KR20110123319A - Secondary tail pipe of jet engine - Google Patents

Secondary tail pipe of jet engine Download PDF

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Publication number
KR20110123319A
KR20110123319A KR1020100042739A KR20100042739A KR20110123319A KR 20110123319 A KR20110123319 A KR 20110123319A KR 1020100042739 A KR1020100042739 A KR 1020100042739A KR 20100042739 A KR20100042739 A KR 20100042739A KR 20110123319 A KR20110123319 A KR 20110123319A
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KR
South Korea
Prior art keywords
jet engine
tail pipe
jet
injection port
main
Prior art date
Application number
KR1020100042739A
Other languages
Korean (ko)
Inventor
경종만
경원식
경훈식
경윤식
임현욱
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경종만
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.)
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Publication date
Application filed by 경종만 filed Critical 경종만
Priority to KR1020100042739A priority Critical patent/KR20110123319A/en
Publication of KR20110123319A publication Critical patent/KR20110123319A/en

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    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64DEQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02Aircraft characterised by the type or position of power plant
    • B64D27/16Aircraft characterised by the type or position of power plant of jet type
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/52Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing

Abstract

PURPOSE: An auxiliary injection port of a jet engine is provided to reduce fuel consumption by improving the energy efficiency of a jet-propelled aircraft. CONSTITUTION: An auxiliary injection port of a jet engine is installed at the slightly rear of a main injection port through a main tail pipe(2) and multiple support units(4) of a jet engine(1). The auxiliary injection port maximizes energy efficiency by generating driving force two or more times through one time of injection.

Description

제트엔진 보조 분사구 {SECONDARY TAIL PIPE OF JET ENGINE}Jet Engine Auxiliary Nozzle {SECONDARY TAIL PIPE OF JET ENGINE}
제트 비행기Jet airplane
비행하기 위하여는 엄청난 연료소비를 수반 할 수밖에 없는 제트 비행기에 있어서 그 에너지를 배가시키기 위한 기술이다It is a technique to multiply the energy of a jet plane that must involve enormous fuel consumption in order to fly.
공지의 제트 비행기는 엄청난 에너지의 폭발 가스가 단 한번의 추진력을 발생하고 그 에너지를 그대로 유지한 체 대기 중으로 소멸되고 마는데 이렇게 무의미하게 소멸되는 에너지를 재활용하는 것이 과제이다.Known jet planes have a huge amount of explosive gas that can be dissipated into the body atmosphere with only one propulsion and maintain that energy. The task is to recycle this irrelevant energy.
본 발명은 이렇게 낭비되는 에너지를 한번 더 활용하기 위하여 주 분사구 뒤에 제2의 보조 분사구를 설치하여 분사된 가스가 제2의 분사구를 관통하여 한번 더 추진력을 발생하도록 하여 이의 효율을 배가할 수 있게 하였다.In order to utilize the wasted energy once more, a second auxiliary injection hole is installed behind the main injection hole, so that the injected gas can generate thrust once again through the second injection hole, thereby doubling its efficiency. .
지구상 문명의 이기 중에서 가장 많은 연료를 사용하는 제트비행기의 에너지 효율을 배가시킴으로 연료 소비를 줄일 수 있어 비용절감은 물론 Co2 배출을 줄이는 일거양득의 효과가 있다.By doubling the energy efficiency of jet airplanes that use the most fuel among the world's civilizations, fuel consumption can be reduced, thereby reducing costs and reducing CO2 emissions.
본 발명을 첨부된 도면에 의거하여 상세히 설명하면 다음과 같다.Hereinafter, the present invention will be described in detail with reference to the accompanying drawings.
도1은 본 발명의 전체구성 설치예시 단면도로서 공지의 엔진 테일 파이프(2)와 연결구(4) 수개에 의해 주 테일 파이프(2)보다 약간 뒤에 제2의 테일 파이프(3)를 고정 설치하여 구성된 것으로 이렇게 된 본 발명은 폭발가스가 주테일 파이프(2)를 빠져 나오는 순간 추진력이 발생되고 유속 에너지를 거의 그대로 갖은 분사 가스가 다시 제2의 테일 파이프(3)를 관통하여 또다시 추진력을 발생하게 되어 한번의 가스분사로 두 번의 추진력을 발생하도록 하였다. 효과 경우에 따라서는 보조 분사구를 2단 3단으로 설치하여 더 많은 추진력을 얻을 수 있다. 도2는 주 배기구와 보조 배기구를 연결 설치한 예시도 이고 도3은 주 배기구 뒤에 프로펠러(5)를 설치한 예시도 이다.FIG. 1 is a cross-sectional view illustrating an overall configuration of the present invention, in which a second tail pipe 3 is fixedly installed slightly behind the main tail pipe 2 by a number of known engine tail pipes 2 and connectors 4. According to the present invention, the propulsion force is generated when the explosive gas exits the main tail pipe (2), and the injection gas having almost the same flow velocity energy passes again through the second tail pipe (3) to generate the propulsion force. In this case, two propulsion forces were generated by one gas injection. In some cases, additional propulsion can be achieved by installing auxiliary nozzles in two stages and three stages. 2 is an exemplary diagram in which a main exhaust port and an auxiliary exhaust port are connected and installed, and FIG. 3 is an exemplary diagram in which a propeller 5 is installed behind the main exhaust port.
도1은 본 발명의 전체 구성 예시단면도Figure 1 is a cross-sectional view of the overall configuration of the present invention
도2는 본 발명의 주 배기구와 보조 배기구의 연결 예시도2 is a diagram illustrating a connection between a main exhaust port and an auxiliary exhaust port of the present invention;
도3은 본 발명의 주 배기구와 보조 프로펠러의 설치 예시도Figure 3 is an installation example of the main exhaust port and the auxiliary propeller of the present invention

Claims (1)

  1. 제트엔진(1)의 메인 테일 파이프(2)와 지지구(4) 수개에 의해 주 분사구보다 약간 뒤에 제2의 보조 분사구를 고정 설치하여 한번의 분사로 두 번 또는 세 번의 추진력을 발생하게 하여 에너지 효율을 극대화 할 수 있도록 된 제트비행기.The second auxiliary nozzle is fixedly installed slightly behind the main nozzle by the main tail pipe 2 and the support 4 of the jet engine 1 to generate two or three propulsion forces in one injection. Jet planes for maximum efficiency.
KR1020100042739A 2010-05-07 2010-05-07 Secondary tail pipe of jet engine KR20110123319A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020100042739A KR20110123319A (en) 2010-05-07 2010-05-07 Secondary tail pipe of jet engine

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Application Number Priority Date Filing Date Title
KR1020100042739A KR20110123319A (en) 2010-05-07 2010-05-07 Secondary tail pipe of jet engine

Publications (1)

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KR20110123319A true KR20110123319A (en) 2011-11-15

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KR1020100042739A KR20110123319A (en) 2010-05-07 2010-05-07 Secondary tail pipe of jet engine

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018097359A1 (en) * 2016-11-25 2018-05-31 김기태 Turbojet drone

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018097359A1 (en) * 2016-11-25 2018-05-31 김기태 Turbojet drone

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