US3921392A - Flame tube shroud assembly for fuel injector nozzle - Google Patents

Flame tube shroud assembly for fuel injector nozzle Download PDF

Info

Publication number
US3921392A
US3921392A US485250A US48525074A US3921392A US 3921392 A US3921392 A US 3921392A US 485250 A US485250 A US 485250A US 48525074 A US48525074 A US 48525074A US 3921392 A US3921392 A US 3921392A
Authority
US
United States
Prior art keywords
flame tube
sprayer head
fuel sprayer
shroud
air
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
US485250A
Other languages
English (en)
Inventor
Eric Carr
Kenneth Mcclave
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.)
Northrop Grumman Properties Ltd
Original Assignee
Lucas Aerospace Ltd
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 Lucas Aerospace Ltd filed Critical Lucas Aerospace Ltd
Application granted granted Critical
Publication of US3921392A publication Critical patent/US3921392A/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
    • 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

Definitions

  • a fuel sprayer head is disposed with clearance in each of the first set of apertures and a shroud surrounds each fuel sprayer head.
  • Each shroud has two hollow limbs extending on opposite sides of the fuel sprayer head and a downstream end portion which interconnects downstream ends of the limbs with adjacent apertures of the second set.
  • the limbs and associated downstream end portion of each shroud have openingstherein directed towards the fuel sprayer head.
  • Each limb has an upstream opening so that air from the passage is directed into the hood to enter the flame tube via the first set of openings and around each fuel sprayer head.
  • a flame tube assembly for a gas turbine engine, said assembly including a flame tube wall, a fuel sprayer head mounted in an aperture in the flame tube wall, a clearance between the sprayer head and the wall around the aperture for flow of air, in use, from an air passage outside the flame tube wall to the interior of the flame tube, and a shroud mounted on the exterior of the flame tube wall and disposed around the said clearance, said shroud having at least one air inlet which is disposed upstream of the clearance relative to the direction of flow of air in the air passage, in use.
  • the shroud comprises two hollow limbs which extends on either side of the fuel sprayer head, each limb having an exit opening on an inner side thereof which is presented to the fuel sprayer head.
  • the shroud has a downstream end portion which opens into at least one further aperture in the flame tube wall.
  • the said downstream end portion interconnects the two hollow limbs at the downstream ends thereof, the upstream ends of the two hollow limbs each having said air inlet therein.
  • FIG. 1 is a schematic perspective view of part of the flame tube assembly for a gas turbine engine, according to the present invention.
  • FIG. 2 is a section on the line 2--2 of FIG. 1.
  • the flame tube assembly is of the annular type and includes an annular, composite flame tube wall having'a plurality of first apertures 11 therein (only one shown) and a plurality of further apertures 12 therein.
  • Each set of first apertures 11 and further apertures 12 are spaced apart circumferentially of the flame tube wall 10.
  • the apertures 11 have their axes radially disposed relative to a longitudinal axis of the flame tube assembly whilst the apertures 12 have their axes disposed substantially parallel to the longitudinal axis of the flame tube assembly.
  • a fuel sprayer head 13 of known type (see FIG. 2).
  • each shroud 17 also includes a downstream end portion 20 which interconnects the limbs 18 and 19. As can be seen best in FIG. 2, the downstream end portion 20 of each shroud 17 communicates with several of the apertures 12 in the wall 10.
  • Each of the limbs 18 and 19 is hollow and is provided with a respective air inlet 21 and 22 at its upstream end relative to the direction of air flow in passage 16.
  • each limb 18 and 19 is provided with a respective exit opening 23 and 24 in an inner side thereof which is presented to the respective fuel sprayer head 13.
  • the downstream end portion 20 of each shroud 17 has an upstream opening 25 therein which is presented to the fuel sprayer head 13 and which interconnects openings 23 and 24.
  • Each shroud l7 surrounds the clearance 14 between each fuel sprayer head 13 and the wall 10 around the respective first aperture 11.
  • each fuel sprayer head 13 serves to supply fuel into the combustion zone 15 in known manner. Air is also introduced into the combustion Zone 15 inter alia through apertures 12. In order to pass through the apertures 11 and those apertures 12 which are covered by downstream end portion 20 of hood 17, air must first pass into hood l7 and it does so by entering inlets 21 and 22 at the upstream end of hood 17. A certain amount of air passes between limbs 18 and 19 to enter the upstream end of each respective first aperture 11 beneath a cranked portion 26 of the respective fuel sprayer head 13. Some of the air entering inlets 21 and 22 in limbs 18 and 19, respectively, passes into the associated first aperture 11 via openings 23 and 24 whilst the remaining air passes into the downstream end portion 20 of the shroud 17 and from thence into the flame tube through apertures 12.
  • the provision of the shroud 17 prevents so-called torching or escape of the flame from the combustion zone 15 into the air passage 16. Furthermore, the provision of the hood 17 further assists in cooling of the associated fuel sprayer head 13.
  • a flame tube assembly for a gas turbine engine including a flame tube wall, a fuel sprayer head mounted in an aperture in said flame tube wall, a clearance between said fuel sprayer head and the wall around the aperture for flow of air from an air passage outside said flame tube wall to the interior of said flame tube, and a shroud mounted on the exterior of said flame tube wall and disposed around said clearance, said shroud comprising two hollow limbs which extend on either side of said fuel sprayer head and a downstream end portion which interconnects said two hollow limbs at downstream ends thereof, each said limb having an air inlet at the upstream end thereof which is disposed upstream of said clearance relative to the direction of flow of air in the air passage, and also having an exit opening on an inner side thereof which is presented to said fuel sprayer head.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Liquid Carbonaceous Fuels (AREA)
  • Fuel-Injection Apparatus (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
US485250A 1973-07-05 1974-07-02 Flame tube shroud assembly for fuel injector nozzle Expired - Lifetime US3921392A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3209173A GB1462368A (en) 1973-07-05 1973-07-05 Flame tube assembly

