JPS55107038A - Small jet engine for model aircraft - Google Patents

Small jet engine for model aircraft

Info

Publication number
JPS55107038A
JPS55107038A JP1533579A JP1533579A JPS55107038A JP S55107038 A JPS55107038 A JP S55107038A JP 1533579 A JP1533579 A JP 1533579A JP 1533579 A JP1533579 A JP 1533579A JP S55107038 A JPS55107038 A JP S55107038A
Authority
JP
Japan
Prior art keywords
turbine
blades
jet engine
chamber
model aircraft
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
JP1533579A
Other languages
Japanese (ja)
Inventor
Akira Naito
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 JP1533579A priority Critical patent/JPS55107038A/en
Publication of JPS55107038A publication Critical patent/JPS55107038A/en
Pending legal-status Critical Current

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Abstract

PURPOSE: To increase thrust force and decrease damage due to overheat of a turbine of a jet engine designed for a model aircraft, by reducing the scale of a real-sized jet engine, with its turbine being positioned in front of the combustion chamber.
CONSTITUTION: An external cylinder 1 builds in a combustion chamber 11 in the rear, turbine chamber 12 at the center, compression chamber 13 in the front, injection port 14 at the rear end and suction port 15 at the front/end. Compressor blades 21 are projected in the compression chamber 13 and a stators 16 between the blades. Blades 31 of the turbine 3 are connected with annular belt 32 from which turbine blades 33 are projected externally. Gas from a fuel tank 6 is injected toward the turbine blades 33. Since pressurized precombustion fuel is blasted, the rotor 3 suffers no overheat nor requires use of special heat-resisting material.
COPYRIGHT: (C)1980,JPO&Japio
JP1533579A 1979-02-13 1979-02-13 Small jet engine for model aircraft Pending JPS55107038A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP1533579A JPS55107038A (en) 1979-02-13 1979-02-13 Small jet engine for model aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP1533579A JPS55107038A (en) 1979-02-13 1979-02-13 Small jet engine for model aircraft

Publications (1)

Publication Number Publication Date
JPS55107038A true JPS55107038A (en) 1980-08-16

Family

ID=11885905

Family Applications (1)

Application Number Title Priority Date Filing Date
JP1533579A Pending JPS55107038A (en) 1979-02-13 1979-02-13 Small jet engine for model aircraft

Country Status (1)

Country Link
JP (1) JPS55107038A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20040079218A (en) * 2003-03-06 2004-09-14 이재창 Jet engine using exhaust gas
KR100521393B1 (en) * 2001-07-18 2005-10-14 이재창 Jet engine using exhaust gas
JP2008019862A (en) * 2007-06-27 2008-01-31 Matsuura Matsue Low pressure turbine driving method and low pressure turbine driving apparatus therefor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100521393B1 (en) * 2001-07-18 2005-10-14 이재창 Jet engine using exhaust gas
KR20040079218A (en) * 2003-03-06 2004-09-14 이재창 Jet engine using exhaust gas
JP2008019862A (en) * 2007-06-27 2008-01-31 Matsuura Matsue Low pressure turbine driving method and low pressure turbine driving apparatus therefor

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