[go: up one dir, main page]

US2951339A - Combustion chamber swirler - Google Patents

Combustion chamber swirler Download PDF

Info

Publication number
US2951339A
US2951339A US803175A US80317559A US2951339A US 2951339 A US2951339 A US 2951339A US 803175 A US803175 A US 803175A US 80317559 A US80317559 A US 80317559A US 2951339 A US2951339 A US 2951339A
Authority
US
United States
Prior art keywords
sleeve
burner
air
swirler
swirl
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 - Lifetime
Application number
US803175A
Other languages
English (en)
Inventor
George R Benson
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.)
RTX Corp
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
Priority to US803175A priority Critical patent/US2951339A/en
Priority to DEU6592A priority patent/DE1118535B/de
Priority to FR807874A priority patent/FR1238089A/fr
Priority to GB37442/59A priority patent/GB887829A/en
Application granted granted Critical
Publication of US2951339A publication Critical patent/US2951339A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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
    • F23R3/34—Feeding into different combustion zones
    • 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

Definitions

  • Brown Patent No. 2,676,460 One form of combustion system for this purpose is disclosed in Brown Patent No. 2,676,460 in which the burner can has an inner sleeve defining a central air passage such that combustion takes places in the annulus defined between the outer sleeve of the burner can and the inner sleeve.
  • a feature of the present invention is a swirler in the inner sleeve to impart a swirl to the air discharging into the burner space from the central passage.
  • thev downstream end of the central air passage is closed so that any air entering this passage is discharged through the small openings in the side walls of the passage.
  • One feature of the present invention is the re placement of this closed end on the passage with a swirler so that additional air from the passage may enter the combustion space with a swirling action.
  • Fig. l is a sectional view through a burner can.
  • Fig. 2 is an end view of the center tube.
  • the burner can in the drawing has an outer sleeve 2 and an inner concentric sleeve 4. These sleeves are interconnected at the upstream ends by an end cap 6 on the burner can which is in the form of a ring extending between the inner and outer sleeves. The upstream end of the inner'sleeve 4 is unobstructed, as shown. A row of fuel nozzles 8 are positioned in openings 10 in the end cap 6 and fuel from these nozzles is discharged into the annular space 12 defined between the two sleeves. In this space combustion of the mixture of fuel and air takes place.
  • the burner can is positioned in a duct as is well known and shown, for example, in the Brown P-atent No. 2,676,460 so that air under pressure is flowing in a generally axial direction around the burner can and also into the central passage 14 within the sleeve 4.
  • the products of combustion are discharged from the burner can into a transition piece 16 connected to the downstream end of the outer sleeve 2.
  • This transition piece is cylindrical at its upper end 18 to receive the end of the sleeve 4 and becomes segmental in shape at its downstream end 20. 1
  • the inner and outer sleeves are made up of short tapering rings overlapping one another and having rows of air inlet openings 22 therein. This form of overlapping rings is described in a Highberg Patent No. 2,801,520.
  • the downstream end of the inner sleeve 4 has positioned therein United States Patent 0 2,951,339 Patented Sept. 6, 1960 ice a row of swirl vanes 24.
  • These vanes are carried by an outer ring 26 secured to the sleeve 4 and extend radially inward.
  • Each vane is positioned at an acute angle to a longitudinal plane with the result that the air passing in a generally axial direction over the vanes is caused to swirl in a helical manner while continuing its generally axial flow and the inner ends of the swirl vanes 24 are connected to and support a dome-shaped center piece 28.
  • the tip of the dome faces in a downstream direction to provide a faired surface for defining an inner wall for the air flowing helically through the swirl vanes 24.
  • This imperforate dome limits the flow through the end of the sleeve 4 so that all of the air entering the combustion space through the end of the sleeve will be restricted to a flow over the swirl vanes and thus enters the space in a helical path.
  • the sleeve 4 in the arrangement shown terminates at a point forward of the downstream end of the outer sleeve 2.
  • a sleeve forming the outer wall of the can, a closure for the upstream end of the sleeve, a plurality of fuel nozzles arranged in a ring in said closure concentrically of said sleeve, said closure having a central opening within the ring of nozzles for the admission of air axially therethrough and swirl means extending transversely across said central opening for imparting a helical swirl to the air entering the sleeve from said central opening.
  • a burner can as in claim 1 in which the central opening has an inner sleeve attached thereto and pro jecting downstream therefrom within the first sleeve with the swirl imparting means positioned transversely across said inner sleeve.
  • a burner can as in claim 1 in which an inner sleeve concentric to the first sleeve extends in a downstream direction from said central opening and is supported by said closure with the swirl imparting means located at the downstream end of said inner sleeve.
  • a burner in a burner can, concentric inner and outer sleeves defining an annular space therebetween and an upstream closure extending between said sleeves and closing the upstream end of the space between said sleeves, the inner sleeve terminating at a point upstream of said outer sleeve, in combination with a swirler positioned transversely across the downstream end of the inner sleeve for imparting a helical swirl to the air passing in an axial direction into the burner can from said inner sleeve.
  • a burner can as in claim 5 in which the swirler includes a ring of swirl vanes and a central imperforate portion.
  • a burner can as in claim 5 in which the swirler includes a ring of swirl vanes and a central imperforate portion with the peak of the dome directed downstream to define a curved surface over which swirling air past the vanes is directed.
  • a burner can as in claim 5 in which the closure supports a ring of fuel nozzles, the inner and outer sleeves having rows of inlet openings in the walls thereof and in which the inner wall terminates forward or the down stream end of the outer sleeve.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
US803175A 1959-03-31 1959-03-31 Combustion chamber swirler Expired - Lifetime US2951339A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
US803175A US2951339A (en) 1959-03-31 1959-03-31 Combustion chamber swirler
DEU6592A DE1118535B (de) 1959-03-31 1959-10-19 Flammrohr fuer Gasturbinen-Brennkammern
FR807874A FR1238089A (fr) 1959-03-31 1959-10-19 Perfectionnements aux tubes de flamme pour turbines à gaz
GB37442/59A GB887829A (en) 1959-03-31 1959-11-04 Improvements relating to flame tubes for combustion systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US803175A US2951339A (en) 1959-03-31 1959-03-31 Combustion chamber swirler

