US3458997A - Supports for fuel burners - Google Patents

Supports for fuel burners Download PDF

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Publication number
US3458997A
US3458997A US661268A US3458997DA US3458997A US 3458997 A US3458997 A US 3458997A US 661268 A US661268 A US 661268A US 3458997D A US3458997D A US 3458997DA US 3458997 A US3458997 A US 3458997A
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United States
Prior art keywords
burner
swirler
supports
combustion chamber
fuel burners
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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
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US661268A
Inventor
Peter Joseph Clark
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ZF International UK Ltd
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Lucas Industries Ltd
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    • 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
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • 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
    • F23R3/36—Supply of different fuels

Definitions

  • a gas turbine engine burner for gas or liquid fuel has an inner passage for liquid fuel surrounded by an annular passage for gas, the burner being mounted in the engine by part-spherical bearings, that at the downstream end being mounted to permit of lengthwise movement of the burner end in the engine to accommodate expansion.
  • This invention relates to fuel burners and to support means therefor, the object being to provide such a burner in a convenient form.
  • a burner is provided with means for supporting it in a structure at two spaced positions lengthwise thereof, comprising a pair of part spherical bearings at said positions respectively, one of the bearings being connected to the burner so as to permit of lengthwise movement of the burner relatively to the structure.
  • FIGURE 1 illustrates in cross-section a burner supported in a gas turbine engine in a manner in accordance with the invention
  • FIGURE 2 is an enlarged view of one end of the burner.
  • the burner illustrated is arranged for the supply of liquid fuel or alternatively gaseous fuel to combustion apparatus of a gas turbine engine.
  • the engine shown has an annular combustion chamber 1 defined by inner and outer walls 2, 3 made up from a plurality of interconnected sections.
  • the chamber 1 is enclosed within an annular air jacket which is defined by inner and outer walls 4, 5.
  • the upstream ends of the air jacket walls 4, are spaced to provide a path for the entry of a proportion of the air within the outer casing and some of this can enter the chamber, as Well as through a swirler 8 at the upstream end of the combustion chamber 1.
  • Attached to the swirler 8 is an annular flare plate 9 forming the upstream wall of the combustion chamber 1. This is attached at its inner and outer edges to the walls 2, 3 of the chamber 1, and there is also an air entry nose piece 9a secured by its inner and outer edges to the combustion chamber walls 2, 3.
  • the burner comprises an inner tubular member 10 through which liquid fuel is intended to be supplied, and inner and outer concentric tubular parts 11, 12 between which gaseous fuel is intended to be supplied.
  • the liquid fuel from the member 10 can be discharged into the combustion chamber 1 from a nozzle 13, and the gaseous fuel can be discharged into the combustion chamber 1 through a plurality of angularly spaced inclined openings 14 formed in a part 15, surrounding the nozzle 13. This part 15 also serves to interconnect the inner and outer parts 11, 12 at their downstream ends.
  • the face of the member 15 between the nozzle 13 and the openings 14 is provided with a plurality of slots 16 arranged at inclined angles to a radial plane at this face, these slots 16 communicating with the space defined between the inner tubular member 10 and the inner tubular part 11. Air enters this space through a radially extending opening 17, this opening being formed in a body 18 to which the upstream ends of the parts 11, 12 are connected. The air is given a swirling motion as it flows through the slots 16 into the combustion chamber 1.
  • passages 19 Through the body 18 extend a plurality of angularly spaced passages 19, which are off-set from the axis of the body which is concentric with the member 10 and parts 11, 12.
  • the passages 19? one of which is shown, communicate through drillings 19a with an annular gallery 10 formed in a part 21 connected to the body 18, the outer boundary of the gallery being defined by a part 22 having an inlet 23 for gaseous fuel.
  • the opposite ends of the passages 19 communicate with the space defined between the inner and outer tubular parts 11, 12.
  • the inner tubular member 10 and the inner and outer tubular parts 11, 12 are sufliciently long to afford a lengthwise spacing between the body 18 r and the member 15 of approximately eleven inches in the present example, and the region surrounding the outer tubular part 12 is that to which the air is admitted.
  • the opening 17 also communicates with this region.
  • the swirler 8 fixed in the flare plate 9 of the engine forms a support for the downstream end of the burner, support being through a part-spherical bearing member 24, which engages the external cylindrical surface of the member 15 to permit lengthwise movement of the burner through the swirler 8 in order to accommodate lengthwire expansion pf the burner.
  • the body 18 has a part-spherical bearing portion 25 engaging a part 26 mounted by a locking nut 27 in an externally flanged sleeve 28 mounted on the outer casing 6 of the engine.
  • a compressible seal 29 is provided between the body 18 and the part 26 which is held in place by the nut 27.
  • This nut also holds the bearing portion 25 against a further complementarily shaped part 30 abutting against a shoulder of the sleeve 28.
  • This part of the outer casing 6 is substantially upstream from the combustion chamber 1, as shown.
  • the sleeve 28 is mounted on the casing 6 by pins 31 and bolts (not shown), the pins being secured in the casing 6, and the sleeve 28 is provided with substantial clearance over the body 18 so that limited movement of these parts about the part spherical bearing can take place.
  • a pin 32 engaging a slot 33 in the sleeve 28 prevents relative angular movement between the sleeve 28 and the body 18.
  • a burner assembly comprising an elongated burner providing passages for fuel to be ejected, support means whereby the burner can be supported in a structure, said support means comprising a part spherical bearing disposed between the burner and the structure near one end of the burner, said bearing being fixed to the burner as well as to the structure, and a further part spherical bearing disposed between the burner and the structure near the other end of the burner, the further bearing being fixed to the structure and connected to the burner to permit relative movement lengthwise of the burner to take place.
  • a burner assembly as claimed in claim 1 in which a swirler is mounted in the structure, said further part spherical bearing being disposed between the swirler and 3 4 the burner, to permit relative lengthwise movement be- 2,965,303 12/1960 Jackson 239-132 tween the burner and the swirler and structure. 3,159,971 12/1964 Moebius et a1. 6039.74 3,320,744 5/1967 Blakely et a1. 60-3974 References Cited 2,675,864 4/1954 Seaver 1226.5 1 2,907,527 10/1959 Cummings 239135 431-139

