GB922541A - Improvements in and relating to internal combustion engines - Google Patents

Improvements in and relating to internal combustion engines

Info

Publication number
GB922541A
GB922541A GB884560A GB884560A GB922541A GB 922541 A GB922541 A GB 922541A GB 884560 A GB884560 A GB 884560A GB 884560 A GB884560 A GB 884560A GB 922541 A GB922541 A GB 922541A
Authority
GB
United Kingdom
Prior art keywords
combustion chamber
air
fuel
wall
combustion
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
Application number
GB884560A
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.)
MAN AG
Original Assignee
MAN Maschinenfabrik Augsburg Nuernberg AG
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 MAN Maschinenfabrik Augsburg Nuernberg AG filed Critical MAN Maschinenfabrik Augsburg Nuernberg AG
Publication of GB922541A publication Critical patent/GB922541A/en
Expired legal-status Critical Current

Links

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
    • F23R3/26—Controlling the air flow
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Nozzles For Spraying Of Liquid Fuel (AREA)

Abstract

922,541. Generating combustion products under pressure. MASCHINENFABRIK AUGSBURG-NURNBERG A.G. March 14, 1960 [March 28, 1959], No. 8845/60. Class 51 (1). [Also in Group XI] Liquid fuel from an intermittently or continuously operating non-atomizing injector 3 is spread in the form of a film 40 over the wall of the combustion chamber 1 of a gas turbine, combustion air is caused to sweep the combustion chamber wall at high speed and the combustion chamber wall is maintained at a temperature at which the period of dwell of the fuel particles thereon before vaporization is a minimum. The fuel injector 3 has a discharge slit disposed close to the combustion chamber wall. Air from a compressor (not shown) enters the combustion chamber and is caused to rotate by manually or automatically adjustable vanes 8. Further air from the compressor passes along an annular channel 12 to cool the combustion chamber wall and is controlled by a valve 13 comprising a radially slotted ring 15 and a co-operating slotted ring 16 which is rotatable and is coupled through a rack 19 and gearing 18 to a motor 17 controlled by a thermostat 14 inside the combustion chamber. Alternatively the valve 13 may comprise pivoted blades having cranks with pins engaging slots in a rotatable control ring located around the outer wall 11 of the annular air channel. Further air is introduced into the combustion chamber through nozzles 20 on the ends of valve controlled pipes 21 which are inclined in the direction of rotation of the air in the combustion chamber; alternatively if an increase in turbulence is required some of the pipes 21 inject air against the direction of rotation. Combustion products or air may be made to circulate in either direction through the core of the combustion chamber by means of two ducts 22, 24 having gate valves 23, 25. Air may also be introduced through a duct 22a at the outlet of the combustion chamber. At starting an atomized jet of fuel from a second injector 6 is ignited by a spark gap 5 and vaporizes the film of fuel.
GB884560A 1959-03-28 1960-03-14 Improvements in and relating to internal combustion engines Expired GB922541A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM41002A DE1131947B (en) 1959-03-28 1959-03-28 Combustion process for gas turbine combustion chambers and equipment for carrying out the process

Publications (1)

Publication Number Publication Date
GB922541A true GB922541A (en) 1963-04-03

Family

ID=7303881

Family Applications (1)

Application Number Title Priority Date Filing Date
GB884560A Expired GB922541A (en) 1959-03-28 1960-03-14 Improvements in and relating to internal combustion engines

Country Status (2)

Country Link
DE (1) DE1131947B (en)
GB (1) GB922541A (en)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3859787A (en) * 1974-02-04 1975-01-14 Gen Motors Corp Combustion apparatus
DE2620424C2 (en) * 1976-05-08 1983-07-21 MTU Motoren- und Turbinen-Union München GmbH, 8000 München Combustion chamber with variable geometry of the air supply for gas turbine engines
DE4415916A1 (en) * 1994-05-05 1995-11-09 Siemens Ag Method of combusting fluidic fuel in air stream

