GB511331A - Internal combustion turbine - Google Patents

Internal combustion turbine

Info

Publication number
GB511331A
GB511331A GB27982/38A GB2798238A GB511331A GB 511331 A GB511331 A GB 511331A GB 27982/38 A GB27982/38 A GB 27982/38A GB 2798238 A GB2798238 A GB 2798238A GB 511331 A GB511331 A GB 511331A
Authority
GB
United Kingdom
Prior art keywords
cylinders
turbine
engine
shaft
gas
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
GB27982/38A
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.)
HARALD DALE
Original Assignee
HARALD DALE
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 HARALD DALE filed Critical HARALD DALE
Priority to GB27982/38A priority Critical patent/GB511331A/en
Publication of GB511331A publication Critical patent/GB511331A/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
    • F02C5/00—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion
    • F02C5/06—Gas-turbine plants characterised by the working fluid being generated by intermittent combustion the working fluid being generated in an internal-combustion gas generated of the positive-displacement type having essentially no mechanical power output
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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

Abstract

511,331. Motor power plant; elastic-fluid turbines. DALE, H. Sept. 26, 1938, No. 27982. [Class 110 (iii)] In a motor plant comprising an internalcombustion engine delivering exhaust gas to a turbine, the gas is compressed in cylinders 14 and then passes to ignition cylinders 16 of smaller capacity, the exhaust gas in part acting upon the turbine rotor 54 and in part upon pistons 17 which are on the same shaft as the pistons 15 of cylinders 14. The engine has a plurality of radial cylinders 14, 16, communicating by ports 36 and sleeve valves 35, each piston 15 being on suction stroke when its corresponding piston 17 is on explosion stroke, valve 35 opening exhaust passage 38 before the end of the explosion stroke. The rotor 54 comprises discs 60 connected by rim spacers 65 which carry the turbine blades 55, and the motive gas entrains cooling and scavenging air from ports 63 leading to a duct 62 in the turbine shaft 50 which is separate from but coaxial with the engine shaft 13.
GB27982/38A 1938-09-26 1938-09-26 Internal combustion turbine Expired GB511331A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB27982/38A GB511331A (en) 1938-09-26 1938-09-26 Internal combustion turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27982/38A GB511331A (en) 1938-09-26 1938-09-26 Internal combustion turbine

Publications (1)

Publication Number Publication Date
GB511331A true GB511331A (en) 1939-08-16

Family

ID=10268376

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27982/38A Expired GB511331A (en) 1938-09-26 1938-09-26 Internal combustion turbine

Country Status (1)

Country Link
GB (1) GB511331A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2138075A (en) * 1983-04-12 1984-10-17 Specialty Systems Inc Driving a turbine by ic engine exhaust gases
WO2008037075A1 (en) * 2006-09-26 2008-04-03 Larry Kathan Rotary internal combustion engine
WO2016201551A1 (en) * 2015-06-16 2016-12-22 Pratt & Whitney Canada Corp. Compound engine assembly with exhaust pipe nozzle

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2138075A (en) * 1983-04-12 1984-10-17 Specialty Systems Inc Driving a turbine by ic engine exhaust gases
WO2008037075A1 (en) * 2006-09-26 2008-04-03 Larry Kathan Rotary internal combustion engine
JP2010504471A (en) * 2006-09-26 2010-02-12 カサン，ラリー Rotary internal combustion engine
US8485156B2 (en) 2006-09-26 2013-07-16 Larry Kathan Rotary internal combustion engine
WO2016201551A1 (en) * 2015-06-16 2016-12-22 Pratt & Whitney Canada Corp. Compound engine assembly with exhaust pipe nozzle
US9759128B2 (en) 2015-06-16 2017-09-12 Pratt & Whitney Canada Corp. Compound engine assembly with exhaust pipe nozzle
US10393014B2 (en) 2015-06-16 2019-08-27 Pratt & Whitney Canada Corp. Engine assembly with exhaust pipe nozzle

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