Publications (1)

Publication Number Publication Date
US2951339A true US2951339A (en) 1960-09-06

Family

ID=25185787

Family Applications (1)

Application Number Title Priority Date Filing Date
US803175A Expired - Lifetime US2951339A (en) 1959-03-31 1959-03-31 Combustion chamber swirler

Country Status (4)

Country Link
US (1) US2951339A (de)
DE (1) DE1118535B (de)
FR (1) FR1238089A (de)
GB (1) GB887829A (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3099134A (en) * 1959-12-24 1963-07-30 Havilland Engine Co Ltd Combustion chambers
DE2538134A1 (de) * 1974-08-27 1976-03-11 Mitsubishi Heavy Ind Ltd Oelbrenner
US3991562A (en) * 1975-07-21 1976-11-16 United Technologies Corporation Combustion chamber assembly having removable center liner
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5253478A (en) * 1991-12-30 1993-10-19 General Electric Company Flame holding diverging centerbody cup construction for a dry low NOx combustor
US6430919B1 (en) * 2000-03-02 2002-08-13 Direct Propulsion Devices, Inc. Shaped charged engine
US20060101801A1 (en) * 2004-11-18 2006-05-18 Siemens Westinghouse Power Corporation Combustor flow sleeve with optimized cooling and airflow distribution

