WO2001083297A3 - Aircraft gas turbine engine having a centrifuge - Google Patents

Aircraft gas turbine engine having a centrifuge Download PDF

Info

Publication number
WO2001083297A3
WO2001083297A3 PCT/KR2001/000727 KR0100727W WO0183297A3 WO 2001083297 A3 WO2001083297 A3 WO 2001083297A3 KR 0100727 W KR0100727 W KR 0100727W WO 0183297 A3 WO0183297 A3 WO 0183297A3
Authority
WO
WIPO (PCT)
Prior art keywords
turbine engine
centrifuge
engine
avoiding
intake
Prior art date
Application number
PCT/KR2001/000727
Other languages
French (fr)
Other versions
WO2001083297A2 (en
Inventor
Jangshik Yun
Original Assignee
Jangshik Yun
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
Priority claimed from KR10-2000-0024157A external-priority patent/KR100368603B1/en
Priority claimed from KR2020000022096U external-priority patent/KR200210910Y1/en
Application filed by Jangshik Yun filed Critical Jangshik Yun
Publication of WO2001083297A2 publication Critical patent/WO2001083297A2/en
Publication of WO2001083297A3 publication Critical patent/WO2001083297A3/en

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
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/055—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with intake grids, screens or guards
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles

Abstract

This invention relates to aircraft turbine engine for preventing an aviation accident by segregating F.O.D. entering the engine during air intake. It is to provide protection apparatus for an turbine engine that does not interfere with the intake air flow while providing means to separate birds, hail and sands etc. The centrifuge (2) is disconnected with the shaft of turbine engine (10) for avoiding engine failure due to extreme vibration shock and rotated freely with the flow of intake air to generate a centrifugal power by utilizing several fans (3) on the surface of elliptical shell (4), and it can be operated only at the time of landing, take-off or emergency with an automatic controlled hydraulic system for avoiding aerodynamic drag and waist of fuel during cruise. Also, it has advantages to increase mechanical life of turbine engine with clean air and thrust power with improving compression effect on the structure of centrifuge.
PCT/KR2001/000727 2000-05-04 2001-05-04 Aircraft gas turbine engine having a centrifuge WO2001083297A2 (en)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
KR2000-24157 2000-05-04
KR10-2000-0024157A KR100368603B1 (en) 2000-05-04 2000-05-04 aircraft gas turbine engine having a centrifuge
KR2000-22096U 2000-08-02
KR2020000022096U KR200210910Y1 (en) 2000-08-02 2000-08-02 aircraft gas turbine engine having an automatic control centrifuge

Publications (2)

Publication Number Publication Date
WO2001083297A2 WO2001083297A2 (en) 2001-11-08
WO2001083297A3 true WO2001083297A3 (en) 2002-03-21

Family

ID=26637916

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/KR2001/000727 WO2001083297A2 (en) 2000-05-04 2001-05-04 Aircraft gas turbine engine having a centrifuge

Country Status (1)

Country Link
WO (1) WO2001083297A2 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10215551A1 (en) * 2002-04-09 2003-10-23 Rolls Royce Deutschland Turboprop aircraft engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3993463A (en) * 1975-08-28 1976-11-23 The United States Of America As Represented By The Secretary Of The Army Particle separator for turbine engines of aircraft
US4004760A (en) * 1975-03-25 1977-01-25 Mitsubishi Jukogyo Kabushiki Kaisha Device for preventing foreign matters from being sucked into a gas turbine engine for an aircraft
US4527387A (en) * 1982-11-26 1985-07-09 General Electric Company Particle separator scroll vanes
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4004760A (en) * 1975-03-25 1977-01-25 Mitsubishi Jukogyo Kabushiki Kaisha Device for preventing foreign matters from being sucked into a gas turbine engine for an aircraft
US3993463A (en) * 1975-08-28 1976-11-23 The United States Of America As Represented By The Secretary Of The Army Particle separator for turbine engines of aircraft
US4527387A (en) * 1982-11-26 1985-07-09 General Electric Company Particle separator scroll vanes
US5123240A (en) * 1990-03-19 1992-06-23 General Electric Co. Method and apparatus for ejecting foreign matter from the primary flow path of a gas turbine engine

Also Published As

Publication number Publication date
WO2001083297A2 (en) 2001-11-08

Similar Documents

Publication Publication Date Title
US11673678B2 (en) Gas-electric propulsion system for an aircraft
RU2641955C2 (en) Aircraft with turbojet engine with opposite rotation fans
US9254924B2 (en) Pressure influencing assembly for an aircraft auxiliary system
US6845606B2 (en) Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation
EP0459816B1 (en) Gas turbine engine powered aircraft environmental control system and boundary layer bleed
US7850116B2 (en) Ducted open rotor apparatus and method
EP1878904A2 (en) Thrust reverser assembly for a gas turbine engine and method of operating same
US8308423B2 (en) Variable area fan nozzle for accommodating a foreign object strike event
EP2096271A2 (en) System and method for passive cooling of gas turbine engine control components
CN101297107B (en) Turbofan engine for stol aircraft
EP2860113B1 (en) Engine mounted inlet plenum for a rotorcraft
US20210171212A1 (en) Hybrid turbine engine with selective electrical module engagement
US8790079B2 (en) Ram air turbine inlet
CN108952971A (en) Control the compressor of turbogenerator
US10718272B2 (en) Variable-geometry boundary layer diverter
US10974813B2 (en) Engine nacelle for an aircraft
WO2001083297A3 (en) Aircraft gas turbine engine having a centrifuge
Dorobat et al. Turboprop engine nacelle optimization for flight increased safety and pollution reduction
GB1302228A (en)
RU2361779C1 (en) Fuselage air bleed for powering aircraft systems
RU2704643C1 (en) Helicopter
Moult The development of the Goblin engine
RU1837035C (en) Carrier system of vertical take-off and landing flying vehicle
Clark et al. Development of the AV-8B propulsion system
Ciepluch The NASA quiet engines

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A2

Designated state(s): US

AL Designated countries for regional patents

Kind code of ref document: A2

Designated state(s): GB

121 Ep: the epo has been informed by wipo that ep was designated in this application
AK Designated states

Kind code of ref document: A3

Designated state(s): US

AL Designated countries for regional patents

Kind code of ref document: A3

Designated state(s): GB

32PN Ep: public notification in the ep bulletin as address of the adressee cannot be established

Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 69(1) EPC (EPO FORM 1205A DATED 07-02-2003)

122 Ep: pct application non-entry in european phase