US2826039A - Gas inlet structure for combustion chambers - Google Patents

Gas inlet structure for combustion chambers Download PDF

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Publication number
US2826039A
US2826039A US357999A US35799953A US2826039A US 2826039 A US2826039 A US 2826039A US 357999 A US357999 A US 357999A US 35799953 A US35799953 A US 35799953A US 2826039 A US2826039 A US 2826039A
Authority
US
United States
Prior art keywords
combustion
gas
chamber
air
channel
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
US357999A
Other languages
English (en)
Inventor
Ashwood Peter Frederick
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development 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
Priority to FR959791D priority Critical patent/FR959791A/fr
Priority to NL207253D priority patent/NL207253A/xx
Priority to NL82911D priority patent/NL82911C/xx
Priority to BE479471D priority patent/BE479471A/xx
Priority to NL90479D priority patent/NL90479C/xx
Priority to GB765/47A priority patent/GB620343A/en
Priority claimed from US793375A external-priority patent/US2667033A/en
Priority to CH271829D priority patent/CH271829A/de
Priority to US357999A priority patent/US2826039A/en
Application filed by Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Publication of US2826039A publication Critical patent/US2826039A/en
Application granted granted Critical
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • Tdiifection flow of reactants in the chamber is, open at both ends to communicate on one handwith .
  • This invention relates to an improved apparatus for the combustion of fuel in a combustion-supporting gas.
  • An object of the invention is to provide for the continuous combustion of large quantities of fuel in a comparatively confined space such as may be required for combustion gas turbines.
  • Such combustion apparatus comprises normally a combustion chamber at least partly enclosed in a duct conveying the combustion-supporting gas. A proportion of this gas andthe fuel are introduced into the chamber at one region thereof and reaction takes place as they proceed ultimately to the chaming along the channel.
  • a further object of the present invention is accordingly to provide a more durable means for conveying gas to an interior region of the combustion space.
  • a channel member extending from the chamber wall towards the interior region so that the open side of the channel faces in the general direction from which the combustion reactants in the chamber approach the member, the chamber being apertured to direct a flow of combustionsupporting gas into the channel.
  • impinging reactants on the cool gas flowing in the channel apparently causes a continuous spilling of that gas over the channel edges whereby they are insulated. It is further proposed with a view to supplementing this effect that the channel be progressively reduced in transverse area in the direction away from the chamber wall to which it is attached. On the other hand, in case the natural tendency to spilling of the channelled gas should be excessive, it is proposed that it be reduced to some extent by inclining the channel member, inwardly of its point of attachment to the chamber wall, in the direction of flow of the impinging stream of reactants. It is considered that a construction embodying both of these features will lead to a more controlled spilling of the channelled gas flow than would otherwise be the case.
  • the combustion apparatus comprises an air duct, 1 having at its upstream end a flange 2 by which it is intended that it should be secured directto the outlet from acompressor in a gas turbine of conventional type.
  • the opposite or downstream end of the air duct has a flange 3 by which it is intended to be secured to the nozzle housing of a turbine.
  • a general arrangement of this character is of course well known and so is not considered to require further description.
  • a combustion chamber within the air duct is a combustion chamber .in the form of a flame tube 4 having its upstream end .formed by a conical baffle 5 with. its apex pointing downstream.
  • a fuel nozzle 6 is arranged in alignment with the apex of the conical baffle 5 to inject fuel in an upstream direction into the upstream limiting region of the flame tube 4.
  • the conical baffle 5 is mounted on a frusto-conical part 7 of the flame tube 4 which forms in efiect an outward and downstream extension from the base of the cone, but also forms a lip 8 extending some distance upstream beyond the base of the cone to form an aperture 9 dimensioned to admit a desired proportion of the total air flow to the interior of the cone, the proportion in the preferred ease illustrated being a minor proportion which *is in the nature of a pilot flow.
  • the flame tube is so arranged that the plane of its entry 9 is close up to that of the flange 2.
  • the air duct except for a short cylindrical part immediately downstream of the compressor at 10, also increases in diameter in the downstream direction so as to form with the frusto-conical nose 7 of the flame tube an annular space 11 of increasing cross sectional area in the downstream direction designed as a diffusion passage suitable for the velocity conditions involved. From the downstream end of the annular diffusion passage 11 so formed both the flame tube and the air duct are of cylindrical form for some distance, the air duct terminating at its downstream end in a tapering section 12 leading to the turbine inlet.
  • the flame tube Upstream of this region the flame tube has an outwardly flared frusto-conical portion 13 which increases in diameter nearly to that of the air casing, the downstream end of this part being radially located by spaced peripheral projections 13a engaging the wall of the air duct. A small amount of air leakage is thus allowed between,
  • the fuel pipes 14 for the nozzle 6 are screened from the air flow by an enclosing fairing 15.
  • the conical baffle forms a diffuser for air entering at 9 and has at least one port or set of ports 16 at or near its apex in order to introduce to a radially inner region at the base of the fuel jet or spray a pilot supply of combustion air insuflicient to cause reversal thereof while, further ports 17, 18, respectively are provided at intervals towards the base of the cone to provide a pilot supply of air to a radially inner intermediate region of the jet or spray and also to the radially outer part of the fuel jet spray at a region where flow reversal thereof will take place in use due to the air flow.
  • the major primary supply of combustion air enters through a set of ports 19 at or near the outlet from the annular dififusion passage 11 (that is at about the shoulder of the flame tube); this supply of air, it will be noted, is so arranged in the region of the fuel jet or spray as to introduce air enveloping the latter somewhat downstream of its region of flow reversal. Further sets of ports 20, 21 for the inlet of secondary combustion air and a cooling or diluent air respectively are provided at spaced downstream zones of the combustion chamber.
  • the flared portion 13 of the flame tube has a circumferentially spaced set of rectangular apertures 23-each of which coincides with the outer end of a channelled scoop 22 attached to the flame tube portion 13.
  • Each scoop extends inwardly and rearwardly of the flame tube from its point of attachment and serves to convey diluent air from the associated rectangular aperture to the central region of the flame tube.
  • the open side of the channel of each scoop faces directly in the upstream direction and the side walls of the channel taper'and converge from the attached end of the scoop with a consequential reduction in transverse area of the channel.
  • Combustion apparatus having a duct for conveying a combustion-supporting gas, a wall combustion chamber at least partly enclosed by said duct and apertured to admit a portion of the combustion-supporting gas to one region of the chamber, means for introducing fuel to said region of the chamber to react with said portion of combustion-supporting gas, said chamber defining a flow path for the combustion reactants and having an outlet to which the combustion reactants flow during reaction, and an elongated channel member extending from the chamber wall inwardly across said combustion reaction flow path, said member being channelled in transverse section throughout its entire length and arranged with the open side of the channel facing upstream towards the approaching combustion reactants, said channel member having an open end facing into said chamber in a direction transverse to the direction of flow, said chamber being further apertured to direct a further portion of combustion-supporting gas into said channel.

