JPS5669422A - Gas turbine engine - Google Patents

Gas turbine engine

Info

Publication number
JPS5669422A
JPS5669422A JP14579179A JP14579179A JPS5669422A JP S5669422 A JPS5669422 A JP S5669422A JP 14579179 A JP14579179 A JP 14579179A JP 14579179 A JP14579179 A JP 14579179A JP S5669422 A JPS5669422 A JP S5669422A
Authority
JP
Japan
Prior art keywords
impeller
air
fuel
gas turbine
nozzle
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.)
Pending
Application number
JP14579179A
Other languages
Japanese (ja)
Inventor
Yoshio Wada
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 JP14579179A priority Critical patent/JPS5669422A/en
Publication of JPS5669422A publication Critical patent/JPS5669422A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To improve thermal efficiency, by providing a fuel combustor at a part of a rotary member.
CONSTITUTION: A gas turbine comprises an impeller A, a main pipe for supplying fuel and a casing. When the impeller A is rotated by an appropriate method, air is sucked from a port near the center of a passage 7 and accelerated by the impeller 4 of a centrifugal compressor because the impeller A has the same construction as the impeller 4. The air is supplied from a compression section 8 to a combustion chamber 9 while the air is compressed by centrifugal force. The air is then ejected from a nozzle 10 in a circumferential direction opposite to the direction of the rotation. The fuel is burned in the combustion chamber 9 to heat the compressed air to eject it from the nozzle 10 at a speed higher than the circumferential velocity of the impeller A. The impeller A is caused to start self-rotation by the reaction of the ejected air.
COPYRIGHT: (C)1981,JPO&Japio
JP14579179A 1979-11-11 1979-11-11 Gas turbine engine Pending JPS5669422A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP14579179A JPS5669422A (en) 1979-11-11 1979-11-11 Gas turbine engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP14579179A JPS5669422A (en) 1979-11-11 1979-11-11 Gas turbine engine

Publications (1)

Publication Number Publication Date
JPS5669422A true JPS5669422A (en) 1981-06-10

Family

ID=15393235

Family Applications (1)

Application Number Title Priority Date Filing Date
JP14579179A Pending JPS5669422A (en) 1979-11-11 1979-11-11 Gas turbine engine

Country Status (1)

Country Link
JP (1) JPS5669422A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6223537A (en) * 1985-05-08 1987-01-31 ホセ、ロレンソ、ロペス、サンチエス Rotary engine
JP2010133273A (en) * 2008-12-02 2010-06-17 Shuzo Onodera Rotary exhaust-type engine for air plane body

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6223537A (en) * 1985-05-08 1987-01-31 ホセ、ロレンソ、ロペス、サンチエス Rotary engine
JP2010133273A (en) * 2008-12-02 2010-06-17 Shuzo Onodera Rotary exhaust-type engine for air plane body

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