 3 along with the oxidizer of step 2,
5. A method as set forth in claim 1 wherein adjacent columns of an oxidizer in step 2 are formed having counter rotating swirling motions.
6. A method as set forth in claim I including the step of : (4) forming a combustion chamber an annular chamber, wherein step 2 the swirling colums: of an oxidizer are directed from both sides of said annular combustion chamber into said hot gases.
7. A combustor including a main combustion chamber, a pilot combustion chamber connected at the upstream end there- of for directing a hot gas flow thereinto at a desired temperature, means for directing a plurality of swirling jets of air into said main combustion chamber so as to establish intimate, contact with the hot gas flov; from said pilot combustion chamber, means for directing a fuel into said main combustion chamber for mixing with the hot gas flow and intermixing air.
8. A combination as set for.th in claim 7 wherein said means for directing a fuel into said main combustion chamber includes means for directing a fuel into said pilot combustion chamber so as to enter a hot gas flov/ and be carried from the pilot combustion chamber into the main combustion chamber.
9. A combination as set forth in claim 7 wherein said means for directing a fuel into said main combustion chamber includes means for directing fuel into said means for directing a plurality of swirl jets of air into said main combustion chamber.
10. A combination as set forth in claim 7 wherein said means for directing a plurality of swirling je s of air into said main combustion chamber comprises tubes fixed to said main combustion chamber adjacent its upstream end, said tubes having swirling means located therein to impart: rotary motion to air passing therethrough. /
11. A combination as set forth in claim 10 wherein said tubes have vanes located therein to swirl flov/ passing the tube .
12. A combination as set forth in claim 7 wherein said means for directing a plurality of swirling jets of air into said main combustion chamber has means to direct said swirling jets at an angle into the main combustion chamber.
13. A combination as set forth in claim 7 where insaid main combustion chamber is annular.
14. A combination as set forth in claim 13 wherein said pilot combustion chamber has an annular discharge which is concentric with the annular main combustion chamber.
15. A combination as set forth in claim 7 wherein said main combustion chamber is formed having a diverging transition member at its forward end, said diverging transition member having a small forward opening and a larger rearward opening which is connected to the outer wall of the combustion chamber, said pilot combustion chamber being connected to the small forward opening of said diverging transition member, fixed to the diverging transition member of said main combustion chamber, said tubes having swirling means located there in.
16. A combination as set forth in claim 15 wherein said tubes are directed at an angle into the main combustion chambe .
17. A combination as set forth in claim 16 wherein said tubes are placed in pairs, said areas between said pairs of tubes being blocked to prevent flow around said tubes .
18. A method of carrying out a combustion process according to claims 1-6 substantially as hereinbefore described with reference to the drawings. A corcbustor according to claims 7-17 substantially as hereinbefore described wi^ crifced with reference to and as illustrated in the accompanying drawings.
IL45684A 1973-10-15 1974-09-19 Swirl combustor with vortex burning and mixing IL45684A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US406771A US3872664A (en) 1973-10-15 1973-10-15 Swirl combustor with vortex burning and mixing

Publications (2)

Publication Number Publication Date
IL45684A0 IL45684A0 (en) 1974-12-31
IL45684A true IL45684A (en) 1976-11-30

Family

ID=23609397

Family Applications (1)

Application Number Title Priority Date Filing Date
IL45684A IL45684A (en) 1973-10-15 1974-09-19 Swirl combustor with vortex burning and mixing

Country Status (11)

Country Link
US (1) US3872664A (en)
JP (1) JPS5858563B2 (en)
CA (1) CA1004481A (en)
CH (1) CH585373A5 (en)
DE (1) DE2449084C2 (en)
FR (1) FR2247674B1 (en)
GB (1) GB1482145A (en)
IL (1) IL45684A (en)
IT (1) IT1022870B (en)
NO (1) NO145081C (en)
SE (1) SE400348B (en)

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Also Published As

Publication number Publication date
US3872664A (en) 1975-03-25
IT1022870B (en) 1978-04-20
NO145081B (en) 1981-09-28
JPS5065708A (en) 1975-06-03
FR2247674A1 (en) 1975-05-09
DE2449084A1 (en) 1975-04-17
DE2449084C2 (en) 1984-09-06
CH585373A5 (en) 1977-02-28
AU7329574A (en) 1976-03-18
IL45684A0 (en) 1974-12-31
NO743677L (en) 1975-06-02
CA1004481A (en) 1977-02-01
SE400348B (en) 1978-03-20
SE7412667L (en) 1975-04-16
GB1482145A (en) 1977-08-03
NO145081C (en) 1982-01-06
JPS5858563B2 (en) 1983-12-26
FR2247674B1 (en) 1980-05-23

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