US3913318A - Gas turbine engine combustion equipment - Google Patents

Gas turbine engine combustion equipment Download PDF

Info

Publication number
US3913318A
US3913318A US386633A US38663373A US3913318A US 3913318 A US3913318 A US 3913318A US 386633 A US386633 A US 386633A US 38663373 A US38663373 A US 38663373A US 3913318 A US3913318 A US 3913318A
Authority
US
United States
Prior art keywords
air
stem
fuel
vaporizer
hollow stem
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
US386633A
Inventor
Roger Geoffrey Fox
Vernon Frederick Cox
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce 1971 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 Rolls Royce 1971 Ltd filed Critical Rolls Royce 1971 Ltd
Application granted granted Critical
Publication of US3913318A publication Critical patent/US3913318A/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
    • F23R3/30—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices
    • F23R3/32—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply comprising fuel prevapourising devices being tubular

Definitions

  • FIG. 5 is a diagrammatic representation of FIG. 5.
  • the present invention relates to fuel vaporizers for use in gas turbine engines.
  • Fuel vaporizers which are well known, have a hollow cylindrical stem which is adapted to be supplied with fuel and air at one end and to deliver a vaporized mixture of air and fuel from one or other ends.
  • the vaporizer may have one or more branches at the other end thereof which extend substantially radially of the stem and in order to cool such vaporizers in the past, the stem has been surrounded by a shroud which was spaced therefrom to provide an annular space for providing an air flow between the shroud and the stem, the air passing axially from the end of the space.
  • the invention could be applied to an unshrouded vaporizer in that some of the air supplied to the vaporizer stem would, before mixing with the fuel, be allowed to pass substantially radially from the stem through holes in the stem.
  • a vaporizer for a gas turbine engine designed to receive air and fuel separately and to mix them together, said vaporizer having a hollow stern, into which the air and the fuel are separately delivered, and having means, which in operation of the vaporizer, allow air, but not fuel, to pass out of the vaporizer in a direction substantially radially of the stern.
  • the vaporizer is provided with a cylindrical shroud surrounding, and radially spaced from, the stem thereof to define an annular space for receiving a supply of air, and wherein said means are holes provided in the cylindrical surface of the shroud through which air passes out of the annular space in a direction substantially radially of the stem.
  • said means are holes provided in the surface of the stem and through which some of the air supplied to the hollow stem passes out of the stem, before mixture with the fuel, in a direction substantially radially of the stem.
  • the vaporizer may have one or two branches at one end of the stem and which extends substantially radially of the stem, the vaporizer thus having an L- or T-shape.
  • FIG. 1 is a diagrammatic view of a gas turbine engine
  • FIG. 2 is a section through the combustion chamber of the engine of HO. 1 showing the vaporizers in more detail
  • FlG. 3 is a sectional plan view of a vaporizer of FIG.
  • FIG. 4 is a sectional plan view of a second vaporizer
  • HO. 5 is a sectional plan view of a third vaporizer.
  • FIG. I a gas turbine engine having a compressor 2, combustion equipment 4, a turbine 6 and a propulsion nozzle 8 all in flow series.
  • the combustion equipment comprises an outer casing 10 and an annular flame tube 12 (FIG. 2).
  • Air is supplied to the flame tube from a compressor delivery duct 3, some of the air passing directly into the flame tube through vaporizers 14, whilst the majority of the air supplied passes into the space 16 between the flame tube and the outer casing, and from there passes into the flame tube through apertures 18 into the wall thereof.
  • Fuel supply pipes 20 supply fuel to the vaporizers where it is mixed with the air and vaporized due to the heat in the surrounding gas in the flame tube.
  • the vaporizers 14 are of substantially T-section, each of which has a cylindrical stem 22 which is connected to the flame tube at one end and radial branches 24 at the free end thereof.
  • each vaporizer Surrounding the stem of each vaporizer is a shroud 26 which is radially spaced from the stem to define an annular passage 28 which is supplied with air from the compressor delivery duct 3. The downstream end of the annular passage is blocked and holes 30 are formed in the shroud to allow the air to emerge substantially radially of the stem as shown by arrows 29.
  • Cooling air is prevented from flowing axially over the radial branches of the T vaporizer, and this prevents a flame from stabilizing of the vaporizer downstreams of the radial branch in the air flow.
  • the holes 30 are positioned, so that there is no impingement of the air flowing through them on the branches.
  • weirs 32 are provided within the stem at the junctions with the radial branches of the vapouriser for creating turbulence in the fuel/air mixture in the branches. This promotes cooling of the branches.
  • the vaporizer 40 shown in FIG. 4 is similar to the one shown in FIGS. 2 and 3 except that the radial arms 24 are replaced by an umbrella 37 which is supported from the stem 22 by struts 38 to form an annular outlet 39.
  • the effect of the umbrella is similar to that of the radial branches 24 in that the air and fuel mixture is emitted from the annular outlet 39.
  • the radial flow of air through the holes 30 promotes further mixing of fuel and air in the primary combustion zone.
  • the vaporizer 40 is mounted from the flame tube 12 in the same manner as is shown in FIG. 2.
  • the vaporizer 31 shown in FIG. 5 is similar to the vapouriser 14 shown in FIGS. 2 and 3 except that it is not prmidctl with a shroud 26 and there is a suhstan tiall; radial outflow oiair through the holes in the stem 22.
  • the fuel supply pipe projects into the stem :1 sufficient distance downstream of the holes 35 in order that fuel and fuel vapor does not How out of the holes 35.
  • the radial flow of air through the holes 35 promotes Further mixing of fuel and air in the primary cornhustion 7one.
  • the vaporizers 14 and shown in FIGS, 2, 3 and 4 may instead have one radial branch 24 and he L- shaped
  • the embodiment shown in detail in FIG 2 illustrates an annular combustion chamber
  • the invention is applicahle to other forms of combustion chamher. such as a reverse Flow combustion chamber or a charnher of the type known as can-annular which in k eludes an array of cylindrical combustion charnhers or cans" disposed in an annular array.
  • a vaporizer for a gas turbine engine for receiving air and Fuel separately and mixing them together.
  • said vaporizer comprising a hollow stern to which air and fuel are delivered separately, at least one radial brunch connected to the hollow stem and through which in operation there passes a flow of a mixture of the air and fuel delivered to the hollow stem, and a cylindrical shroud surrounding and radially spaced from the ho]- low stem to define an annular space for receiving a sup ply of air but not fuel the cylindrical shroud having means defining holes provided in the wall thereof through which in operation air passes out oi said annular space in a direction substantially radially of the stem to mix with the mixture of air and fuel discharged from the radial branch of the hollow stem immediately downstream of the discharge from said radial branch 2.
  • a vaporizer as claimed in claim 1 and having a general T-shape comprising said hollow stem which constitutes the leg of the T and two transverse radial branches connected to said hollow stem,

