US3121996A - Liquid fuel combustion apparatus - Google Patents

Liquid fuel combustion apparatus Download PDF

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Publication number
US3121996A
US3121996A US142124A US14212461A US3121996A US 3121996 A US3121996 A US 3121996A US 142124 A US142124 A US 142124A US 14212461 A US14212461 A US 14212461A US 3121996 A US3121996 A US 3121996A
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combustion chamber
air
liquid fuel
body part
combustion
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US142124A
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Smith John
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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
    • F23R3/36—Supply of different fuels
    • 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

Definitions

  • This invention relates to liquid fuel combustion apparatus of the kind comprising in combination a sheet metal combustion chamber, a casing surrounding the combustion chamber in spaced relationship to define therebetween an air jacket, a liquid fuel burner at one end of the combustion chamber, and a sWirle-r surrounding the burner and through which combustion air can be introduced :from the air jacket into the combustion chamber.
  • the object of the invention is to provide such apparatus in a convenient form having provision whereby an alternative and gaseous fuel may be used instead of liquid fuel.
  • the burner is mounted within a hollow body part to which are also connected the vanes of the siwirler, and there is formed in the body part one or more passages for the introduction of an alternative and gaseous fuel, said passage or passages being in communication with the combustion chamber.
  • FIGURE 1 is a sectional side view illustrating one example of the invention
  • FIGURE 2 is an end view, partly broken away, illustrating the burner and swirler
  • FIGURE 3 is a view similar to FIGURE 1 illustrating a modification
  • FIGURE 4 is a fragmentary section on the line 4--4 in FIGURE 3
  • PiGURE 5 is a sectional view illustrating a detail of the combustion chamber common to both examples.
  • a sheet metal combustion chamber 6 of generally cylindrical form which is surrounded in spaced relationship by a sheet metal outer casing '7 so as todefine an air jacket therebetween.
  • the casing 7 is of cylindrical form, and the combustion chamber 6 is mounted concentrically therein.
  • one part of the casing 7 (FiGURE 5) intermediate the ends of the chamber 6 is of increased diameter and has an air inlet 8 at one side, the cross-section of the casing at this part being almost cylindrical but eccentric with respect to the combustion chamber.
  • the radial depth of the air jacket is at its maximum near the inlet and diminishes from the inlet to a point diametrically opposite thereto.
  • One end of the combustion chamber is shaped to form a substantially conical flare 9 and at the centre of the flare is mounted a hollow body part '19.
  • a liquid fuel burner 12 mounted in spaced rela onship
  • the nozzle Olf which is supported within a nose piece 13 closing the inner end of the bore.
  • Air from the air jacket can enter the annular space within the bore around the burner 12 through one or more angularly spaced passages 14 in the body part it in use, such air serves to cool the burner, and is discharged to the combustion chamber through angularly spaced slots 15 in the nose piece 13, thereby serving to minimise formation of carbon on the burner nozzle.
  • a proportion of the air enters a cap 12 surrounding the nozzle.
  • the slots 15 extend at inclinations to radii of the nose piece 13, and in the latter beyond the outer ends of the slots me formed annularly arar-nged rows of gas inlet holes 16.
  • the holes 16 do not communicate with the bore 11, but are in communication with passages, or an annular passage 17 in the body part It to which a gaseous fuel such, for example, as a natural gas can be adrnitted through an inlet 18 at the outer end of the body part.
  • the swirler At the inner end of the body part is a swirler which surrounds the nose piece 13 and through which primary combustion air can be admitted from the air jacket to the combustion chamber.
  • the swirler includes a pair of spaced annular discs 19, 2d, the disc .19 being welded to a fiange 21 in the body part it ⁇ and having an inner portion 1 9 bent to cylindrical form and welded at its end to the nose piece .13 to define in part the outer side of the passage 1'7.
  • the disc 26" is welded or otherwise secured to separately formed and substantially cylindrical part 22 to which the flare 9 is connected.