Publications (1)

Publication Number Publication Date
US3921392A true US3921392A (en) 1975-11-25

Family

ID=10333091

Family Applications (1)

Application Number Title Priority Date Filing Date
US485250A Expired - Lifetime US3921392A (en) 1973-07-05 1974-07-02 Flame tube shroud assembly for fuel injector nozzle

Country Status (6)

Country Link
US (1) US3921392A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
JP (1) JPS5323886B2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
DE (1) DE2432220C3 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
FR (1) FR2324872A1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
GB (1) GB1462368A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)
IT (1) IT1016299B (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2851859A (en) * 1952-07-16 1958-09-16 Onera (Off Nat Aerospatiale) Improvements in combustion chambers for turbo-jet, turbo-prop and similar engines
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants
US2926495A (en) * 1955-12-29 1960-03-01 Gen Electric Fuel injection nozzle
US3030774A (en) * 1959-05-14 1962-04-24 Frederick W Henning Igniter nozzle anti-coking device
US3088279A (en) * 1960-08-26 1963-05-07 Gen Electric Radial flow gas turbine power plant

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2851859A (en) * 1952-07-16 1958-09-16 Onera (Off Nat Aerospatiale) Improvements in combustion chambers for turbo-jet, turbo-prop and similar engines
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants
US2926495A (en) * 1955-12-29 1960-03-01 Gen Electric Fuel injection nozzle
US3030774A (en) * 1959-05-14 1962-04-24 Frederick W Henning Igniter nozzle anti-coking device
US3088279A (en) * 1960-08-26 1963-05-07 Gen Electric Radial flow gas turbine power plant

Also Published As

Publication number Publication date
FR2324872B1 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1978-02-17
FR2324872A1 (fr) 1977-04-15
DE2432220C3 (de) 1980-02-28
DE2432220A1 (de) 1975-01-23
DE2432220B2 (de) 1979-06-21
JPS5323886B2 (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1978-07-18
GB1462368A (en) 1977-01-26
JPS5070711A (GUID-C5D7CC26-194C-43D0-91A1-9AE8C70A9BFF.html) 1975-06-12
IT1016299B (it) 1977-05-30

Similar Documents

Publication Publication Date Title
US3869864A (en) Combustion chambers for gas turbine engines
US4870826A (en) Casing for a turbojet engine combustion chamber
US2999359A (en) Combustion equipment of gas-turbine engines
US6295801B1 (en) Fuel injector bar for gas turbine engine combustor having trapped vortex cavity
US5235805A (en) Gas turbine engine combustion chamber with oxidizer intake flow control
US6286317B1 (en) Cooling nugget for a liner of a gas turbine engine combustor having trapped vortex cavity
US5941076A (en) Deflecting feeder bowl assembly for a turbojet engine combustion chamber
US3698186A (en) Afterburner combustion apparatus
US3299632A (en) Combustion chamber for a gas turbine engine
US3316714A (en) Gas turbine engine combustion equipment
US5934067A (en) Gas turbine engine combustion chamber for optimizing the mixture of burned gases
US2977760A (en) Annular combustion chambers for use with compressors capable of discharging combustion supporting medium with a rotary swirl through an annular outlet
US3516252A (en) Fuel manifold system
GB2377487A (en) Air inlet bushes used in a combustion chamber of a gas turbine
US5653109A (en) Annular combustor with fuel manifold
US3952503A (en) Gas turbine engine combustion equipment
GB675300A (en) Improvements in or relating to exhaust ducting of gas-turbine engines
US3383855A (en) Gas turbine engine
CN110094758A (zh) 用于改进的排放和耐用性的燃烧器及运行方法
US3653207A (en) High fuel injection density combustion chamber for a gas turbine engine
US3238718A (en) Gas turbine engine
US5335491A (en) Combustion chamber with axially displaced fuel injectors
US2833115A (en) Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like
EP3832206B1 (en) Combustor for a gas turbine engine
RU2461778C2 (ru) Диффузионная камера газотурбинного двигателя, камера сгорания и содержащий их газотурбинный двигатель