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Spray-Type Burners (AREA)
  • Air Supply (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Abstract

A vaporizer for a gas turbine engine. The vaporizer has a shroud surrounding the stem and is used to provide a cooling air space. It is provided with holes from which the cooling air issues radially. The radial jets improve combustion efficiency and reduce smoke emission.

Description

United States Patent mi Fox et al.
l l Oct. 21,1975
l l GAS TURBINE ENGINE COMBUSTION EQUIPMENT [75] Inventors Roger Geoffrey Fox; Vernon Frederick Cox, both of Bristol, England Rolls-Royce (1971 Limited. London, England [22] Filed: Aug. 8, 1973 [21] Appl. No: 386,633
{73] Assignee:
[30] Foreign Application Priority Data Aug. 10, 1972 United Kingdom 37305/72 [52} US. Cl .i (SO/39.66; 60/3971; 60/3974 R [51] Int. Cl .i FOZc 7/18; FOIZe 7/22 [58} Field of Search 60/397], 39.74 R. 39.66
[56] References Cited UNITED STATES PATENTS Clarke ct al. v130/3971 X 2,595.765 5/1952 Clarke et ul 60/3971 X 2.602.292 7/1952 Buckland et al.. 60/3971 2.982.098 5/1961 Vickery 60/3971 3 724207 4/1973 Johnson 1 i 60/3974 R 3.757522 9/1973 Caruel et al. 60/3971 Primary Examiner Ci J. Husar Assisrant ExaminerRobert E. Garrett Attorney, Agent, or Firm-Stevens, Davis, Miller & Mosher [57] ABSTRACT A vaporizer for a gas turbine engine. The vaporizer has a shroud surrounding the stem and is used to provide a cooling air space. It is provided with holes from which the cooling air issues radially. The radial jets improve combustion efficiency and reduce smoke emission.
2 Claims, 5 Drawing Figures US. Patent Oct. 21, 1975 Sheet 1 of2 3,913,318
FIG. I.
US. Patent Oct.21,1975 Sheet 2 of2 3,913,318
FIG. 5.
GAS TURBINE ENGINE COMBUSTION EQUIPMENT The present invention relates to fuel vaporizers for use in gas turbine engines. Fuel vaporizers, which are well known, have a hollow cylindrical stem which is adapted to be supplied with fuel and air at one end and to deliver a vaporized mixture of air and fuel from one or other ends.
The vaporizer may have one or more branches at the other end thereof which extend substantially radially of the stem and in order to cool such vaporizers in the past, the stem has been surrounded by a shroud which was spaced therefrom to provide an annular space for providing an air flow between the shroud and the stem, the air passing axially from the end of the space.
It has now been discovered that if the cooling air from said annular space is allowed to pass from the space substantially radially of the stem through holes in the shroud instead of axially of the stem from the annular space at the free end of the shroud, that this radial emission of cooling air improves the temperature distribution in the combustion chamber and leads to improved combustion efficiency. Furthermore, a problem of the burning out of the branches of a branched vapouriser which occured with air passing from the shroud axially of the stem is overcome.
It is not necessary that all the air passes out of the shroud radially in order to achieve improved temperature distribution in the combustion chamber and improved combustion efflciency, these benefits could be gained while still allowing some of the air to pass axially from the end of the space but the problem of the burning out of the branches might occur.
Furthermore, the invention could be applied to an unshrouded vaporizer in that some of the air supplied to the vaporizer stem would, before mixing with the fuel, be allowed to pass substantially radially from the stem through holes in the stem.
According to the invention there is provided a vaporizer for a gas turbine engine and designed to receive air and fuel separately and to mix them together, said vaporizer having a hollow stern, into which the air and the fuel are separately delivered, and having means, which in operation of the vaporizer, allow air, but not fuel, to pass out of the vaporizer in a direction substantially radially of the stern.
In a preferred form of the invention the vaporizer is provided with a cylindrical shroud surrounding, and radially spaced from, the stem thereof to define an annular space for receiving a supply of air, and wherein said means are holes provided in the cylindrical surface of the shroud through which air passes out of the annular space in a direction substantially radially of the stem.
In a further preferred form of the invention all of the air supplied to the annular space passes out of the space through said holes in a direction substantially radially of the stem.
In another preferred form of the invention said means are holes provided in the surface of the stem and through which some of the air supplied to the hollow stem passes out of the stem, before mixture with the fuel, in a direction substantially radially of the stem.
In yet a further preferred form of the invention the vaporizer may have one or two branches at one end of the stem and which extends substantially radially of the stem, the vaporizer thus having an L- or T-shape.
Three examples of the invention will now be more particularly described, by way of example only, with reference to the accompanying drawings in which:
FIG. 1 is a diagrammatic view ofa gas turbine engine,