  • a plurality of angularly spaced and tangentially extending vanes 23 which serve both to space and interconnect the discs 19, 2t ⁇ , and also to impart a swirling effect to the air entering the combustion chamber between the discs.
  • This scoop may take the forrn of an annular sheet metal sleeve 25 secured at its one end to the periphery of the chamber, and extending in spaced relationship relative thereto towards the flare 9 around the holes 24, and a second sheet metal and annular member 26 of substantially U cross section having one limb secured to the chamber at the inner side of the free end of the sleeve 25, and its other limb disposed at the outer side of the free end of the sleeve.
  • the action of this scoop is to cause a proportion of the air flowing the jacket towards the swirlcr to change direction and to enter the chamber through the holes 24.
  • FIG- URES 3 and 4 The modification of the invention illustrated in FIG- URES 3 and 4 is similar to that shown in FIGURES 1 and 2, and like parts have been designated with the same reference numerals.
  • piece 13 is omitted and air llows through the passage or passages 14 to the bore 111 and around the burner 1-2 to the combustion chamber.
  • each vane 23 has formed therein a bore 2'7 which communicates with the passage 17 and with three further passages 2-3. Where gaseous fuel is employed, this fuel flows through the passage 17, the bores 27, the passages 23 and the central hole in the disc 20 to the combustion chamber.
  • passages 29 are provided through which air from the air jacket can enter the combastion chamber.
  • the gas inlet can be closed and the apparatus caused to operate on liquid fuel sprayed into the combustion chamber from the burner in the normal manner.
  • this gas can be used as the fuel and fed through the gas inlet to the combustion chamber, whilst the supply of liquid fuel is interrupted.
  • Liquid fuel combustion apparatus comprising in combination a sheet metal combustion chamber, a casing surrounding said combustion chamber in spaced relationship thereto so as to define there-with an air jacket surrounding said combustion chazniber which is provided at one end with a central opening for admitting f ueland primary combustion air to the interior of said combustion chamber, a liquid fuel burner situated at said end of said combustion chamber, and provided with a discharge nozln this example, however, the nose zle which communicates through said central opening with the interior of said combustion chamber, an air swirler provided with a pair of spaced annular discs which are interconnected by a plurality of spaced vanes, and which surround said liquid fuel burner with the outer and inner peripheral portions of the space between said discs in communication respectively with said air jacket and said central opening in one end of said combustion chamber so that primary combustion air can flow from said air jacket through said air swirler to the interior of said combustion chamber, and a hollow body part to which said air swirler is secured, and in which said liquid fuel burner is mounted in spaced relationship there
  • Liquid fuel combustion apparatus having a nose piece which surrounds the discharge nozzle of said liquid fuel burner, and which is provided with holes establishing communication between said combustion chamber and the alternative and gaseous fuel passages in said hollow body part.
  • Liquid fuel combustion apparatus according to claim 1, wherein the vanes of said air swirler are formed with passages which establish communication between said combustion chamber and the alternative and gaseous fuel passage in said hollow body part.

Description

Feb. 25, 1964 J. SMITH LIQUID FUEL COMBUSTION APPARATUS 2 Sheets-Sheet 1 Filed 001;. 2, 1961 Feb. 25, 1964 J. SMITH LIQUID F-UEL COMBUSTION APPARATUS 2 Sheets-Sheet 2 Filed 001',- 2, 1961 amass Patented Feb. 25, 1964 3 121 996 LlQUll) FUEL (IOli IEESHON APPARATUS .lohn Smith, {jinn-ch, near Acerington, England, assignor to loseph Lucas (industries) Limited, Birmingham, En land Filed on. 2, ran, Ser. No. 142,124
3 Claims. (El. rill-39.74)
This invention relates to liquid fuel combustion apparatus of the kind comprising in combination a sheet metal combustion chamber, a casing surrounding the combustion chamber in spaced relationship to define therebetween an air jacket, a liquid fuel burner at one end of the combustion chamber, and a sWirle-r surrounding the burner and through which combustion air can be introduced :from the air jacket into the combustion chamber.
