EP1534945A4 - Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules - Google Patents

Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Info

Publication number
EP1534945A4
EP1534945A4 EP03799749A EP03799749A EP1534945A4 EP 1534945 A4 EP1534945 A4 EP 1534945A4 EP 03799749 A EP03799749 A EP 03799749A EP 03799749 A EP03799749 A EP 03799749A EP 1534945 A4 EP1534945 A4 EP 1534945A4
Authority
EP
European Patent Office
Prior art keywords
aircraft
vehicles
turbojet engines
integrated bypass
bypass turbojet
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.)
Withdrawn
Application number
EP03799749A
Other languages
German (de)
English (en)
Other versions
EP1534945A2 (fr
Inventor
Marius A Paul
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
PAUL Marius A
Original Assignee
Individual
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 US10/292,892 external-priority patent/US6733436B2/en
Priority claimed from US10/337,032 external-priority patent/US20030192304A1/en
Priority claimed from US10/383,462 external-priority patent/US6966174B2/en
Application filed by Individual filed Critical Individual
Publication of EP1534945A2 publication Critical patent/EP1534945A2/fr
Publication of EP1534945A4 publication Critical patent/EP1534945A4/fr
Withdrawn legal-status Critical Current

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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0075—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors the motors being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
    • F02C3/073—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages the compressor and turbine stages being concentric
    • 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
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • 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
    • 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
    • F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • 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
    • F02K3/04—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—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 plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • Y02T50/40—Weight reduction
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP03799749A 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules Withdrawn EP1534945A4 (fr)

Applications Claiming Priority (13)

Application Number Priority Date Filing Date Title
US37261802P 2002-04-15 2002-04-15
US372618P 2002-04-15
US37473702P 2002-04-23 2002-04-23
US374737P 2002-04-23
US40546002P 2002-08-23 2002-08-23
US405460P 2002-08-23
US292892 2002-11-12
US10/292,892 US6733436B2 (en) 2002-07-09 2002-11-12 Detachable combination instrument for health-care and treatment
US337032 2003-01-06
US10/337,032 US20030192304A1 (en) 2002-04-15 2003-01-06 Integrated bypass turbojet engines for aircraft and other vehicles
US383462 2003-03-06
US10/383,462 US6966174B2 (en) 2002-04-15 2003-03-06 Integrated bypass turbojet engines for air craft and other vehicles
PCT/US2003/010855 WO2004092567A2 (fr) 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Publications (2)

Publication Number Publication Date
EP1534945A2 EP1534945A2 (fr) 2005-06-01
EP1534945A4 true EP1534945A4 (fr) 2006-08-30

Family

ID=33304243

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03799749A Withdrawn EP1534945A4 (fr) 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Country Status (4)

Country Link
EP (1) EP1534945A4 (fr)
AU (1) AU2003299459A1 (fr)
CA (1) CA2484580A1 (fr)
WO (1) WO2004092567A2 (fr)

Families Citing this family (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1841960B1 (fr) 2004-12-01 2011-05-25 United Technologies Corporation Ailettes de rotor de soufflante pour moteur a turbine en bout
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006060004A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Dispositif de combustion pour moteur de turbine
WO2006059975A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Foyer peripherique pour moteur a turbine de bout
WO2006059988A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine de bout modulaire
DE602004019709D1 (de) 2004-12-01 2009-04-09 United Technologies Corp Tip-turbinentriebwerk und entsprechendes betriebsverfahren
EP1834076B1 (fr) 2004-12-01 2011-04-06 United Technologies Corporation Groupe d'aubes de turbine d'un rotor de soufflante et procédé de montage d'un tel groupe
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
EP1828568B1 (fr) 2004-12-01 2011-03-23 United Technologies Corporation Ensemble rotor de soufflante-turbine pour moteur a turbine de bout
EP1831521B1 (fr) 2004-12-01 2008-08-20 United Technologies Corporation Ensemble aubes de guidage d'admission de soufflante variable, turbomachine dotee d'un tel ensemble et procede de commande correspondant
EP1828574B1 (fr) 2004-12-01 2010-11-03 United Technologies Corporation Ensemble de boite de vitesses a couplage proximal pour moteur de turbine a pression d'entree
EP1825116A2 (fr) 2004-12-01 2007-08-29 United Technologies Corporation Refroidissement par ejecteur de l'enveloppe exterieure d'un moteur a turbine de bout
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
WO2006059980A2 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Aspiration par diffuseur pour moteur a turbine d'extremite
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006059979A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Carter intégral, aube fixe, bâti et mélangeur d'un moteur à turbine en bout
WO2006059990A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Refroidissement regeneratif des aubes et pales de turbine pour moteur a turbine d'extremite
WO2006060013A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ensemble de joint de rotor de ventilateur de moteur de turbine a pression d’entree
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
WO2006059999A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Pluralite d'aubages directeurs d'entree commandes individuellement dans un reacteur a double flux et procede de commande correspondant
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
EP1819907A2 (fr) 2004-12-01 2007-08-22 United Technologies Corporation Pale de ventilateur comprenant une section de diffuseur integrale et une section de pale de turbine a aube destine a une moteur a turbine a aube
US8087885B2 (en) 2004-12-01 2012-01-03 United Technologies Corporation Stacked annular components for turbine engines
WO2006059981A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Joint hydraulique pour boite de vitesses de moteur a turbine d'extremite
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
EP1834067B1 (fr) 2004-12-01 2008-11-26 United Technologies Corporation Ensemble de pales de soufflante pour moteur a turbine de bout et procede de montage
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
EP1828545A2 (fr) 2004-12-01 2007-09-05 United Technologies Corporation Elements annulaires de rotor de turbine
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
EP1825111B1 (fr) 2004-12-01 2011-08-31 United Technologies Corporation Carter de compresseur à rotation inverse pour un moteur à turbine en bout
EP1825177B1 (fr) 2004-12-01 2012-01-25 United Technologies Corporation Purgeur gonflable destine a un moteur a turbine et methode de reglage d'air de purge
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
DE602004019710D1 (de) 2004-12-01 2009-04-09 United Technologies Corp Fernbetätigung für eine verstellbare stufe eines verdichters für einen turbinenmotor
EP1825117B1 (fr) 2004-12-01 2012-06-13 United Technologies Corporation Moteur à turbine équipé d'une soufflante et d'un compresseur entraînés par un engrenage différentiel
WO2006059989A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Structure de support de moteur a turbine de bout
EP1831519B1 (fr) 2004-12-01 2010-08-04 United Technologies Corporation Moteur à turbine en bout avec étages soufflante et turbine multiples
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006062497A1 (fr) 2004-12-04 2006-06-15 United Technologies Corporation Bâti moteur à turbine en bout de pale
US7201558B2 (en) * 2005-05-05 2007-04-10 United Technologies Corporation Seal arrangement for a fan-turbine rotor assembly
US20130019585A1 (en) * 2007-05-11 2013-01-24 Brian Merry Variable fan inlet guide vane for turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
CN107813947A (zh) * 2017-11-27 2018-03-20 大连理工大学 一种利用排气续航的混合动力无人飞行器
US10989408B2 (en) * 2018-09-13 2021-04-27 Raytheon Technologies Corporation Additive integral combustor expansion spring
CN111332477B (zh) * 2020-02-21 2022-09-20 中国电子科技集团公司第二十九研究所 一种逆升压涡轮旁路控制装置及方法
US11549463B2 (en) * 2021-02-22 2023-01-10 General Electric Company Compact low-pressure compressor
CN116677498B (zh) * 2023-08-03 2023-10-17 中国航发四川燃气涡轮研究院 基于氢能的新型高超声速组合发动机