FIG. 2 is a section through the combustion chamber of the engine of HO. 1 showing the vaporizers in more detail,
FlG. 3 is a sectional plan view of a vaporizer of FIG.
FIG. 4 is a sectional plan view of a second vaporizer, and
HO. 5 is a sectional plan view of a third vaporizer.
Referring now to the drawings, there is shown in FIG. I a gas turbine engine having a compressor 2, combustion equipment 4, a turbine 6 and a propulsion nozzle 8 all in flow series.
The combustion equipment comprises an outer casing 10 and an annular flame tube 12 (FIG. 2). Air is supplied to the flame tube from a compressor delivery duct 3, some of the air passing directly into the flame tube through vaporizers 14, whilst the majority of the air supplied passes into the space 16 between the flame tube and the outer casing, and from there passes into the flame tube through apertures 18 into the wall thereof. Fuel supply pipes 20 supply fuel to the vaporizers where it is mixed with the air and vaporized due to the heat in the surrounding gas in the flame tube.
The vaporizers 14 are of substantially T-section, each of which has a cylindrical stem 22 which is connected to the flame tube at one end and radial branches 24 at the free end thereof.
Surrounding the stem of each vaporizer is a shroud 26 which is radially spaced from the stem to define an annular passage 28 which is supplied with air from the compressor delivery duct 3. The downstream end of the annular passage is blocked and holes 30 are formed in the shroud to allow the air to emerge substantially radially of the stem as shown by arrows 29.
The effects of this are two fold:
a. The radial flow of air, although relatively small promotes further mixing of fuel and air in the primary combustion zone, and this improves the temperature distribution in the combustion chamber, and the combustion efficiency.
b. Cooling air is prevented from flowing axially over the radial branches of the T vaporizer, and this prevents a flame from stabilizing of the vaporizer downstreams of the radial branch in the air flow.
The holes 30 are positioned, so that there is no impingement of the air flowing through them on the branches.
in addition, weirs 32 are provided within the stem at the junctions with the radial branches of the vapouriser for creating turbulence in the fuel/air mixture in the branches. This promotes cooling of the branches.
The vaporizer 40 shown in FIG. 4 is similar to the one shown in FIGS. 2 and 3 except that the radial arms 24 are replaced by an umbrella 37 which is supported from the stem 22 by struts 38 to form an annular outlet 39. The effect of the umbrella is similar to that of the radial branches 24 in that the air and fuel mixture is emitted from the annular outlet 39. The radial flow of air through the holes 30 promotes further mixing of fuel and air in the primary combustion zone. The vaporizer 40 is mounted from the flame tube 12 in the same manner as is shown in FIG. 2.
The vaporizer 31 shown in FIG. 5 is similar to the vapouriser 14 shown in FIGS. 2 and 3 except that it is not prmidctl with a shroud 26 and there is a suhstan tiall; radial outflow oiair through the holes in the stem 22. The fuel supply pipe projects into the stem :1 sufficient distance downstream of the holes 35 in order that fuel and fuel vapor does not How out of the holes 35. The radial flow of air through the holes 35 promotes Further mixing of fuel and air in the primary cornhustion 7one. in operation there is a pressure drop across the wall of the stem which promotes a radial out- How of air through the holes 35 and this pressure drop could he increased by the weir 32 or other known means such as converging outlets at the exits to the radial hranches 24 The holes 35 are so positioned that there is no impingement of the air flowing through the holes 35 on the branches 24.
The vaporizers 14 and shown in FIGS, 2, 3 and 4 may instead have one radial branch 24 and he L- shaped The embodiment shown in detail in FIG 2 illustrates an annular combustion chamber However, the invention is applicahle to other forms of combustion chamher. such as a reverse Flow combustion chamber or a charnher of the type known as can-annular which in k eludes an array of cylindrical combustion charnhers or cans" disposed in an annular array.
What we claim is:
l. A vaporizer for a gas turbine engine for receiving air and Fuel separately and mixing them together. said vaporizer comprising a hollow stern to which air and fuel are delivered separately, at least one radial brunch connected to the hollow stem and through which in operation there passes a flow of a mixture of the air and fuel delivered to the hollow stem, and a cylindrical shroud surrounding and radially spaced from the ho]- low stem to define an annular space for receiving a sup ply of air but not fuel the cylindrical shroud having means defining holes provided in the wall thereof through which in operation air passes out oi said annular space in a direction substantially radially of the stem to mix with the mixture of air and fuel discharged from the radial branch of the hollow stem immediately downstream of the discharge from said radial branch 2. A vaporizer as claimed in claim 1 and having a general T-shape comprising said hollow stem which constitutes the leg of the T and two transverse radial branches connected to said hollow stem,
i r w