The object of the invention is to provide such apparatus in a convenient form having provision whereby an alternative and gaseous fuel may be used instead of liquid fuel.
Acccrdin to the invention in liquid fuel combustion apparatus of the kind specified the burner is mounted within a hollow body part to which are also connected the vanes of the siwirler, and there is formed in the body part one or more passages for the introduction of an alternative and gaseous fuel, said passage or passages being in communication with the combustion chamber.
in the accompanying drawings, FIGURE 1 is a sectional side view illustrating one example of the invention, FIGURE 2 is an end view, partly broken away, illustrating the burner and swirler, FIGURE 3 is a view similar to FIGURE 1 illustrating a modification, FIGURE 4 is a fragmentary section on the line 4--4 in FIGURE 3, and PiGURE 5 is a sectional view illustrating a detail of the combustion chamber common to both examples.
Referring first to FIGURES 1 and 2, there is provided a sheet metal combustion chamber 6 of generally cylindrical form which is surrounded in spaced relationship by a sheet metal outer casing '7 so as todefine an air jacket therebetween. The casing 7 is of cylindrical form, and the combustion chamber 6 is mounted concentrically therein. However, one part of the casing 7 (FiGURE 5) intermediate the ends of the chamber 6 is of increased diameter and has an air inlet 8 at one side, the cross-section of the casing at this part being almost cylindrical but eccentric with respect to the combustion chamber. Thus at this part the radial depth of the air jacket is at its maximum near the inlet and diminishes from the inlet to a point diametrically opposite thereto.
One end of the combustion chamber is shaped to form a substantially conical flare 9 and at the centre of the flare is mounted a hollow body part '19. Mounted in spaced rela onship Within a central bore 111 in the body part is a liquid fuel burner 12, the nozzle Olf which is supported within a nose piece 13 closing the inner end of the bore. Air from the air jacket can enter the annular space within the bore around the burner 12 through one or more angularly spaced passages 14 in the body part it in use, such air serves to cool the burner, and is discharged to the combustion chamber through angularly spaced slots 15 in the nose piece 13, thereby serving to minimise formation of carbon on the burner nozzle. Moreover, a proportion of the air enters a cap 12 surrounding the nozzle.
The slots 15 extend at inclinations to radii of the nose piece 13, and in the latter beyond the outer ends of the slots me formed annularly arar-nged rows of gas inlet holes 16. The holes 16 do not communicate with the bore 11, but are in communication with passages, or an annular passage 17 in the body part It to which a gaseous fuel such, for example, as a natural gas can be adrnitted through an inlet 18 at the outer end of the body part.
At the inner end of the body part is a swirler which surrounds the nose piece 13 and through which primary combustion air can be admitted from the air jacket to the combustion chamber. The swirler includes a pair of spaced annular discs 19, 2d, the disc .19 being welded to a fiange 21 in the body part it} and having an inner portion 1 9 bent to cylindrical form and welded at its end to the nose piece .13 to define in part the outer side of the passage 1'7. The disc 26" is welded or otherwise secured to separately formed and substantially cylindrical part 22 to which the flare 9 is connected. Secured to the adjacent faces of the pair of discs are a plurality of angularly spaced and tangentially extending vanes 23 which serve both to space and interconnect the discs 19, 2t}, and also to impart a swirling effect to the air entering the combustion chamber between the discs.
In the periphery of the combustion chamber are formed angularl' and axially spaced plunger holes 24 through which secondary combustion air and dilution air can enter the chamber from he air jacket. However, it will be understood that air in the jacket will how in contra direction to the gases in the chamber, and in order to direct the secondary combustion air into the holes 24 nearer the flare 9 a scoop is provided in the air jacket. This scoop may take the forrn of an annular sheet metal sleeve 25 secured at its one end to the periphery of the chamber, and extending in spaced relationship relative thereto towards the flare 9 around the holes 24, and a second sheet metal and annular member 26 of substantially U cross section having one limb secured to the chamber at the inner side of the free end of the sleeve 25, and its other limb disposed at the outer side of the free end of the sleeve. The action of this scoop is to cause a proportion of the air flowing the jacket towards the swirlcr to change direction and to enter the chamber through the holes 24.