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Superconductor Devices And Manufacturing Methods Thereof (AREA)
  • Spray-Type Burners (AREA)

Description

Aug. 5, 1969 P. J. CLARK SUPPORTS FOR FUEL BURNERS Filed Aug. 17, 1967 lllllllllllllll United States Patent US. Cl. 6039.74 2 Claims ABSTRACT OF THE DISCLOSURE A gas turbine engine burner for gas or liquid fuel has an inner passage for liquid fuel surrounded by an annular passage for gas, the burner being mounted in the engine by part-spherical bearings, that at the downstream end being mounted to permit of lengthwise movement of the burner end in the engine to accommodate expansion.
This invention relates to fuel burners and to support means therefor, the object being to provide such a burner in a convenient form.
In accordance with the present invention a burner is provided with means for supporting it in a structure at two spaced positions lengthwise thereof, comprising a pair of part spherical bearings at said positions respectively, one of the bearings being connected to the burner so as to permit of lengthwise movement of the burner relatively to the structure.
The invention will now be described with reference to the accompanying drawings, in which FIGURE 1 illustrates in cross-section a burner supported in a gas turbine engine in a manner in accordance with the invention, and FIGURE 2 is an enlarged view of one end of the burner.
The burner illustrated is arranged for the supply of liquid fuel or alternatively gaseous fuel to combustion apparatus of a gas turbine engine. The engine shown has an annular combustion chamber 1 defined by inner and outer walls 2, 3 made up from a plurality of interconnected sections. The chamber 1 is enclosed within an annular air jacket which is defined by inner and outer walls 4, 5. There is also an outer casing 6 to the interior of which air is admitted at the upstream end in a manner not shown.
The upstream ends of the air jacket walls 4, are spaced to provide a path for the entry of a proportion of the air within the outer casing and some of this can enter the chamber, as Well as through a swirler 8 at the upstream end of the combustion chamber 1. Attached to the swirler 8 is an annular flare plate 9 forming the upstream wall of the combustion chamber 1. This is attached at its inner and outer edges to the walls 2, 3 of the chamber 1, and there is also an air entry nose piece 9a secured by its inner and outer edges to the combustion chamber walls 2, 3.
Supported upon the outer casing 6 and also within the swirler 8 are a plurality of equi-angularly spaced elongated burners, one of which is shown in cross-section in the drawing.
The burner comprises an inner tubular member 10 through which liquid fuel is intended to be supplied, and inner and outer concentric tubular parts 11, 12 between which gaseous fuel is intended to be supplied. The liquid fuel from the member 10 can be discharged into the combustion chamber 1 from a nozzle 13, and the gaseous fuel can be discharged into the combustion chamber 1 through a plurality of angularly spaced inclined openings 14 formed in a part 15, surrounding the nozzle 13. This part 15 also serves to interconnect the inner and outer parts 11, 12 at their downstream ends.
The face of the member 15 between the nozzle 13 and the openings 14 is provided with a plurality of slots 16 arranged at inclined angles to a radial plane at this face, these slots 16 communicating with the space defined between the inner tubular member 10 and the inner tubular part 11. Air enters this space through a radially extending opening 17, this opening being formed in a body 18 to which the upstream ends of the parts 11, 12 are connected. The air is given a swirling motion as it flows through the slots 16 into the combustion chamber 1.