Claims (2)

1. A vaporizer for a gas turbine engine for receiving air and fuel separately and mixing them together, said vaporizer comprising a hollow stem to which air and fuel are delivered separately, at least one radial branch connected to the hollow stem and through which in operation there passes a flow of a mixture of the air and fuel delivered to the hollow stem, and a cylindrical shroud surrounding and radially spaced from the hollow stem to define an annular space for receiving a supply of air but not fuel, the cylindrical shroud having means defining holes provided in the wall thereof through which in operation air passes out of said annular space in a direction substantially radially of the stem to mix with the mixture of air and fuel discharged from the radial branch of the hollow stem immediately downstream of the discharge from said radial branch.
2. A vaporizer as claimed in claim 1 and having a general T-shape comprising said hollow stem which constitutes the leg of the T and two transverse radial branches connected to said hollow stem.
US386633A 1972-08-10 1973-08-08 Gas turbine engine combustion equipment Expired - Lifetime US3913318A (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
GB3730572A GB1435083A (en) 1972-08-10 1972-08-10 Gas turbine engine combustion equipment
BE140334A BE810354A (en) 1972-08-10 1974-01-30 IMPROVEMENT OF TURBO REACTOR COMBUSTION DEVICES
NL7401496A NL7401496A (en) 1972-08-10 1974-02-04 COMBUSTION DEVICE FOR A GAS TURBINE ENGINE.
LU69355 1974-02-08