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR348124A (en) * 1903-11-19 1905-04-03 Franz Windhausen Internal combustion or explosion turbine
CH163490A (en) * 1932-10-11 1933-08-31 Bataafsche Petroleum Method and device for the combustion of liquid fuels.
US2110209A (en) * 1934-10-13 1938-03-08 Baker Perkins Co Inc Furnace
DE749456C (en) * 1937-07-25 1944-11-24 Pre-chamber two-stroke internal combustion engine with external ignition
CH214477A (en) * 1939-01-30 1941-04-30 Bbc Brown Boveri & Cie Cooling device on pipes, containers, housings or the like through which hot gases flow or which include them.
DE730691C (en) * 1941-01-14 1943-01-15 Wagner Hochdruck Dampfturbinen Oil or dust burner
CH230332A (en) * 1941-12-20 1943-12-31 Licentia Gmbh Combustion chamber for pressurized combustion of gas turbines.
CH229934A (en) * 1942-10-06 1943-11-30 Bbc Brown Boveri & Cie Gas turbine plant.
CH241750A (en) * 1944-11-30 1946-03-31 Oerlikon Maschf Combustion chamber for gas turbine plant.
GB621789A (en) * 1945-10-19 1949-04-20 Power Jets Res & Dev Ltd Improved ignition system for gas turbine engines
CH260175A (en) * 1947-09-23 1949-02-28 Sulzer Ag Combustion chamber, in particular for gas turbines.
US2621477A (en) * 1948-06-03 1952-12-16 Power Jets Res & Dev Ltd Combustion apparatus having valve controlled passages for preheating the fuel-air mixture
BE490776A (en) * 1948-10-26
GB700672A (en) * 1949-02-02 1953-12-09 Henning Christian Rosengart Improvements in or relating to gas turbines
FR1011417A (en) * 1949-02-03 1952-06-23 Onera (Off Nat Aerospatiale) Improvements made to continuous flow internal combustion engines, in particular those for aerodynes
CH291617A (en) * 1949-06-29 1953-06-30 Canadian Patents Dev Combustion chamber for gas turbine.
GB685062A (en) * 1949-12-31 1952-12-31 Lucas Ltd Joseph Improvements relating to combustion chambers for jet engines, gas turbines or the like
BE501222A (en) * 1950-02-14
DE892096C (en) * 1950-12-02 1953-08-20 Armstrong Siddeley'Motors Limited, Coventry, Warwickshire (Großbritannien) Combustion chamber for liquid fuel
DE865683C (en) * 1951-12-18 1953-02-05 Hans Krug Injection process for a high-speed diesel engine with a combustion chamber of rotation in the piston
US2654997A (en) * 1952-02-23 1953-10-13 Esther C Goddard Two-liquid combustion chamber for rocket apparatus
DE959694C (en) * 1952-12-20 1957-03-07 Armstrong Siddeley Motors Ltd Evaporators and burners for liquid fuels, especially for gas turbines and jet engines
US2819732A (en) * 1954-07-14 1958-01-14 Thompson Prod Inc Variable area turbine entrance nozzle
CH324502A (en) * 1954-12-18 1957-09-30 Bbc Brown Boveri & Cie Automatic air control device in combustion chambers of gas turbine plants
DE1777112A1 (en) * 1968-09-07 1971-04-01 Carl Thiel & Soehne Gmbh Process and system for coating metallic workpieces

Also Published As

Publication number Publication date
DE1131947B (en) 1962-06-20

Similar Documents

Publication Publication Date Title
US2595505A (en) Coaxial combustion products generator, turbine, and compressor
GB1467499A (en) Combustion apparatus
GB1136543A (en) Liquid fuel combustion apparatus for gas turbine engines
GB1333881A (en) Combustion apparatus
GB1478395A (en) Apparatus for supplying a mixture of fuel and air to a combustion chamber
GB911759A (en) Improvements in fluid fuel combustion apparatus
GB840054A (en) A device for generating power gases for driving power plants such as turbines
GB1427540A (en) Devices for prevapourising liquid fuel
GB1069217A (en) Improvements relating to engines
GB801281A (en) Improvements in or relating to reaction turbines
GB904142A (en) Improvements in or relating to gas-turbine engines
GB1180929A (en) Combustion Apparatus, for example for Gas Turbines.
GB809300A (en) Improvements relating to combustion chambers for combustion turbines, jet propulsionengines and the like
GB1535765A (en) Variable cycle turbofan engines
GB922541A (en) Improvements in and relating to internal combustion engines
SE8006213L (en) MIXTURES FOR COMBUSTION ENGINES
GB469180A (en) Improvements in or relating to turbines
GB891278A (en) A gas turbine power unit
GB1524217A (en) Combustion chamber for a gas turbine engine
GB811745A (en) Improvements relating to combustion chambers for gas-turbine or jet-propulsion devices and the method of operating the same
GB1530331A (en) Starting device for a gas turbine engine
GB861101A (en) Combination power plant for an aircraft
GB1503425A (en) Gas turbine ducted fan jet engines for supersonic flight
GB826961A (en) Liquid fuel combustion apparatus
GB944585A (en) An apparatus for burning oil having a high carbon to hydrogen ratio