Through the body 18 extend a plurality of angularly spaced passages 19, which are off-set from the axis of the body which is concentric with the member 10 and parts 11, 12. The passages 19?, one of which is shown, communicate through drillings 19a with an annular gallery 10 formed in a part 21 connected to the body 18, the outer boundary of the gallery being defined by a part 22 having an inlet 23 for gaseous fuel. The opposite ends of the passages 19 communicate with the space defined between the inner and outer tubular parts 11, 12.
It is to be noted that the inner tubular member 10 and the inner and outer tubular parts 11, 12 are sufliciently long to afford a lengthwise spacing between the body 18 r and the member 15 of approximately eleven inches in the present example, and the region surrounding the outer tubular part 12 is that to which the air is admitted. The opening 17 also communicates with this region.
The swirler 8 fixed in the flare plate 9 of the engine forms a support for the downstream end of the burner, support being through a part-spherical bearing member 24, which engages the external cylindrical surface of the member 15 to permit lengthwise movement of the burner through the swirler 8 in order to accommodate lengthwire expansion pf the burner.
The body 18 has a part-spherical bearing portion 25 engaging a part 26 mounted by a locking nut 27 in an externally flanged sleeve 28 mounted on the outer casing 6 of the engine. A compressible seal 29 is provided between the body 18 and the part 26 which is held in place by the nut 27. This nut also holds the bearing portion 25 against a further complementarily shaped part 30 abutting against a shoulder of the sleeve 28. This part of the outer casing 6 is substantially upstream from the combustion chamber 1, as shown.
The sleeve 28 is mounted on the casing 6 by pins 31 and bolts (not shown), the pins being secured in the casing 6, and the sleeve 28 is provided with substantial clearance over the body 18 so that limited movement of these parts about the part spherical bearing can take place. A pin 32 engaging a slot 33 in the sleeve 28 prevents relative angular movement between the sleeve 28 and the body 18.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
1. A burner assembly comprising an elongated burner providing passages for fuel to be ejected, support means whereby the burner can be supported in a structure, said support means comprising a part spherical bearing disposed between the burner and the structure near one end of the burner, said bearing being fixed to the burner as well as to the structure, and a further part spherical bearing disposed between the burner and the structure near the other end of the burner, the further bearing being fixed to the structure and connected to the burner to permit relative movement lengthwise of the burner to take place.
2. A burner assembly as claimed in claim 1 in which a swirler is mounted in the structure, said further part spherical bearing being disposed between the swirler and 3 4 the burner, to permit relative lengthwise movement be- 2,965,303 12/1960 Jackson 239-132 tween the burner and the swirler and structure. 3,159,971 12/1964 Moebius et a1. 6039.74 3,320,744 5/1967 Blakely et a1. 60-3974 References Cited 2,675,864 4/1954 Seaver 1226.5 1 2,907,527 10/1959 Cummings 239135 431-139
US661268A 1966-08-18 1967-08-17 Supports for fuel burners Expired - Lifetime US3458997A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB37035/66A GB1127637A (en) 1966-08-18 1966-08-18 Supports for fuel burners