Publications (1)

Publication Number Publication Date
US3913318A true US3913318A (en) 1975-10-21

Family

ID=27424617

Family Applications (1)

Application Number Title Priority Date Filing Date
US386633A Expired - Lifetime US3913318A (en) 1972-08-10 1973-08-08 Gas turbine engine combustion equipment

Country Status (11)

Country Link
US (1) US3913318A (en)
JP (1) JPS5310209B2 (en)
AU (1) AU472058B2 (en)
BE (1) BE810354A (en)
CA (1) CA985918A (en)
DE (1) DE2340013C3 (en)
FR (1) FR2209042B1 (en)
GB (1) GB1435083A (en)
LU (1) LU69355A1 (en)
NL (1) NL7401496A (en)
SE (1) SE384247B (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1979000387A1 (en) * 1977-12-14 1979-06-28 Caterpillar Tractor Co Fuel vaporizing combustor tube
USRE30925E (en) * 1977-12-14 1982-05-11 Caterpillar Tractor Co. Fuel vaporizing combustor tube
US4389185A (en) * 1980-10-31 1983-06-21 Alpkvist Jan A Combustor for burning a volatile fuel with air
US20060175428A1 (en) * 2005-02-07 2006-08-10 Pratt & Whitney Canada Corp. Low cost pressure atomizer
US20150276226A1 (en) * 2014-03-28 2015-10-01 Siemens Energy, Inc. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine
CN105716120A (en) * 2016-02-22 2016-06-29 中国科学院工程热物理研究所 Fuel-cooled type evaporating pipe structure
US20170356657A1 (en) * 2016-06-13 2017-12-14 Rolls-Royce North American Technologies Inc. Swirl stabilized vaporizer combustor
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber
US12000589B2 (en) * 2022-06-30 2024-06-04 Doosan Enerbility Co., Ltd Jet nozzle, combustor, and gas turbine including same

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4070826A (en) * 1975-12-24 1978-01-31 General Electric Company Low pressure fuel injection system
DE2641605C2 (en) * 1975-12-24 1986-06-19 General Electric Co., Schenectady, N.Y. Device for supplying air and fuel

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2593849A (en) * 1952-04-22 Liquid fuel burner with diverse air
US2595765A (en) * 1949-01-01 1952-05-06 Lucas Ltd Joseph Liquid fuel burner
US2602292A (en) * 1951-03-31 1952-07-08 Gen Electric Fuel-air mixing device
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems
US3724207A (en) * 1971-08-05 1973-04-03 Gen Motors Corp Combustion apparatus
US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB902511A (en) * 1960-04-19 1962-08-01 Bristol Siddeley Engines Ltd Improvements in or relating to combustion chambers
FR1590542A (en) * 1968-11-04 1970-04-13
US3579983A (en) * 1969-05-05 1971-05-25 Snecma Improvements in or relating to combustion chambers

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2593849A (en) * 1952-04-22 Liquid fuel burner with diverse air
US2595765A (en) * 1949-01-01 1952-05-06 Lucas Ltd Joseph Liquid fuel burner
US2602292A (en) * 1951-03-31 1952-07-08 Gen Electric Fuel-air mixing device
US2982098A (en) * 1953-04-22 1961-05-02 Power Jets Res & Dev Ltd Liquid fuel vaporizing combustion systems
US3757522A (en) * 1971-07-16 1973-09-11 Moteurs D Aviat D Et Const Devices for pre-vaporising liquid fuel
US3724207A (en) * 1971-08-05 1973-04-03 Gen Motors Corp Combustion apparatus

