WO1999060268A1 - Bloc moteur pour aeronef - Google Patents

Bloc moteur pour aeronef Download PDF

Info

Publication number
WO1999060268A1
WO1999060268A1 PCT/IB1998/000743 IB9800743W WO9960268A1 WO 1999060268 A1 WO1999060268 A1 WO 1999060268A1 IB 9800743 W IB9800743 W IB 9800743W WO 9960268 A1 WO9960268 A1 WO 9960268A1
Authority
WO
WIPO (PCT)
Prior art keywords
power unit
duct
airfoil
airfoils
engine
Prior art date
Application number
PCT/IB1998/000743
Other languages
English (en)
Inventor
Zisis Gazos
Valentin Nazarov
Original Assignee
Otarid Consult Limited
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 Otarid Consult Limited filed Critical Otarid Consult Limited
Priority to PCT/IB1998/000743 priority Critical patent/WO1999060268A1/fr
Priority to AU70734/98A priority patent/AU7073498A/en
Publication of WO1999060268A1 publication Critical patent/WO1999060268A1/fr

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03H99/00—Subject matter not provided for in other groups of this subclass
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/025—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the by-pass flow being at least partly used to create an independent thrust component
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to a gas turbine engine, intended for any kind of flying vehicle power unit capable to create propulsion for the flight of flying vehicle, particularly aircraft.
  • the flight of the current flying vehicle is provided by means of devices for creation of lift and jet thrust of the power unit.
  • Gas turbine engines require a number of support systems in order to render the engine operational. All these components of a power unit and interfaces between them and the engine become increasingly complex as the number of associated systems increases in the process of technical development.
  • the power unit of the aircraft representing the turbojet engine having inlet gas generator and outlet assembly is known (CI. EP 0 519 823 B1, Int. CI. F 02 C 7/20, Date of publication: Dec. 21, 1994).
  • Its gas generator consists of compressor, combustion chamber and turbine.
  • Other power unit represents at least one engine comprising inlet, gas generator, body of a duct and outlet, is known (cf. EP 0 244 515 A3, Int. CI. F 02 K 3/04, Date of publication: Nov. 11, 1987).
  • Said gas turbine engine has fan and booster, combustion chamber, nozzles, gearboxes, shaft and relates to a great number of engines of high bypass ratio. It is adopted as a prototype of the present invention.
  • This engine thrust force has unidirectional propulsion whereas an aircraft requires a system of forces which are simultaneously operated in three-dimensional space.
  • This invention has as its object to produce a gas turbine power unit of the preceeding ones which makes possible to greatly improve the operational characteristics of the engines of the current art, namely: - creation of additional forces of a thrust along with a jet thrust and adjusting of their values irrespective of operational mode of engines,
  • active driver-propulsor principle is put in the basis of the invention.
  • active driver-propulsor it is meant a device by means of which the total energy of the working medium is conversed into propulsion in the process of direct interaction of high energetic fluid working medium, posessing kinetic energy (speed and mass ), potential energy ( pressure and temperature ) and internal energy ( molecular interaction forces ), with thermogasdynamic airfoils disposed in ducts of the power unit.
  • the structure of the energy carrier-working medium can be various both on physical, and on chemical properties. It can be gases: an air, argon, oxygen and others, it can also be two-phase and multiphase mixtures of gases with vapours of fluids.
  • the application of hydrocarbon fuel oxidation is widespread in the current engines. If as a working medium air is used only at standard atmospheric parameters, it is accepted to name aerodynamic those forces, which are obtained as a result of interaction between thermogasdynamic airfoils and the working medium. Thus it is necessary to take into account, that in the field of aviation the aerodynamic processes proceed in open unlimited space and a wing only has energy ( kinetic ) and air is in balanced energy condition. When a wing produces air disturbance potential energy of air is transfered in the lift and the jet thrust.
  • the upwind surface (the lower one) of a wing moving with the high speed at an angle of attack , depresses air and pushes its mass downwards.
  • the second half of a wing energy is dispersed in a space as kinetic energy of the thrown off air.
  • airfoil shaped bodies such as aircraft wings, rudders, sails and gas turbine rotor blades and stator vanes have streamlined shape which at angle of attack induce forces.