The modification of the invention illustrated in FIG- URES 3 and 4 is similar to that shown in FIGURES 1 and 2, and like parts have been designated with the same reference numerals. piece 13 is omitted and air llows through the passage or passages 14 to the bore 111 and around the burner 1-2 to the combustion chamber. Further, each vane 23 has formed therein a bore 2'7 which communicates with the passage 17 and with three further passages 2-3. Where gaseous fuel is employed, this fuel flows through the passage 17, the bores 27, the passages 23 and the central hole in the disc 20 to the combustion chamber. Moreover, in this modification passages 29 are provided through which air from the air jacket can enter the combastion chamber.
By constructions as above described the gas inlet can be closed and the apparatus caused to operate on liquid fuel sprayed into the combustion chamber from the burner in the normal manner. However, if desired, where a ready source of gas is available, this gas can be used as the fuel and fed through the gas inlet to the combustion chamber, whilst the supply of liquid fuel is interrupted.
Having thus described my invention what I claim as new and desire to secure by Letters Patent is:
1. Liquid fuel combustion apparatus comprising in combination a sheet metal combustion chamber, a casing surrounding said combustion chamber in spaced relationship thereto so as to define there-with an air jacket surrounding said combustion chazniber which is provided at one end with a central opening for admitting f ueland primary combustion air to the interior of said combustion chamber, a liquid fuel burner situated at said end of said combustion chamber, and provided with a discharge nozln this example, however, the nose zle which communicates through said central opening with the interior of said combustion chamber, an air swirler provided with a pair of spaced annular discs which are interconnected by a plurality of spaced vanes, and which surround said liquid fuel burner with the outer and inner peripheral portions of the space between said discs in communication respectively with said air jacket and said central opening in one end of said combustion chamber so that primary combustion air can flow from said air jacket through said air swirler to the interior of said combustion chamber, and a hollow body part to which said air swirler is secured, and in which said liquid fuel burner is mounted in spaced relationship thereto, the space between said liquid fuel burner and said hollow body part being in communication with the interior of said combustion chamber, said hollow body part having formed therein at least one passage which communicates with said central opening in one end of said combustion chamber, and through which an alternative and gaseouse fuel can be introduced into said combustion chamber, and said hollow body part also having formed therein at least one other passage through which air from said air jacket can flow around said liquid fuel burner and into said combustion chamber.
2. Liquid fuel combustion apparatus according to claim 1, and having a nose piece which surrounds the discharge nozzle of said liquid fuel burner, and which is provided with holes establishing communication between said combustion chamber and the alternative and gaseous fuel passages in said hollow body part.
3. Liquid fuel combustion apparatus according to claim 1, wherein the vanes of said air swirler are formed with passages which establish communication between said combustion chamber and the alternative and gaseous fuel passage in said hollow body part.