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1979000387A1 (en) * 1977-12-14 1979-06-28 Caterpillar Tractor Co Fuel vaporizing combustor tube
US4188782A (en) * 1977-12-14 1980-02-19 Caterpillar Tractor Co. Fuel vaporizing combustor tube
USRE30925E (en) * 1977-12-14 1982-05-11 Caterpillar Tractor Co. Fuel vaporizing combustor tube
US4389185A (en) * 1980-10-31 1983-06-21 Alpkvist Jan A Combustor for burning a volatile fuel with air
US20060175428A1 (en) * 2005-02-07 2006-08-10 Pratt & Whitney Canada Corp. Low cost pressure atomizer
US7320440B2 (en) 2005-02-07 2008-01-22 Pratt & Whitney Canada Corp. Low cost pressure atomizer
US20150276226A1 (en) * 2014-03-28 2015-10-01 Siemens Energy, Inc. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine
US10139111B2 (en) * 2014-03-28 2018-11-27 Siemens Energy, Inc. Dual outlet nozzle for a secondary fuel stage of a combustor of a gas turbine engine
CN105716120A (en) * 2016-02-22 2016-06-29 中国科学院工程热物理研究所 Fuel-cooled type evaporating pipe structure
US20170356657A1 (en) * 2016-06-13 2017-12-14 Rolls-Royce North American Technologies Inc. Swirl stabilized vaporizer combustor
US10767865B2 (en) * 2016-06-13 2020-09-08 Rolls-Royce North American Technologies Inc. Swirl stabilized vaporizer combustor
US20230184438A1 (en) * 2019-10-08 2023-06-15 Safran Helicopter Engines Pre-vaporisation tube for a turbine engine combustion chamber
US11841140B2 (en) * 2019-10-08 2023-12-12 Safran Helicopter Engines Pre-vaporization tube for a turbine engine combustion chamber
US12000589B2 (en) * 2022-06-30 2024-06-04 Doosan Enerbility Co., Ltd Jet nozzle, combustor, and gas turbine including same

Also Published As

Publication number Publication date
JPS5310209B2 (en) 1978-04-12
LU69355A1 (en) 1974-05-17
FR2209042A1 (en) 1974-06-28
DE2340013C3 (en) 1981-05-07
NL7401496A (en) 1975-08-06
GB1435083A (en) 1976-05-12
CA985918A (en) 1976-03-23
AU5907473A (en) 1975-02-13
JPS49124414A (en) 1974-11-28
FR2209042B1 (en) 1976-09-17
BE810354A (en) 1974-05-16
AU472058B2 (en) 1976-05-13
DE2340013A1 (en) 1974-02-21
DE2340013B2 (en) 1980-08-28
SE384247B (en) 1976-04-26

Similar Documents

Publication Publication Date Title
US2856755A (en) Combustion chamber with diverse combustion and diluent air paths
US10711699B2 (en) Auxiliary torch ignition
US5359847A (en) Dual fuel ultra-low NOX combustor
CN101672483B (en) Gas turbine
US2679137A (en) Apparatus for burning fuel in a fast moving gas stream
US20190010872A1 (en) Auxiliary torch ignition
US5713206A (en) Gas turbine ultra low NOx combustor
US5289685A (en) Fuel supply system for a gas turbine engine
US3433015A (en) Gas turbine combustion apparatus
US7966821B2 (en) Reduced exhaust emissions gas turbine engine combustor
US3925002A (en) Air preheating combustion apparatus
US4193260A (en) Combustion apparatus
US2635426A (en) Annular vaporizer
US3913318A (en) Gas turbine engine combustion equipment
GB1427146A (en) Combustion apparatus for gas turbine engines
JP2005121351A (en) Method and device for cooling turbine engine combustor exit temperature
US3952503A (en) Gas turbine engine combustion equipment
RU2379537C2 (en) Method to improve ignition in two-flow turbojet engine afterburner and afterburner to this end
CN102777932A (en) A combustor nozzle and method for supplying fuel to a combustor
US2704435A (en) Fuel burning means for a gaseous-fluid propulsion jet
CN104024737B (en) For combustion chamber and the burner apparatus of gas turbine
US3653207A (en) High fuel injection density combustion chamber for a gas turbine engine
GB1075958A (en) Gas turbine engine
EP1207344B1 (en) Combustor
US3043101A (en) By-pass gas turbine engine employing reheat combustion