  • Thermogasdynamic airfoils according to the invention should be regarded as a surface, creating lift, control and propulsion forces at its flowing about by compressed fluid working medium at the expense of conversion of said working medium energy into said forces, which are transmitted via the duct and the engine body to the aircraft.
  • the power unit of an flying vehicle represents at least one engine comprising nacelle, inlet, gas generator, supercharger, duct body and outlet, characterized in that in the cross- sections of the power unit duct at least one thermogasdynamic airfoil is disposed with its uninterrupted flowing about by the working medium at all modes of the power unit operation.
  • thermogasdynamic airfoil is made in the form of at least two segments with partial overlap by one segment of another, forming the slotted nozzles which are curvilinear ones and converging in own cross-sections and these nozzles are intended for acceleration of a fluid working medium flowing about the upwind (lower) surface to the downwind (upper) surface of said airfoils.
  • At least one local zone of the streamline deformation is created in which interaction of rigid surfaces of the airfoil with the fluid working medium implements in the form of: accelerations and/or decelerations, heating and/or cooling, compression and/or expansion of a molecular structure of the working medium.
  • Engines of the present power unit are formed as one or multicontoured devices. At least one said segment of aforesaid airfoil is arranged with the capability of the adjustment of its angle of attack in relation to the direction of the flow of the working medium by means of its shaft extended out of the duct.
  • thermogasdynamic airfoils are integrated in the airfoil cascade.
  • said airfoils is made bilaterally attached inside the duct body or, for example, in the rotatable enforced ring on the bearing support.
  • Said ring and bearing support are integral with a structure in which they are mounted. Self-lubricated bearings are used eliminating the need for an external lubrication system.
  • Said airfoil cascades are mounted in the inlet and/or outlet in the aforesaid enforced rotatable rings with their capability to rotate in relation to the fore-aft axis of the engine.
  • At least one airfoil cascade is made inclined and rigidly fixed after a fan in the duct of the engine.
  • the nacelle of the power unit has an enforced boom which is intended for the taking loads induced by said airfoils and transmitted via the bearings, the enforced rings and flange joints or any other similar device which may be used to secure the ends of the airfoils to the body of the duct, the inlet and the outlet and hence help transmit said loads.
  • Said loads from said enforced boom are directly transmitted via an engine-support beam and/or engine pylon mounting to an airframe of the flying vehicle.
  • the load transfer mechanism between said airfoils and the aircraft body is made so to be capable of withstanding loads experienced during the aircraft maneuvers, e.g. vehicle roll, pitch and yaw.
  • Said airfoiles may be formed by some segments, a number of which depends on size and configuration of the duct and conditional limits of said local zones of deformation of streamlines of the fluid working medium.
  • the multisegmented structure of said airfoils is capable to adjust angles of attack of some segments and hence form curvilinear narrowed downwards nozzles by use of which it is possible to create the local boost of the flow of the fluid working medium and flowing about the downwind of airfoils with simultaneous local deceleration of the flow at the upwind surface. As a result, one can insrease the active forces without changing the speed of the flow in the duct.
  • Kf ( ⁇ ) is a factor describing obtaining of active propulsion on rigid surface of thermogasdynamic airfoils depending on an angle of attack of said airfoils relating to the direction of the flow of the fluid working medium.
  • the analog of this factor can be a lift factor of a wing Cy in a function from an angle of attack of a wing to the flight direction of an aircraft, and size S - area of a rigid streamlined surface of a wing in the plan.
  • thermogasdynamic airfoils are built in, for example: in the air inlet, after the fan in the duct and in the exhaust nozzle, which locally deform streamlines of the fluid working medium.
  • the speeds of the fluid working medium (kinetic energy) on take-off operational mode of the power unit are known: in the inlet it is about of 190 m/sec, in the bypass contour it equals about 150 m/ sec, in the exhaust nozzle it equals 470 m/ sec.
  • A-319 has two engines, so the lift force of two burning engines, when the airplane is on the runway and ready for take-off run, is increasing up to
  • A-319 static take-off mass is about 140.000 kg, one can subtract 18260 kg and get A-319 mass 121740 kg.