Landscapes

  • 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)
US357999A 1947-01-09 1953-05-28 Gas inlet structure for combustion chambers Expired - Lifetime US2826039A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
NL207253D NL207253A (zh) 1947-01-09
NL82911D NL82911C (zh) 1947-01-09
BE479471D BE479471A (zh) 1947-01-09
NL90479D NL90479C (zh) 1947-01-09
FR959791D FR959791A (zh) 1947-01-09
GB765/47A GB620343A (en) 1947-01-09 1947-01-09 Improvements in or relating to diffusion systems for operation in high velocity air streams
CH271829D CH271829A (de) 1947-01-09 1947-12-30 Verbrennungseinrichtung.
US357999A US2826039A (en) 1947-01-09 1953-05-28 Gas inlet structure for combustion chambers

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
GB271829X 1947-01-09
US793375A US2667033A (en) 1947-01-09 1947-12-23 Combustion apparatus for operation in fast-moving air streams
US357999A US2826039A (en) 1947-01-09 1953-05-28 Gas inlet structure for combustion chambers

Publications (1)

Publication Number Publication Date
US2826039A true US2826039A (en) 1958-03-11

Family

ID=32329572

Family Applications (1)

Application Number Title Priority Date Filing Date
US357999A Expired - Lifetime US2826039A (en) 1947-01-09 1953-05-28 Gas inlet structure for combustion chambers

Country Status (6)