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US3458997A true US3458997A (en) 1969-08-05

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US661268A Expired - Lifetime US3458997A (en) 1966-08-18 1967-08-17 Supports for fuel burners

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US (1) US3458997A (en)
BE (1) BE702833A (en)
DE (1) DE1601598A1 (en)
GB (1) GB1127637A (en)
NL (1) NL6711357A (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3854285A (en) * 1973-02-26 1974-12-17 Gen Electric Combustor dome assembly
US3879940A (en) * 1973-07-30 1975-04-29 Gen Electric Gas turbine engine fuel delivery tube assembly
US4082499A (en) * 1976-11-12 1978-04-04 Allis-Chalmers Corporation Multipurpose kiln shell gas burner
WO1980000593A1 (en) * 1978-09-15 1980-04-03 Caterpillar Tractor Co Dual fluid fuel nozzle
US4229944A (en) * 1977-03-11 1980-10-28 Motoren- Und Turbinen-Union Munchen Gmbh Fuel injection nozzle assembly for gas turbine drive
US4451230A (en) * 1980-06-06 1984-05-29 Italimpianti Societa Impianti P.A. Radiant flat flame burner
US5292244A (en) * 1992-04-10 1994-03-08 Institute Of Gas Technology Premixed fuel/air burner
EP1584867A2 (en) * 2004-04-09 2005-10-12 Delavan Inc. Alignment and positioning system for installing a fuel injector in a gas turbine engine
US20060207258A1 (en) * 2005-03-21 2006-09-21 Tanner Keith M Fuel injector bearing plate assembly and swirler assembly
US20080066720A1 (en) * 2006-09-14 2008-03-20 James Scott Piper Gas turbine fuel injector with a removable pilot assembly
WO2009055045A2 (en) * 2007-10-26 2009-04-30 Solar Turbines Incorporated Gas turbine fuel injector with removable pilot liquid tube
US20110162372A1 (en) * 2010-01-05 2011-07-07 General Electric Company Integral flange connection fuel nozzle body for gas turbine
US10408456B2 (en) * 2015-10-29 2019-09-10 Rolls-Royce Plc Combustion chamber assembly

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4454711A (en) * 1981-10-29 1984-06-19 Avco Corporation Self-aligning fuel nozzle assembly
US4903476A (en) * 1988-12-27 1990-02-27 General Electric Company Gas turbine igniter with ball-joint support
US5415000A (en) * 1994-06-13 1995-05-16 Westinghouse Electric Corporation Low NOx combustor retro-fit system for gas turbines

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2675864A (en) * 1950-03-15 1954-04-20 Jay J Seaver Burner for open-hearth furnaces
US2907527A (en) * 1956-04-10 1959-10-06 Thompson Ramo Wooldridge Inc Nozzle
US2965303A (en) * 1959-03-30 1960-12-20 United Aircraft Corp Coolant injection in a fuel nozzle
US3159971A (en) * 1961-02-24 1964-12-08 Parker Hannifin Corp Resilient nozzle mount
US3320744A (en) * 1965-11-15 1967-05-23 Sonic Dev Corp Gas turbine engine burner

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2675864A (en) * 1950-03-15 1954-04-20 Jay J Seaver Burner for open-hearth furnaces
US2907527A (en) * 1956-04-10 1959-10-06 Thompson Ramo Wooldridge Inc Nozzle
US2965303A (en) * 1959-03-30 1960-12-20 United Aircraft Corp Coolant injection in a fuel nozzle
US3159971A (en) * 1961-02-24 1964-12-08 Parker Hannifin Corp Resilient nozzle mount
US3320744A (en) * 1965-11-15 1967-05-23 Sonic Dev Corp Gas turbine engine burner