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2175866A (en) * 1934-04-16 1939-10-10 Philip S Arnold Fuel burner
US2813397A (en) * 1957-01-02 1957-11-19 United Aircraft Corp Thermal expansion means for combustion chambers
GB800512A (en) * 1955-01-03 1958-08-27 Lucas Industries Ltd Liquid fuel combustion chambers

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB670092A (en) * 1949-01-03 1952-04-16 Rolls Royce Improvements relating to combustion equipment for gas-turbine engines
US2676460A (en) * 1950-03-23 1954-04-27 United Aircraft Corp Burner construction of the can-an-nular type having means for distributing airflow to each can

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2175866A (en) * 1934-04-16 1939-10-10 Philip S Arnold Fuel burner
GB800512A (en) * 1955-01-03 1958-08-27 Lucas Industries Ltd Liquid fuel combustion chambers
US2813397A (en) * 1957-01-02 1957-11-19 United Aircraft Corp Thermal expansion means for combustion chambers

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3099134A (en) * 1959-12-24 1963-07-30 Havilland Engine Co Ltd Combustion chambers
DE2538134A1 (de) * 1974-08-27 1976-03-11 Mitsubishi Heavy Ind Ltd Oelbrenner
US4173118A (en) * 1974-08-27 1979-11-06 Mitsubishi Jukogyo Kabushiki Kaisha Fuel combustion apparatus employing staged combustion
US3991562A (en) * 1975-07-21 1976-11-16 United Technologies Corporation Combustion chamber assembly having removable center liner
US5197278A (en) * 1990-12-17 1993-03-30 General Electric Company Double dome combustor and method of operation
US5253478A (en) * 1991-12-30 1993-10-19 General Electric Company Flame holding diverging centerbody cup construction for a dry low NOx combustor
US6430919B1 (en) * 2000-03-02 2002-08-13 Direct Propulsion Devices, Inc. Shaped charged engine
US20060101801A1 (en) * 2004-11-18 2006-05-18 Siemens Westinghouse Power Corporation Combustor flow sleeve with optimized cooling and airflow distribution
US7574865B2 (en) 2004-11-18 2009-08-18 Siemens Energy, Inc. Combustor flow sleeve with optimized cooling and airflow distribution

Also Published As

Publication number Publication date
GB887829A (en) 1962-01-24
DE1118535B (de) 1961-11-30
FR1238089A (fr) 1960-08-05

Similar Documents

Publication Publication Date Title
US2676460A (en) Burner construction of the can-an-nular type having means for distributing airflow to each can
US2488911A (en) Combustion apparatus for use with turbines
US3099134A (en) Combustion chambers
US4193260A (en) Combustion apparatus
US2638745A (en) Gas turbine combustor having tangential air inlets for primary and secondary air
US4301657A (en) Gas turbine combustion chamber
US2856755A (en) Combustion chamber with diverse combustion and diluent air paths
US2475911A (en) Combustion apparatus
US3299632A (en) Combustion chamber for a gas turbine engine
US2531810A (en) Air inlet arrangement for combustion chamber flame tubes
US2555965A (en) End cap for fluid fuel combustors
US3540216A (en) Two-flow gas turbine jet engine
US2965303A (en) Coolant injection in a fuel nozzle
US2977760A (en) Annular combustion chambers for use with compressors capable of discharging combustion supporting medium with a rotary swirl through an annular outlet
US2618928A (en) Combustion apparatus with vaned fuel injector means
US3527052A (en) Combustion system with aerodynamically variable geometry
US3483699A (en) Fuel injector for a gas turbine engine
US3946553A (en) Two-stage premixed combustor
US2951339A (en) Combustion chamber swirler
US2560223A (en) Double air-swirl baffle construction for fuel burners
US2632299A (en) Precombustion chamber
US3451216A (en) Combustion equipment
US3184918A (en) Cooling arrangement for crossover tubes
US2982099A (en) Fuel injection arrangement in combustion equipment for gas turbine engines
US3082603A (en) Combustion chamber with primary and secondary air flows