References Cited in the file of this patent UNITED STATES PATENTS 2,697,191 Lee Aug. 19, 1952 2,638,745 Nathan May 19, 1953 2,680,951 Winter et a1. June 15, 1954 2,973,624 Pierce et al. Mar. 7, 1961 FOREIGN PATENTS 704,468 Great Britain Feb. 24, 1954 736,635 Great Britain Sept. 14, 1955

Claims (1)

1. LIQUID FUEL COMBUSTION APPARATUS COMPRISING IN COMBINATION A SHEET METAL COMBUSTION CHAMBER, A CASING SURROUNDING SAID COMBUSTION CHAMBER IN SPACED RELATIONSHIP THERETO SO AS TO DEFINE THEREWITH AN AIR JACKET SURROUNDING SAID COMBUSTION CHAMBER WHICH IS PROVIDED AT ONE END WITH A CENTRAL OPENING FOR ADMITTING FUEL AND PRIMARY COMBUSTION AIR TO THE INTERIOR OF SAID COMBUSTION CHAMBER, A LIQUID FUEL BURNER SITUATED AT SAID END OF SAID COMBUSTION CHAMBER, AND PROVIDED WITH A DISCHARGE NOZZLE WHICH COMMUNICATES THROUGH SAID CENTRAL OPENING WITH THE INTERIOR OF SAID COMBUSTION CHAMBER, AN AIR SWIRLER PROVIDED WITH A PAIR OF SPACED ANNULAR DISCS WHICH ARE INTERCONNECTED BY A PLURALITY OF SPACED VANES, AND WHICH SURROUND SAID LIQUID FUEL BURNER WITH THE OUTER AND INNER PERIPHERAL PORTIONS OF THE SPACE BETWEEN SAID DISCS IN COMMUNICATION RESPECTIVELY WITH SAID AIR JACKET AND SAID CENTRAL OPENING IN ONE END OF SAID COMBUSTION CHAMBER SO THAT PRIMARY COMBUSTION AIR CAN FLOW FROM SAID AIR JACKET THROUGH SAID AIR SWIRLER TO THE INTERIOR OF SAID COMBUSTION CHAMBER, AND A HOLLOW BODY PART TO WHICH SAID AIR SWIRLER IS SECURED, AND IN WHICH SAID LIQUID FUEL BURNER IS MOUNTED IN SPACED RELATIONSHIP THERETO, THE SPACE BETWEEN SAID LIQUID FUEL BURNER AND SAID HOLLOW BODY PART BEING IN COMMUNICATION WITH THE INTERIOR OF SAID COMBUSTION CHAMBER, SAID HOLLOW BODY PART HAVING FORMED THEREIN AT LEAST ONE PASSAGE WHICH COMMUNICATES WITH SAID CENTRAL OPENING IN ONE END OF SAID COMBUSTION CHAMBER, AND THROUGH WHICH AN ALTERNATIVE AND GASEOUS FUEL CAN BE INTRODUCED INTO SAID COMBUSTION CHAMBER, AND SAID HOLLOW BODY PART ALSO HAVING FORMED THEREIN AT LEAST ONE OTHER PASSAGE THROUGH WHICH AIR FROM SAID AIR JACKET CAN FLOW AROUND SAID LIQUID FUEL BURNER AND INTO SAID COMBUSTION CHAMBER.
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Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3667221A (en) * 1969-04-17 1972-06-06 Gen Electric Fuel delivery apparatus
US3741483A (en) * 1971-12-10 1973-06-26 Mitsubishi Heavy Ind Ltd Combustion air supply arrangement for gas turbines
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3845620A (en) * 1973-02-12 1974-11-05 Gen Electric Cooling film promoter for combustion chambers
US3899882A (en) * 1974-03-27 1975-08-19 Westinghouse Electric Corp Gas turbine combustor basket cooling
JPS50133312A (en) * 1974-04-10 1975-10-22
US3952503A (en) * 1973-03-20 1976-04-27 Rolls-Royce (1971) Limited Gas turbine engine combustion equipment
FR2336555A1 (en) * 1975-12-24 1977-07-22 Gen Electric PERFECTED CARBURATION SYSTEM FOR GAS TURBINE
US4050238A (en) * 1975-03-14 1977-09-27 Daimler-Benz Aktiengesellschaft Film evaporating combustion chamber
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
FR2418867A1 (en) * 1978-03-01 1979-09-28 Gen Electric LOW CALORIFIC GAS COMBUSTION CHAMBER
US4343148A (en) * 1980-03-07 1982-08-10 Solar Turbines Incorporated Liquid fueled combustors with rotary cup atomizers
US4343147A (en) * 1980-03-07 1982-08-10 Solar Turbines Incorporated Combustors and combustion systems