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3854285A (en) * 1973-02-26 1974-12-17 Gen Electric Combustor dome assembly
US3879940A (en) * 1973-07-30 1975-04-29 Gen Electric Gas turbine engine fuel delivery tube assembly
US4082499A (en) * 1976-11-12 1978-04-04 Allis-Chalmers Corporation Multipurpose kiln shell gas burner
US4229944A (en) * 1977-03-11 1980-10-28 Motoren- Und Turbinen-Union Munchen Gmbh Fuel injection nozzle assembly for gas turbine drive
WO1980000593A1 (en) * 1978-09-15 1980-04-03 Caterpillar Tractor Co Dual fluid fuel nozzle
US4258544A (en) * 1978-09-15 1981-03-31 Caterpillar Tractor Co. Dual fluid fuel nozzle
US4451230A (en) * 1980-06-06 1984-05-29 Italimpianti Societa Impianti P.A. Radiant flat flame burner
US5292244A (en) * 1992-04-10 1994-03-08 Institute Of Gas Technology Premixed fuel/air burner
US7356994B2 (en) 2004-04-09 2008-04-15 Delavan Inc Alignment and positioning system for installing a fuel injector in a gas turbine engine
EP1584867A3 (en) * 2004-04-09 2006-05-17 Delavan Inc. Alignment and positioning system for installing a fuel injector in a gas turbine engine
EP1584867A2 (en) * 2004-04-09 2005-10-12 Delavan Inc. Alignment and positioning system for installing a fuel injector in a gas turbine engine
US20050223709A1 (en) * 2004-04-09 2005-10-13 Delavan Inc. Alignment and positioning system for installing a fuel injector in a gas turbine engine
US20060207258A1 (en) * 2005-03-21 2006-09-21 Tanner Keith M Fuel injector bearing plate assembly and swirler assembly
EP1710503A1 (en) * 2005-03-21 2006-10-11 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US8726667B2 (en) 2005-03-21 2014-05-20 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US7628019B2 (en) 2005-03-21 2009-12-08 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US8291706B2 (en) 2005-03-21 2012-10-23 United Technologies Corporation Fuel injector bearing plate assembly and swirler assembly
US8166763B2 (en) 2006-09-14 2012-05-01 Solar Turbines Inc. Gas turbine fuel injector with a removable pilot assembly
US20080066720A1 (en) * 2006-09-14 2008-03-20 James Scott Piper Gas turbine fuel injector with a removable pilot assembly
EP2212622A2 (en) * 2007-10-26 2010-08-04 Solar Turbines Incorporated Gas turbine fuel injector with removable pilot liquid tube
CN101939593B (en) * 2007-10-26 2012-10-03 索拉透平公司 Gas turbine fuel injector with removable pilot liquid tube
US8286433B2 (en) 2007-10-26 2012-10-16 Solar Turbines Inc. Gas turbine fuel injector with removable pilot liquid tube
WO2009055045A3 (en) * 2007-10-26 2010-08-26 Solar Turbines Incorporated Gas turbine fuel injector with removable pilot liquid tube
RU2468296C2 (en) * 2007-10-26 2012-11-27 Соулар Тёрбинз Инкорпорейтед Fuel injector of gas turbine engine with removable auxiliary liquid fuel pipe
WO2009055045A2 (en) * 2007-10-26 2009-04-30 Solar Turbines Incorporated Gas turbine fuel injector with removable pilot liquid tube
US20110162372A1 (en) * 2010-01-05 2011-07-07 General Electric Company Integral flange connection fuel nozzle body for gas turbine
US8661823B2 (en) * 2010-01-05 2014-03-04 General Electric Company Integral flange connection fuel nozzle body for gas turbine
US10408456B2 (en) * 2015-10-29 2019-09-10 Rolls-Royce Plc Combustion chamber assembly

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Publication number Publication date
BE702833A (en) 1968-01-15
GB1127637A (en) 1968-09-18
NL6711357A (en) 1968-02-19
DE1601598A1 (en) 1970-08-27

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