WO2001083297A2 - Aircraft gas turbine engine having a centrifuge - Google Patents

Aircraft gas turbine engine having a centrifuge Download PDF

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Publication number
WO2001083297A2
WO2001083297A2 PCT/KR2001/000727 KR0100727W WO0183297A2 WO 2001083297 A2 WO2001083297 A2 WO 2001083297A2 KR 0100727 W KR0100727 W KR 0100727W WO 0183297 A2 WO0183297 A2 WO 0183297A2
Authority
WO
WIPO (PCT)
Prior art keywords
centrifuge
turbine engine
fans
hydraulic
elliptical shell
Prior art date
Application number
PCT/KR2001/000727
Other languages
French (fr)
Other versions
WO2001083297A3 (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

Definitions

  • This invention relates to aircraft turbine engine for preventing an aviation
  • Fig. 1 generally it is installed with subsonic duct 30 for reducing
  • the centrifuge 2 is disconnected with the shaft of turbine engine 10 for
  • Fig.1 is an illustrative view for a turbine engine as in prior art
  • Fig.2 is an illustrative view for a turbine engine having a centrifuge as in
  • Fig.3 is an axial sectional view for a bearing installed on a turbine engine as
  • Fig.4 is a front view for a turbine engine as in this invention
  • Fig.5 is a side view for a turbine engine as in this mvention
  • Fig.6 shows an embodiment of operation as in this invention
  • Fig.7 is an illustrative view for an automatic control centrifuge as in this
  • Fig.8 shows a projection of fan as in this invention
  • Fig.9 shows a removal of fan as in this invention
  • Fig. 2 is an illustrative view for a turbine engine having a centrifuge as in
  • a centrifuge 2 is mounted on the inlet duct to segregate any kinds of F.O.D.
  • dynamical power comprising:
  • An elliptical shell 4 installed on the inlet of a duct 30 as shown in Fig. 2;
  • Fig. 7 is an illustrative view for an automatic control centrifuge as in this
  • dynamical power comprising:
  • An ultrasonic sensor 42 installed at the leading point of centrifuge 2;
  • An automatic control unit 40 connected with an ultrasonic sensor 42
  • a hydraulic piston 54 and cylinder 52 installed inside of said hydraulic
  • a coupling 56 connected at said hydraulic piston 54 through a connecting
  • a connecting rod 58 connected with fans 6 through tension cables 59 as
  • Means including pulleys 62, springs 64 and spring holders 68 for retracting fans 6 as shown in Fig. 8 & 9;
  • Fig. 6 shows an embodiment of operation as in this invention
  • actuator 50 is released an hydraulic pressure through hydraulic cable 51 in
  • fans is reverted to the outer surface of an elliptical shell
  • automatic control unit 40 could be converted from a
  • a principal object of the present invention is to provide a safe apparatus to

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Centrifugal Separators (AREA)

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.

