CN104712457A - Hypersonic aircraft engine with low fuel consumption - Google Patents

Hypersonic aircraft engine with low fuel consumption Download PDF

Info

Publication number
CN104712457A
CN104712457A CN201310665561.9A CN201310665561A CN104712457A CN 104712457 A CN104712457 A CN 104712457A CN 201310665561 A CN201310665561 A CN 201310665561A CN 104712457 A CN104712457 A CN 104712457A
Authority
CN
China
Prior art keywords
aircraft engine
fuel consumption
aircraft
low fuel
engine
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
CN201310665561.9A
Other languages
Chinese (zh)
Inventor
黄乐歌
Original Assignee
黄乐歌
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 黄乐歌 filed Critical 黄乐歌
Priority to CN201310665561.9A priority Critical patent/CN104712457A/en
Publication of CN104712457A publication Critical patent/CN104712457A/en
Pending legal-status Critical Current

Links

Abstract

The invention mainly provides an aircraft engine manufactured through a new theory. The aircraft engine is mainly characterized in that a high-power generator set is additionally arranged at the front end of a turbofan engine, and working medium gas (i.e., compressed air) in an outer duct is electrolyzed for plasma jet flow, so that the purpose that an aircraft conducts low-fuel-consumption hypersonic flight is achieved.

Description

Low oil consumption hypersonic speed aeroengine
One, technical field
The present invention relates to a kind of motor, belong to aircraft engine field.
Two, background technique
Airscrew engine aircraft, achieve the dream of mankind's flight, jet-propelled owing to adopting the new structure being different from propeller cavitation at motor, although can sound barrier be broken through, and hypersonic speed can not be reached, upper two kinds of motors improve howsoever, can only be to increase on its original base, and do not have the breakthrough of matter, because this is that its basic principle institute is determined.
For above-mentioned first two motor, the invention provides a kind of new engine principles, to reach the breakthrough of matter, is that aircraft realizes low oil consumption hypersonic flight.
The present invention mainly arranges the garden hoop having inlayed permanent magnet in the front fan of turbofan engine any one group or array blade outer end, and coil is set inside corresponding by-pass air duct, form generator set, again outside main duct jet nozzle and inside by-pass air duct jet nozzle, zirconium or hafnium positive and negative electrode are set, reach the Working medium gas (i.e. pressurized air) of electrolysis by-pass air duct, become plasma jet, because plasma jet has very large kinetic energy and impact force, can spray from jet pipe with high speed (being about 800 ~ 2000m/s), aircraft can be made to reach the hypersonic flying speed of 2880 ~ 7200km/h.Its fuel consumption is only equivalent to or slightly larger than the oil consumption (can be considered baseline power oil consumption) of turbojet engine, and its active force is plasma jet, its power consumption is that the Working medium gas (i.e. pressurized air) of by-pass air duct is as its energy, the object that aircraft reaches low oil consumption and hypersonic flight, and its voyage and at that time rapid-result proportional relation.
The principle of the invention is advanced, and only need do some to turbofan engine and improve, gram to compress as far as possible on the motor of gross weight for unit of measurement, though add the weight of generator set, but motor is not take weight as primary concern fortunately, but calculate with thrust weight ratio, this will feel very atypical concerning the people only having inertial thinking, accepts new principle and needs courage and penetrating and correct judgement!
Accompanying drawing explanation
Accompanying drawing is structural representation of the present invention
1. coil, 2. permanent magnet, 3. by-pass air duct Working medium gas, 4. zirconium or hafnium negative electrode, 5. zirconium or hafnium positive electrode in figure.

Claims (1)

1. the present invention's mainly electrolysis by-pass air duct Working medium gas (pressurized air), is plasma jet, is purport marrow of the present invention, and all without claimant's license, user all should be considered as infringement.
CN201310665561.9A 2013-12-11 2013-12-11 Hypersonic aircraft engine with low fuel consumption Pending CN104712457A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201310665561.9A CN104712457A (en) 2013-12-11 2013-12-11 Hypersonic aircraft engine with low fuel consumption

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201310665561.9A CN104712457A (en) 2013-12-11 2013-12-11 Hypersonic aircraft engine with low fuel consumption

Publications (1)

Publication Number Publication Date
CN104712457A true CN104712457A (en) 2015-06-17

Family

ID=53412105

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201310665561.9A Pending CN104712457A (en) 2013-12-11 2013-12-11 Hypersonic aircraft engine with low fuel consumption

Country Status (1)

Country Link
CN (1) CN104712457A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107013268A (en) * 2015-11-23 2017-08-04 通用电气公司 Compression radome fairing for jet engine exhaust
CN111636974A (en) * 2020-06-08 2020-09-08 清华大学 High-efficiency propeller with large thrust-weight ratio and secondary expansion acting capacity
CN111636976A (en) * 2020-06-08 2020-09-08 清华大学 Three-duct high-thrust-weight-ratio efficient power propeller

