GB287701A - Improvements in internal combustion turbines - Google Patents

Improvements in internal combustion turbines

Info

Publication number
GB287701A
GB287701A GB21925A GB21925A GB287701A GB 287701 A GB287701 A GB 287701A GB 21925 A GB21925 A GB 21925A GB 21925 A GB21925 A GB 21925A GB 287701 A GB287701 A GB 287701A
Authority
GB
United Kingdom
Prior art keywords
rotor
air
passages
blades
nozzles
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
GB21925A
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
Application filed by Individual filed Critical Individual
Priority to GB21925A priority Critical patent/GB287701A/en
Publication of GB287701A publication Critical patent/GB287701A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

287,701. Carter, B. C. Jan. 3, 1925. Radial-flow type; working-fluid supply.-Air introduced at ports 10, passes between radia blades 7 and is driven by centrifugal action through passages 12, 13 between radial blades 8 Fuel is introduced into passages 13 from pipes 14, the passages 12 being closed in the neighbourhood of the pipes 14 by bridge pieces 17. The mixture is ignited by plugs 15, not electrodes or catalytic devices, and the products of combustion mix with the air from the passages 12 and pass out of the rotor through rearwardly directed nozzles 9. The blades 7, 8 and the balls of the nozzles 9 overlap radially. The nozzles 9 may open on the sides of the rotor. Screw blades 19 may be fitted in the air ports 10. The air may be supplied under pressure to the ports by a pair of centrifugal compressors. The flow through the rotor may be made intermittent by means of a cylindrical stationary grating. The rotor may be used without any casing, or the casing may be arranged as a second rotor with exhaust nozzles. When compressors are used, air may be used to cool the casing. Specification 227,151 is referred to.
GB21925A 1925-01-03 1925-01-03 Improvements in internal combustion turbines Expired GB287701A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB21925A GB287701A (en) 1925-01-03 1925-01-03 Improvements in internal combustion turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB21925A GB287701A (en) 1925-01-03 1925-01-03 Improvements in internal combustion turbines

Publications (1)

Publication Number Publication Date
GB287701A true GB287701A (en) 1928-04-26

Family

ID=9700506

Family Applications (1)

Application Number Title Priority Date Filing Date
GB21925A Expired GB287701A (en) 1925-01-03 1925-01-03 Improvements in internal combustion turbines

Country Status (1)

Country Link
GB (1) GB287701A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2594629A (en) * 1947-03-29 1952-04-29 Exner Hellmuth Alfredo Arturo Jet-reaction motor, including gas nozzle generating steam
US2945619A (en) * 1954-09-21 1960-07-19 Mclure Carl Ballard Stage expansion reaction turbines
EP0153066A1 (en) * 1984-02-06 1985-08-28 A/S Kongsberg Väpenfabrikk Dual-entry centrifugal compressor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2594629A (en) * 1947-03-29 1952-04-29 Exner Hellmuth Alfredo Arturo Jet-reaction motor, including gas nozzle generating steam
US2945619A (en) * 1954-09-21 1960-07-19 Mclure Carl Ballard Stage expansion reaction turbines
EP0153066A1 (en) * 1984-02-06 1985-08-28 A/S Kongsberg Väpenfabrikk Dual-entry centrifugal compressor

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