  • this aircraft is provided with additional propulsion which can be considered as a useful force substantially improving transport characteristics of aircrafts. Particularly, as for A-319 its take-off run will be shorter.
  • the local deformations of streamlines of the fluid working medium with large value of energy in the duct of the engine can be created by rigid streamlined surfaces of said airfoils which arranged so that the forces created on them will be directed not only vertically upwards, but also to a lateral side (to the right or to the left), forwards - backwards.
  • Fig.1 shows the concept of the power unit of an aircraft executed, for example, on the basis of the bypass turbojet engine CFM 56-5.
  • Fig.2 shows the inlet with disposed in it three thermogasdynamic airfoils integrated by the enforced ring in the airfoil cascade.
  • Fig.3 represents cross-sectional cut of the airfoil.
  • the present power unit of an flying vehicle can have one and/or multicontoured scheme and comprise one or some engines.
  • the engine circumscribed here as an example, has at least one bypass gas turbine engine comprising inlet 1 , gas generator 2, body of the duct 3, outlet 4 and nacelle 5.
  • the engine has airfoil cascades 6,7 and 8 in which, for simplification of design and increase of manufacturability of the power unit, thermogasdynamic airfoils 9 are integrated.
  • Airfoils 9 of airfoil cascade 6,7, and 8, for creation of active non-balanced propulsion, directed, for example, upwards, are arranged at positive angle of attack in relation to horizontal plane and to direction of the flow of the fluid compressed working medium in the duct 22 of the power unit.
  • Airfoils 9 are arranged so that adjustment of their angles of attack in relation to the direction of the flow allows to adjust the active propulsion on its value and direction.
  • Airfoils 9 can be disposed in two mutually perpendicular vertical and horizontal planes (in the drawings is not shown) for the obtaining not only lift, but also thrust and control active propulsion. Variable angle of attack of these airfoils 9 is provided maneurveing and deceleration of an aircraft.
  • Thermogasdynamic airfoil 9 comprises, for instance, two segments 10 with partial overlap by one of another, forming the slotted nozzles 11, which are curvilinear and converging in own cross-sections and these nozzles are intended for acceleration of the fluid working medium flowing about the upwind (lower) surface 12 to the downwind (upper) surface 13 of the airfoil.
  • External surfaces of the airfoil 9 can be covered with any kind of materials with high adhesive properties and aerodynamic cleanness.
  • thermogasdynamic airfoils 9 are disposed and rigidly fixed with the positive angles of attack in relation to the direction of the flow of the fluid working medium.
  • Some segments or every of them can be formed adjustable relating to the angle of attack by means of a shaft 16 extended out of the duct.
  • Fixed segments 10 are integrated in one whole enforced structure by means of one or some support ribs 17.
  • Thermogasdynamic airfoils 9 are disposed in the form of airfoil cascades 6,7 and 8 in three sections in the lengthwise direction of the duct: in the inlet 1 , after the fan 18 and in the outlet 4.
  • the airfoil cascade 8 in the inlet comprises three thermogasdynamic airfoils 9, which are mounted in the enforced ring 19.
  • the enforced ring 19 is mounted on support bearings 20 as integral part with the inlet and is capable to rotate in relation to the fore-aft axis of the engine.
  • a turn of one whole structure consisting of the enforced ring 10, airfoil cascade 8 and thermogasdynamic airfoils 9 is changed their attitude in relation to horizon, hence direction of forces in relation to horizon is also changed. As a result, an aircraft flight is changed to the required direction.
  • thermogasdynamic airfoils 9 are fixed.
  • the airfoil cascade 7 is mounted consistng of two thermogasdynamic airfoils 9 fixed in the enforced ring (it is not shown) on the support bearings by the same manner like in the inlet. A turn of the whole ring structure is changed attitude of said airfoils 9 of cascade 7 in relation to horizon and hence control of forces in direction is provided.
  • Thermogasdynamic airfoils 9 can comprise, for example, seven streamlined segment. A number of such segments can be changed depending on a volume of a duct and conditional limits of local zones of deformation of streamlines of a flow of a working medium. It is expediently to arrange some segments adjustable for the changing of angles of attack 15 to the direction of a flow with the purpose of the control of direction and/or value of propulsion.
  • thermogasdynamic airfoils Fig.3
  • the mutisegmented structure of the thermogasdynamic airfoils Fig.3
  • the capability to regulate their angles of attack allow arranging of slotted curvilinear nozzles
