GB945096A - Combustion chamber for liquid fuels - Google Patents

Combustion chamber for liquid fuels

Info

Publication number
GB945096A
GB945096A GB2754/61A GB275461A GB945096A GB 945096 A GB945096 A GB 945096A GB 2754/61 A GB2754/61 A GB 2754/61A GB 275461 A GB275461 A GB 275461A GB 945096 A GB945096 A GB 945096A
Authority
GB
United Kingdom
Prior art keywords
chamber
oxygen
injected
combustion
water
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
GB2754/61A
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.)
Individual
Original Assignee
Individual
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 claimed from DEB56439A external-priority patent/DE1142253B/en
Application filed by Individual filed Critical Individual
Publication of GB945096A publication Critical patent/GB945096A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/27—Fluid drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
    • F02K9/60—Constructional parts; Details not otherwise provided for
    • F02K9/62—Combustion or thrust chambers
    • F02K9/64—Combustion or thrust chambers having cooling 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)

Abstract

945,096. Rocket and other combustion chambers. L. BOLKOW, [trading as BOLKOWENTWICKLUNGEN KOMM.-GES]. Jan. 24, 1961 [Jan. 29, 1960], No. 2754/61. Headings F1J and F1L. In a combustion chamber for liquid fuels a liquid coolant flows spirally along the interior wall of the chamber from a pre-combustion chamber or mixing chamber into which it has been injected tangentially. Fuel oil, oxygen or an oxygen carrier and water are all injected tangentially into a chamber 5 and the water flows into the combustion chamber 1 taking with it a layer of oil. The water absorbs heat from the wall 4 and evaporates the oil which mixes with .the oxygen for combustion. In analternative construction atomized fuel oil is injected axially and the oxygen is injected tangentially into a chamber surrounding the fuel nozzle, this chamber being independent of the chamber 5. In a further construction the oxygen may be injected axially while the fuel oil and water are injected tangentially into the chamber 5.
GB2754/61A 1960-01-29 1961-01-24 Combustion chamber for liquid fuels Expired GB945096A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEB56439A DE1142253B (en) 1960-01-29 1960-01-29 Combustion chamber for liquid fuels

Publications (1)

Publication Number Publication Date
GB945096A true GB945096A (en) 1963-12-23

Family

ID=6971332

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2754/61A Expired GB945096A (en) 1960-01-29 1961-01-24 Combustion chamber for liquid fuels

Country Status (2)

Country Link
FR (1) FR1278451A (en)
GB (1) GB945096A (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1332910A (en) * 1970-10-15 1973-10-10 Kayser Lutz Tilo Rocket type combustion chamber

Also Published As

Publication number Publication date
FR1278451A (en) 1961-12-08

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