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2404767A (en) * 1941-10-28 1946-07-23 Armstrong Siddeley Motors Ltd Jet propulsion plant
US2611241A (en) * 1946-03-19 1952-09-23 Packard Motor Car Co Power plant comprising a toroidal combustion chamber and an axial flow gas turbine with blade cooling passages therein forming a centrifugal air compressor
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines
US3112610A (en) * 1961-02-27 1963-12-03 Joseph J Jerger Constant pressure shrouded propeller
US3283509A (en) * 1963-02-21 1966-11-08 Messerschmitt Boelkow Blohm Lifting engine for vtol aircraft
US3606210A (en) * 1969-11-06 1971-09-20 Ralph E Busby Engine mounting for vtol aircraft and the like
FR2076450A5 (fr) * 1970-01-15 1971-10-15 Snecma
US3603082A (en) * 1970-02-18 1971-09-07 Curtiss Wright Corp Combustor for gas turbine having a compressor and turbine passages in a single rotor element
GB1361036A (en) * 1971-11-05 1974-07-24 Hansford R J Gas turbine ducted fan propulsion unit
US3899886A (en) * 1973-11-19 1975-08-19 Gen Motors Corp Gas turbine engine control
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
No further relevant documents disclosed *

Also Published As

Publication number Publication date
CA2484580A1 (fr) 2004-10-28
AU2003299459A1 (en) 2004-11-04
WO2004092567A2 (fr) 2004-10-28
EP1534945A2 (fr) 2005-06-01
WO2004092567A3 (fr) 2005-04-07

Similar Documents

Publication Publication Date Title
EP1534945A4 (fr) Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules
GB2405181B (en) Turbomachine with low noise emissions for aircraft
EP1472136A4 (fr) Conception d'aeronef et aile interne d'aeronef
GB0520487D0 (en) Low sulphur diesel fuel and aviation turbine fuel
AU2003243627A8 (en) Microturbine engine system
GB2422875B (en) Systems and methods for starting aircraft engines
AU2003225664A1 (en) Multi-spool by-pass turbofan engine
GB2402978B (en) A combination of an aircraft and a gas turbine engine
GB2407142B (en) An arrangement for bleeding the boundary layer from an aircraft engine
GB0218849D0 (en) Lubrication system for gas turbine engine
AU2003279905A1 (en) Integrated property database and search engine
DE60316513D1 (de) Fluggasturbinentriebwerk mit Kontrolleitschaufel für gegenläufige Niederdruckturbine
GB2411437B (en) Aircraft gas turbine engines
EP1818663A4 (fr) Procede et systeme d'adaptation performances de monteur transitoire
GB2407134B (en) Aircraft engine mounting assembly
GB2398798B (en) Methods and apparatus for manufacturing turbine engine components
GB0328671D0 (en) Aircraft engine mounting
AU6482100A (en) Drag reduction for gas turbine engine components
GB0419692D0 (en) Helicopter turbine engine protection system
GB0222198D0 (en) Aircraft engine exhaust shroud
DE50301210D1 (de) Turboprop-Flugzeugtriebwerk
GB0204411D0 (en) Air and fuel condition system for the combustion engine
AU2003242020A1 (en) Method for reducing the noise level of an aviation engine and system for carrying out said method
AU2003205606A8 (en) Aircraft gps instrumentation system and relative method
GB0203293D0 (en) Aero engine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20041104

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IT LI LU MC NL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL LT LV MK

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: PAUL, MARIUS A.

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PAUL, MARIUS A.

RIC1 Information provided on ipc code assigned before grant

Ipc: F02K 3/068 20060101ALI20060420BHEP

Ipc: F02C 1/00 20060101AFI20050413BHEP

A4 Supplementary search report drawn up and despatched

Effective date: 20060731

17Q First examination report despatched

Effective date: 20061020

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20070303