DE3203342A1 (en) * 1981-02-03 1982-08-12 Nissan Motor Co., Ltd., Yokohama, Kanagawa Air duct to an injection valve for a gas turbine
FR2505401A1 (en) * 1981-05-11 1982-11-12 Rolls Royce IMPROVED ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
US6094916A (en) * 1995-06-05 2000-08-01 Allison Engine Company Dry low oxides of nitrogen lean premix module for industrial gas turbine engines
US20040211186A1 (en) * 2003-04-28 2004-10-28 Stuttaford Peter J. Flamesheet combustor
WO2008019997A1 (en) * 2006-08-16 2008-02-21 Siemens Aktiengesellschaft Swirler passage and burner for a gas turbine engine
US20090151357A1 (en) * 2007-12-14 2009-06-18 Snecma System for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20110271682A1 (en) * 2009-01-16 2011-11-10 Snecma Device for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20150113994A1 (en) * 2013-03-12 2015-04-30 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US20180209654A1 (en) * 2017-01-23 2018-07-26 Man Diesel & Turbo Se Combustion chamber of a gas turbine, gas turbine and method for operating the same
US20190003712A1 (en) * 2017-06-28 2019-01-03 Man Diesel & Turbo Se Combustion chamber of a gas turbine, gas turbine and method for operating the same
GB2578823B (en) * 2018-10-18 2021-11-03 Man Energy Solutions Se Dual fuel combustion chamber of a gas turbine

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US2607191A (en) * 1947-11-28 1952-08-19 United Aircraft Corp Vortex producing mechanism for mixing combustion chamber fluids
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
GB704468A (en) * 1951-03-22 1954-02-24 Gasturbine Mij N V Improvements in or relating to combustion chambers for liquid, gaseous or pulverisedsolid fuels
US2680951A (en) * 1948-01-02 1954-06-15 Power Jets Res & Dev Ltd Combustion apparatus for burning particles of solid or heavy liquid fuel in a fast moving stream
GB736635A (en) * 1953-06-25 1955-09-14 Lucas Industries Ltd Liquid fuel combustion apparatus
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US2607191A (en) * 1947-11-28 1952-08-19 United Aircraft Corp Vortex producing mechanism for mixing combustion chamber fluids
US2680951A (en) * 1948-01-02 1954-06-15 Power Jets Res & Dev Ltd Combustion apparatus for burning particles of solid or heavy liquid fuel in a fast moving stream
GB704468A (en) * 1951-03-22 1954-02-24 Gasturbine Mij N V Improvements in or relating to combustion chambers for liquid, gaseous or pulverisedsolid fuels
GB736635A (en) * 1953-06-25 1955-09-14 Lucas Industries Ltd Liquid fuel combustion apparatus
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners

Cited By (35)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3667221A (en) * 1969-04-17 1972-06-06 Gen Electric Fuel delivery apparatus
US3741483A (en) * 1971-12-10 1973-06-26 Mitsubishi Heavy Ind Ltd Combustion air supply arrangement for gas turbines
US3777983A (en) * 1971-12-16 1973-12-11 Gen Electric Gas cooled dual fuel air atomized fuel nozzle
US3845620A (en) * 1973-02-12 1974-11-05 Gen Electric Cooling film promoter for combustion chambers
US3952503A (en) * 1973-03-20 1976-04-27 Rolls-Royce (1971) Limited Gas turbine engine combustion equipment
US3899882A (en) * 1974-03-27 1975-08-19 Westinghouse Electric Corp Gas turbine combustor basket cooling
JPS50133312A (en) * 1974-04-10 1975-10-22
US4050238A (en) * 1975-03-14 1977-09-27 Daimler-Benz Aktiengesellschaft Film evaporating combustion chamber