  • Gas turbine power unit application according to the present invention in a ultiengine variant allows to create a system of adjustable on value and direction active propulsion, lift, thrust and control forces. This system can be applied for effective control of the space attitude of a flying vehicle, as it was described above, characterized in that
  • the active driver-propulsor represents the duct 22 in the form of the contou r with disposed in it supercharger having the fan 18, in the inlet 1 and/or in the outlet 4 and/or inside the duct body 3 after fan 18 the airfoil cascades 6, 7, 8 with thermogasdynamic airfoils 9 are disposed with flowing them about by the flow of the fluid working medium for the creation of additional active propulsion, non-balanced, lift, thrust
  • the present power unit is operated by the following way.
  • the gas generator 2 actuates a compressor (it is not shown) and the fan 18, unducing the flow of the fluid working medium through the inlet 1 , duct 22 and the outlet 4.
  • the flow passes the airfoils
  • thermogasdynamic airfoil 9 creates on its downwind (upper) surface 13 the zone of low pressure and on its upperwind (lower) surface 12 the zone of high pressure.
  • the pressure differential on every segment 10 induces a force attached to this segment and oriented perpendicularly to the direction of the flow towards its downwind (upper) surface
  • the present invention allows: to embody the device for creation propulsion additionally to the jet thrust and for adjusting its value irrespective of a mode of operation of flying vehicle ; to increase total efficiency of the power unit; to decrease its power-to-
  • Multiengine power unit allows to control by use of additional propulsion an aircraft in vehicle roll, pitch and course irrespective of speed and altitude of a flight.
  • the width of this ring in the length of the duct is 800 mm.
  • three airfoils 9 are disposed.
  • the length of the upper airfoil is 1280 mm, the middle one is 1800 mm, the lower one is 1300 mm.
  • Summary airfoils area is 1 ,88 m .
  • the calculation for the evaluation of lift of said airfoil cascade is produced on the formula:
  • Ff (n) is additional force in a function from frequency of rotation (operational mode) of the engine, (kg); Kf ( ⁇ -) is factor of propulsion (lift), in this case factor Kf c) is approximately equals to a factor Cy and is determined on wind tunnel testing at specific speeds of flow; is density of air at zero altitude equals 0,125 kg sec 2 /m y ; V is speed of flow the account of local accelerations, (m ⁇ sec); S is area of thermogasdynamic airfoils in the plan (m 2 ).
  • the industrial applicability of the present invention is represented as most actual in connection with a deadlock situation in the aviation science, aircraft production and in the field of flying vehicle operation.
  • the cost of even insignificant increase of transport effectiveness of a flying vehicle exceeds US$ 1,5 billions.
  • Application of the present invention does not require expenditure for R&D, reorganization of manufacturing of serial engines, new process of engineering and new materials. It is required to establish comparatively small workshop for the manufacturing of the airfoil cascades and their installation in the engines.
  • Their application to the current flying vehicles allows approximately 17% increase of a transport effectivenes.
  • As for using devices according to the invention for new types of aircrafts it allows 3 times increase of the transport effectiveness.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Bloc moteur, en particulier moteur à turbine à gaz, destiné à n'importe quel type de bloc moteur pour aéronef capable de créer des forces de propulsion, de levage et de commande pour le vol dudit aéronef. La présente invention repose sur le principe de l'organe moteur-propulseur actif qui est un dispositif à l'aide duquel l'énergie totale d'un milieu de travail est convertie en propulsion dans le processus d'interaction directe du milieu de travail hautement énergétique avec des ailerons à dynamique gazeuse thermique placés dans des parties de la canalisation d'entrée d'air d'un moteur. Le bloc moteur selon la présente invention représente un moteur dans la canalisation duquel des ailerons à dynamique gazeuse thermique sont placés à des angles d'attaques réglés. Le milieu de travail fluide s'écoulant autour des ailerons, ces derniers créent à l'intérieur de la canalisation une propulsion supplémentaire qui est directement transmise à l'avion via le corps de canalisation.
PCT/IB1998/000743 1998-05-15 1998-05-15 Bloc moteur pour aeronef WO1999060268A1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
PCT/IB1998/000743 WO1999060268A1 (fr) 1998-05-15 1998-05-15 Bloc moteur pour aeronef
AU70734/98A AU7073498A (en) 1998-05-15 1998-05-15 Power unit for flying vehicle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/IB1998/000743 WO1999060268A1 (fr) 1998-05-15 1998-05-15 Bloc moteur pour aeronef