Country Link
US (1) US2826039A (zh)
BE (1) BE479471A (zh)
CH (1) CH271829A (zh)
FR (1) FR959791A (zh)
GB (1) GB620343A (zh)
NL (3) NL90479C (zh)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3266250A (en) * 1963-01-31 1966-08-16 Rolls Royce Combustion equipment for a gas turbine engine
US4590769A (en) * 1981-01-12 1986-05-27 United Technologies Corporation High-performance burner construction
US5187937A (en) * 1988-06-22 1993-02-23 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
US5321947A (en) * 1992-11-10 1994-06-21 Solar Turbines Incorporated Lean premix combustion system having reduced combustion pressure oscillation
US5372008A (en) * 1992-11-10 1994-12-13 Solar Turbines Incorporated Lean premix combustor system
US20160209030A1 (en) * 2015-01-16 2016-07-21 National Chung-Shan Institute Of Science And Technology Combustion supporting device
CN106287814A (zh) * 2016-09-29 2017-01-04 南京航空航天大学 一种轴向进气的地面燃气轮机单管燃烧室

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1123868B (de) * 1958-08-26 1962-02-15 Schweizerische Lokomotiv Brennkammer, insbesondere fuer Gasturbinen
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB578764A (en) * 1942-09-08 1946-07-11 Rover Co Ltd Improvements relating to combustion chambers for internal combustion turbines
US2446059A (en) * 1944-10-05 1948-07-27 Peabody Engineering Corp Gas heater
US2448561A (en) * 1946-05-01 1948-09-07 Westinghouse Electric Corp Gas turbine apparatus
US2531810A (en) * 1946-06-05 1950-11-28 Kellogg M W Co Air inlet arrangement for combustion chamber flame tubes
US2541171A (en) * 1947-01-25 1951-02-13 Kellogg M W Co Air inlet structure for combustion chambers
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
US2601000A (en) * 1947-05-23 1952-06-17 Gen Electric Combustor for thermal power plants having toroidal flow path in primary mixing zone
US2610467A (en) * 1946-04-03 1952-09-16 Westinghouse Electric Corp Combustion chamber having telescoping walls and corrugated spacers

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB578764A (en) * 1942-09-08 1946-07-11 Rover Co Ltd Improvements relating to combustion chambers for internal combustion turbines
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
US2446059A (en) * 1944-10-05 1948-07-27 Peabody Engineering Corp Gas heater
US2610467A (en) * 1946-04-03 1952-09-16 Westinghouse Electric Corp Combustion chamber having telescoping walls and corrugated spacers
US2448561A (en) * 1946-05-01 1948-09-07 Westinghouse Electric Corp Gas turbine apparatus
US2531810A (en) * 1946-06-05 1950-11-28 Kellogg M W Co Air inlet arrangement for combustion chamber flame tubes
US2541171A (en) * 1947-01-25 1951-02-13 Kellogg M W Co Air inlet structure for combustion chambers
US2601000A (en) * 1947-05-23 1952-06-17 Gen Electric Combustor for thermal power plants having toroidal flow path in primary mixing zone

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3266250A (en) * 1963-01-31 1966-08-16 Rolls Royce Combustion equipment for a gas turbine engine
US4590769A (en) * 1981-01-12 1986-05-27 United Technologies Corporation High-performance burner construction
US5187937A (en) * 1988-06-22 1993-02-23 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland Gas turbine engine combustors
US5321947A (en) * 1992-11-10 1994-06-21 Solar Turbines Incorporated Lean premix combustion system having reduced combustion pressure oscillation
US5372008A (en) * 1992-11-10 1994-12-13 Solar Turbines Incorporated Lean premix combustor system
US20160209030A1 (en) * 2015-01-16 2016-07-21 National Chung-Shan Institute Of Science And Technology Combustion supporting device
US10082291B2 (en) * 2015-01-16 2018-09-25 National Chung-Shan Institute Of Science And Technology Combustion supporting device
CN106287814A (zh) * 2016-09-29 2017-01-04 南京航空航天大学 一种轴向进气的地面燃气轮机单管燃烧室

Also Published As

Publication number Publication date
NL207253A (zh)
CH271829A (de) 1950-11-15
NL82911C (zh)
BE479471A (zh)
NL90479C (zh)
GB620343A (en) 1949-03-23
FR959791A (zh) 1950-04-05

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