FR2336555A1 (en) * 1975-12-24 1977-07-22 Gen Electric PERFECTED CARBURATION SYSTEM FOR GAS TURBINE
US4155220A (en) * 1977-01-21 1979-05-22 Westinghouse Electric Corp. Combustion apparatus for a gas turbine engine
FR2418867A1 (en) * 1978-03-01 1979-09-28 Gen Electric LOW CALORIFIC GAS COMBUSTION CHAMBER
US4343148A (en) * 1980-03-07 1982-08-10 Solar Turbines Incorporated Liquid fueled combustors with rotary cup atomizers
US4343147A (en) * 1980-03-07 1982-08-10 Solar Turbines Incorporated Combustors and combustion systems
DE3203342A1 (en) * 1981-02-03 1982-08-12 Nissan Motor Co., Ltd., Yokohama, Kanagawa Air duct to an injection valve for a gas turbine
US4466250A (en) * 1981-02-03 1984-08-21 Nissan Motor Company, Limited Air passageway to air injection valve for gas turbine engine
FR2505401A1 (en) * 1981-05-11 1982-11-12 Rolls Royce IMPROVED ANNULAR COMBUSTION CHAMBER FOR A GAS TURBINE ENGINE
US6094916A (en) * 1995-06-05 2000-08-01 Allison Engine Company Dry low oxides of nitrogen lean premix module for industrial gas turbine engines
US6935116B2 (en) * 2003-04-28 2005-08-30 Power Systems Mfg., Llc Flamesheet combustor
US20040211186A1 (en) * 2003-04-28 2004-10-28 Stuttaford Peter J. Flamesheet combustor
US8181464B2 (en) 2006-08-16 2012-05-22 Siemens Aktiengesellschaft Swirler with concentric fuel and air tubes for a gas turbine engine
WO2008019997A1 (en) * 2006-08-16 2008-02-21 Siemens Aktiengesellschaft Swirler passage and burner for a gas turbine engine
EP1892469A1 (en) * 2006-08-16 2008-02-27 Siemens Aktiengesellschaft Swirler passage and burner for a gas turbine engine
US20090277179A1 (en) * 2006-08-16 2009-11-12 Nigel Wilbraham Swirler passage and burner for a gas turbine engine
US8312723B2 (en) * 2007-12-14 2012-11-20 Snecma System for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20090151357A1 (en) * 2007-12-14 2009-06-18 Snecma System for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20110271682A1 (en) * 2009-01-16 2011-11-10 Snecma Device for injecting a mixture of air and fuel into a turbomachine combustion chamber
US8590312B2 (en) * 2009-01-16 2013-11-26 Snecma Device for injecting a mixture of air and fuel into a turbomachine combustion chamber
US20150113994A1 (en) * 2013-03-12 2015-04-30 Pratt & Whitney Canada Corp. Combustor for gas turbine engine
US10378774B2 (en) * 2013-03-12 2019-08-13 Pratt & Whitney Canada Corp. Annular combustor with scoop ring for gas turbine engine
US20180209654A1 (en) * 2017-01-23 2018-07-26 Man Diesel & Turbo Se Combustion chamber of a gas turbine, gas turbine and method for operating the same
JP2018119780A (en) * 2017-01-23 2018-08-02 マン・ディーゼル・アンド・ターボ・エスイー Combustion chamber for gas turbine, gas turbine and operating method for gas turbine
EP3351854B1 (en) * 2017-01-23 2021-08-04 MAN Energy Solutions SE Combustion chamber of a gas turbine, gas turbine and method for operating the same
US20190003712A1 (en) * 2017-06-28 2019-01-03 Man Diesel & Turbo Se Combustion chamber of a gas turbine, gas turbine and method for operating the same
EP3421885B1 (en) * 2017-06-28 2022-12-21 MAN Energy Solutions SE Combustion chamber of a gas turbine, gas turbine and method for operating the same
GB2578823B (en) * 2018-10-18 2021-11-03 Man Energy Solutions Se Dual fuel combustion chamber of a gas turbine

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