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075115A (en) * 1961-03-27 1963-01-22 John W Flowers Ion source with space charge neutralization
US5539274A (en) * 1993-09-07 1996-07-23 Tokyo Electron Limited Electron beam excited plasma system
CN1293303A (en) * 1999-10-16 2001-05-02 王世其 Electromagnetically propulsive gas jet engine
CN1293307A (en) * 1999-10-16 2001-05-02 王世其 Electromagnetic plasma propeller
CN1314070A (en) * 1998-06-26 2001-09-19 汤姆森管电子有限公司 Plasma accelerator arrangement
CN1904358A (en) * 2005-07-26 2007-01-31 李晓辉 Plasma collision offect propeller

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3075115A (en) * 1961-03-27 1963-01-22 John W Flowers Ion source with space charge neutralization
US5539274A (en) * 1993-09-07 1996-07-23 Tokyo Electron Limited Electron beam excited plasma system
CN1314070A (en) * 1998-06-26 2001-09-19 汤姆森管电子有限公司 Plasma accelerator arrangement
CN1293303A (en) * 1999-10-16 2001-05-02 王世其 Electromagnetically propulsive gas jet engine
CN1293307A (en) * 1999-10-16 2001-05-02 王世其 Electromagnetic plasma propeller
CN1904358A (en) * 2005-07-26 2007-01-31 李晓辉 Plasma collision offect propeller

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107013268A (en) * 2015-11-23 2017-08-04 通用电气公司 Compression radome fairing for jet engine exhaust
CN107013268B (en) * 2015-11-23 2020-03-06 通用电气公司 Compression fairing for jet engine exhaust
US10920713B2 (en) 2015-11-23 2021-02-16 General Electric Company Compression cowl for jet engine exhaust
CN111636974A (en) * 2020-06-08 2020-09-08 清华大学 High-efficiency propeller with large thrust-weight ratio and secondary expansion acting capacity
CN111636976A (en) * 2020-06-08 2020-09-08 清华大学 Three-duct high-thrust-weight-ratio efficient power propeller
CN111636974B (en) * 2020-06-08 2021-05-28 清华大学 High-efficiency propeller with large thrust-weight ratio and secondary expansion acting capacity

Similar Documents

Publication Publication Date Title
US10000293B2 (en) Gas-electric propulsion system for an aircraft
CN104712457A (en) Hypersonic aircraft engine with low fuel consumption
Yinghong et al. Experimental investigation on airfoil suction side flow separation by pulse plasma aerodynamic actuation
Felder et al. Sensitivity of mission energy consumption to turboelectric distributed propulsion design assumptions on the N3-X hybrid wing body aircraft
EP2548802A3 (en) Aircraft versatile power system
CN203294315U (en) Supporting structure of power plant
Liu et al. Turboelectric distributed propulsion system modelling for hybrid-wing-body aircraft
CN205078365U (en) Jet engine
WO2010060595A3 (en) Air start unit for starting aircraft turbines
CN201083164Y (en) Turbine-rocket embedded type engine
Kang et al. Research on boundary layer ingestion effects of distributed propulsion configuration
Phan Leading edge embedded fan airfoil concept--A new powered high lift technology
KR20110123319A (en) Secondary tail pipe of jet engine
Chao et al. A conceptual analysis of an aircraft with rear-mounted open rotor engines
JIA et al. Numerical Investigation on Shroud Leakage Flow in Turbine Cascade [J]
CN203294316U (en) Power input rear shaft sleeve adjusting device
Pan et al. Flow separation control of lobed ejector/forced mixer by ventilation
Cai et al. Optimization design of a fan casing for reducing vibration
Shin et al. A two-dimensional numerical analysis of the unstart process in an inlet/isolator model
Whurr et al. Optimizing propulsive efficiency in aircraft with boundary layer ingesting distributed propulsion
Wang et al. Control methods for supersonic jet screech tones
CN109026438A (en) High efficiency jet propeller
Coleman Separation Control on Generic ROBIN Rotorcraft Fuselage Using Plasma Actuators
Min et al. Performance Prediction of Ducted Propeller Based on CFD Method
Giakoumakis Techno-economic and environmental risk assessment of a turbo-electric distributed propulsion system on a blended wing body aircraft

Legal Events

Date Code Title Description
PB01 Publication
C06 Publication
SE01 Entry into force of request for substantive examination
C10 Entry into substantive examination
WD01 Invention patent application deemed withdrawn after publication

Application publication date: 20150617

C02 Deemed withdrawal of patent application after publication (patent law 2001)