Publications (1)

Publication Number Publication Date
WO1999060268A1 true WO1999060268A1 (fr) 1999-11-25

Family

ID=11004716

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/IB1998/000743 WO1999060268A1 (fr) 1998-05-15 1998-05-15 Bloc moteur pour aeronef

Country Status (2)

Country Link
AU (1) AU7073498A (fr)
WO (1) WO1999060268A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1690790A1 (fr) * 2005-02-11 2006-08-16 ROLLS-ROYCE plc Système de turbo-moteur
US7165744B2 (en) 2004-01-21 2007-01-23 Rolls-Royce Plc Turbine engine arrangements

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2165704A1 (fr) * 1971-10-27 1973-08-10 Piret Daniel
EP0244515A2 (fr) 1986-04-16 1987-11-11 The Boeing Company Moteur d'avion à soufflante avec carénage tournant
EP0519823A1 (fr) 1991-06-19 1992-12-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Structure de suspension arrière d'un turboréacteur
FR2695960A1 (fr) * 1992-09-23 1994-03-25 Snecma Moteur à cycle variable pour un avion à décollage vertical.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2165704A1 (fr) * 1971-10-27 1973-08-10 Piret Daniel
EP0244515A2 (fr) 1986-04-16 1987-11-11 The Boeing Company Moteur d'avion à soufflante avec carénage tournant
EP0519823A1 (fr) 1991-06-19 1992-12-23 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Structure de suspension arrière d'un turboréacteur
FR2695960A1 (fr) * 1992-09-23 1994-03-25 Snecma Moteur à cycle variable pour un avion à décollage vertical.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
"CFM 56 EXECUTIVE OVERVIEW MOSCOW AIR SHOW", SNECMA PUBLICATION, August 1997 (1997-08-01)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7165744B2 (en) 2004-01-21 2007-01-23 Rolls-Royce Plc Turbine engine arrangements
EP1690790A1 (fr) * 2005-02-11 2006-08-16 ROLLS-ROYCE plc Système de turbo-moteur

Also Published As

Publication number Publication date
AU7073498A (en) 1999-12-06

Similar Documents

Publication Publication Date Title
US20220041297A1 (en) Fluidic propulsive system and thrust and lift generator for aerial vehicles
US5039031A (en) Turbocraft
US5149012A (en) Turbocraft
WO1999060268A1 (fr) Bloc moteur pour aeronef
RU2457153C2 (ru) Единая технология эксплуатации и производства транспортных средств "максинио", безаэродромный электросамолет (варианты), несущее устройство, турбороторный двигатель (варианты), полиступенчатый компрессор, обечайка винтовентилятора, способ работы турбороторного двигателя и способ создания подъемной силы электросамолета
Kong Propulsion system Integration of turboprop aircraft for basic trainer
WO1999058852A1 (fr) Procede de generation de forces permettant le mouvement de vehicules et dispositif pour sa mise en oeuvre
KR102668106B1 (ko) 이젝터 및 에어포일 구조체
TAPE et al. Direct lift STOVL engine integration
CA1092371A (fr) Soucoupe volante avec turbine radiale
Tape et al. Vectoring exhaust systems for STOL tactical aircraft
CA1074134A (fr) Appareil volant en forme de disque, mu par une turbine a poussee radiale
Peterson Tailoring the Lift Fan V/STOL Concept to Mission Requirements
Winborn The Propulsive Wing Turbofan V/STOL
Miller Performance of a forward swept wing fighter utilizing thrust vectoring and reversing
WOSSER et al. A GEM FOR AMPHIBIOUS SUPPORT
ADAMSON et al. Engine/airframe matching considerations for subsonic V/STOL aircraft
Sippel et al. Advanced technology turbofan propulsion designed for spaceplane acceleration missions
Tsien Aerodynamics and Aircraft Design: A Report Prepared for the AAF Scientific Advisory Group
Robbins V/STOL Aircraft Gas Turbine Requirements
FAIRCHILD HILLER CORP PALO ALTO CA HILLER AIRCRAFT DIV HEAVY-LIFT TURBOJET ROTOR SYSTEM. VOLUME 3. DESIGN LAYOUT STUDIES
Tsien et al. Toward New Horizons. Volume 4. Aerodynamics and Aircraft Design
Loth et al. Thrust efficiency of powered lift systems
Thames Reaction Control Systems for V/STOL Aircraft
Ross et al. Application of thrust vectoring to future aircraft design

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AL AM AT AU AZ BA BB BG BR BY CA CH CN CU CZ DE DK EE ES FI GB GE GH GM GW HU ID IL IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MD MG MK MN MW MX NO NZ PL PT RO RU SD SE SG SI SK SL TJ TM TR TT UA UG US UZ VN YU ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): GH GM KE LS MW SD SZ UG ZW AM AZ BY KG KZ MD RU TJ TM AT BE CH CY DE DK ES FI FR GB GR IE IT LU MC NL PT SE BF BJ CF CG CI CM GA GN ML MR NE SN TD TG

DFPE Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed before 20040101)
121 Ep: the epo has been informed by wipo that ep was designated in this application
NENP Non-entry into the national phase

Ref country code: KR

REG Reference to national code

Ref country code: DE

Ref legal event code: 8642

NENP Non-entry into the national phase

Ref country code: CA

122 Ep: pct application non-entry in european phase