Description

AIRCRAFT GAS TURBINE ENGINE HAVING
A CENTRIFUGE
Technical Field
This invention relates to aircraft turbine engine for preventing an aviation
accident by segregating any kinds of F.O.D.(Foreign Object Damage), like
birds, hail, soil & sands etc. entering the engine during air intake, and for
supplying clean air in to the engine.
Background Art
It is well known to generate thrust power of the gas turbine engine with the
process of intake, compression, explosion and exhaust by utilizing air as
shown in Fig. 1, generally it is installed with subsonic duct 30 for reducing
velocity of inlet air as shown in Fig. 1.
Heretofore, it has a safety hazard with F.O.D., like birds, hail, soil and sands
causing a critical damage for an internal turbine engine or a severe
malfunction of an aircraft in flight, Also it is known to reduce the thermal
efficiency with an heavy rain and diminish mechanical life of turbine engine
with corrosion material.
Thus some aircraft turbine engines have been commonly provided with inlet
covers, such as screens and the like to prevent ingestion of sizable F.O.D.,
however, screens have been found to produce a safety hazard when ice forms over the screen, impair the efficiency of the engine by interfering
with normal air flow to the turbine engine, and break up frequently with
disastrous results to the engine.
One type of prior art, introduced in protection element against bird ingestion
into aircraft turbines, U.S. Pat. No. 6,089,824 filed in USA, provide a means
to break up a foreign object in to smaller, harmless pieces, however, it may
have some damage on the shaft of a turbine engine due to an extreme
vibration shock. Since a turbine engine has a tubular shaft attached to its
center so that the shaft rotates at the same speed as the turbine.
Disclosure of Invention
This present invention clears the above problem with the centrifuge by
spinning freely with the aero dynamical power of intake air at the inlet of
duct.
In accordance with the principles of the present invention, there is provided
an apparatus for segregating any kinds of F.O.D., like birds, hail and sands
in the intake air entering in a turbine engine.
The centrifuge 2 is disconnected with the shaft of turbine engine 10 for
avoiding an 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 an 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 minimizing aerodynamic drag and waist of
fuel due to the operation of a centrifuge during cruise flight.
Also it has several advantages to improve mechanical life of turbine
engine with clean air and thrust power with improving compression effect
on the structure of centrifuge.
Brief Description of the Drawings
Fig.1 is an illustrative view for a turbine engine as in prior art
Fig.2 is an illustrative view for a turbine engine having a centrifuge as in
this invention
Fig.3 is an axial sectional view for a bearing installed on a turbine engine as
in this invention
Fig.4 is a front view for a turbine engine as in this invention
Fig.5 is a side view for a turbine engine as in this mvention
Fig.6 shows an embodiment of operation as in this invention
Fig.7 is an illustrative view for an automatic control centrifuge as in this
invention
Fig.8 shows a projection of fan as in this invention
Fig.9 shows a removal of fan as in this invention
- Mark for major part of drawings - 2: centrifuge 4: shell
6: fin shaped fan 10: turbine engine
30: air inlet 40: automatic control unit
42: ultrasonic sensor 50: hydraulic actuator
Best Mode for Carrying Out the Invention
Preferred embodiments of the present invention will be explained hereafter
with reference to accompanied embodiments.
It is well known machine about the structure and function of a gas turbine
engine as in prior art on the Fig. 1; therefore, it is not necessary to explain
here.
Fig. 2 is an illustrative view for a turbine engine having a centrifuge as in
this invention.
A centrifuge 2 is mounted on the inlet duct to segregate any kinds of F.O.D.
like birds, hail and sands in the intake air entering to a turbine engine 10 as
in this invention.
In a gas turbine engine 10 having a centrifuge 2 rotated freely by the aero
dynamical power, comprising:
An elliptical shell 4 installed on the inlet of a duct 30 as shown in Fig. 2;
The shaft 36 of a centrifuge 2 fixed on the two bearings 32 as shown in Fig.
2; Two bearings 32 installed at the center hub of duct 30 with supporters 34 as
shown in Fig. 2 & 3;
Several fans 6 fixed on said elliptical shell and formed with a long shape of
a fish fin as shown in Fig. 4 & 5;
Fig. 7 is an illustrative view for an automatic control centrifuge as in this
invention.
In a gas turbine engine having a centrifuge rotated freely by the aero
dynamical power, comprising:
An ultrasonic sensor 42 installed at the leading point of centrifuge 2;
An automatic control unit 40 connected with an ultrasonic sensor 42
through line 44;
A hydraulic actuator 50 connected with an automatic control unit 40
through a hydraulic cable 51 ;
A hydraulic piston 54 and cylinder 52 installed inside of said hydraulic
actuator as shown in Fig. 8 & 9;
A coupling 56 connected at said hydraulic piston 54 through a connecting
rod 58 to be rotated inside of a centrifuge 2 as shown in Fig. 8 & 9;
A connecting rod 58 connected with fans 6 through tension cables 59 as
shown in Fig. 8 & 9;
Means including pulleys 62, springs 64 and spring holders 68 for retracting fans 6 as shown in Fig. 8 & 9;
Slots 5 shaped on the elliptical shell 4 for the path of fans 6 as shown in Fig.
8 & 9.
Alternatively it is composed of with a solenoid magnetic unit (not shown)
instead of said hydraulic actuator for retracting electrically said fans on the
elliptical shell.
Fig. 6 shows an embodiment of operation as in this invention,
It can be segregated for any kinds of a F.O.D. like birds, hail, sands and
heavy rain which is heavier than air in density by separating with centrifugal
power of a rotating fans 6 during passing through the surface of an elliptical
shell 2, therefore it can be taken only clean air without a F.O.D. to a turbine
engine through duct 30.
Referring to Fig. 7, 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 due to the centrifuge during cruise flight
by utilizing an automatic control unit 40, also it can be stopped operating by
a pilot's control during cruise flight.
Referring to Fig. 8, in the event of a pilot applies an automatic control unit
40, it is applied with an hydraulic pressure in an hydraulic cylinder 52 to
push an hydraulic piston 54 forwardly, and then a connecting rod 58 is pulled with a joint 56 of a shaft forwardly, wherein said joint 56 is a kind of
coupling for an hydraulic piston 54 and a rotatory connecting rod 58 inside
of a centrifuge 2, and then connecting bolt 68 is pulled with a tension cable
59 through a pulley 62 to retract with changing to the direction of square
while depressing an extension spring 64, finally fans 6 is completed to
remove from the outer surface of an elliptical shell 4 through slot 5 as
shown in Fig. 9, and the centrifuge should be stopped spinning because
there is no an aero dynamical power of rotation due to removal of fans on
the surface of an elliptical shell 4.
In the event of an emergency with suddenly appearing of birds, hail, sands
and heavy rain during normal flight without operating a centrifuge 2 on the
state of removal fans 6 from outer surface of an elliptical shell 4, an
ultrasonic sensor 42 fixed at the leading point of centrifuge 2 is
automatically become aware of F.O.D. approaching near in the front of an
aircraft, and then the signal of said ultrasonic sensor 42 is transmitted to an
automatic control unit 40 through a sensor line 44, further, an hydraulic
actuator 50 is released an hydraulic pressure through hydraulic cable 51 in
accordance with an order of an automatic control unit 40 automatically.
Referring to Fig. 8, fans is reverted to the outer surface of an elliptical shell
4 through slot 5 with an extension force of spring 64 due to a released pressure in an hydraulic actuator 50, therefore, the centrifuge 2 is started
spinning with the aero dynamical power of fans 6, and then the F.O.D. can
be segregated to out of inlet duct 30 in the direction of circumference after
hitting with fans 6.
Furthermore the automatic control unit 40 could be converted from a
mechanical apparatus to an electrical apparatus, so that it can be replaced
with a solenoid magnetic, an electric line and an electro magnetic instead of
an hydraulic actuator 50, an hydraulic cable 51 and a piston 54 each other
for retracting electrically fans 6 as in the above principle of hydraulic
operation.
Industrial Applicability
A principal object of the present invention is to provide a safe apparatus to
prevent aviation accident due to F.O.D. like birds, hail, sands and heavy rain
in the intake air entering in a turbine engine.
Also, it has several advantages to improve the mechanical life of a turbine
engine with clean inlet air, and to increase the thrust power with a better
compression effect on the structure of centrifuge, and to expand for utilizing
a turbine engine as in the power of vehicle on ground sea or water with
segregating any kinds of F.O.D. like birds, hail, sands and scattering water.

Claims

What is claimed is:
1. In a gas turbine engine having a centrifuge rotated freely by the aero
dynamical power, comprising:
An elliptical shell installed on the inlet of a duct;
The shaft of said centrifuge fixed on the two bearings;
Said two bearings installed at the center hub of said duct with supporters;
Several fans fixed on said elliptical shell;
Said several fans formed with a long shape of a fin.
2. In a gas turbine engine having a centrifuge with an automatic control unit,
comprising:
An ultrasonic sensor installed at the leading point of said centrifuge;
An automatic control unit connected with said ultrasonic sensor;
A hydraulic actuator connected with said automatic control unit through
hydraulic cable;
A hydraulic piston and a hydraulic cylinder installed in said hydraulic
actuator;
A coupling connected at said hydraulic piston through a connecting rod to
be rotated inside of said centrifuge;
A connecting rod connected with said fans via pulleys through tension
cables; Means including said pulleys, springs and spring holders for retracting said
fans;
Slots shaped on the elliptical shell for the path of said fans.
3. The apparatus of claim 2, further comprising a solenoid magnetic unit
instead of said hydraulic actuator for retracting said fans on said elliptical
shell.
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
KR10-2000-0024157A KR100368603B1 (en) 2000-05-04 2000-05-04 aircraft gas turbine engine having a centrifuge
KR2000-24157 2000-05-04
KR2020000022096U KR200210910Y1 (en) 2000-08-02 2000-08-02 aircraft gas turbine engine having an automatic control centrifuge
KR2000-22096U 2000-08-02

Publications (2)

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

Cited By (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

Cited By (2)

* 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
US6746207B1 (en) 2002-04-09 2004-06-08 Rolls-Royce Deutschland Ltd & Co Kg Turboprop aircraft engine

Also Published As

Publication number Publication date
WO2001083297A3 (en) 2002-03-21

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