GB1166292A - By-Pass Turbojet Engine for STOL or VTOL Aircraft. - Google Patents

By-Pass Turbojet Engine for STOL or VTOL Aircraft.

Info

Publication number
GB1166292A
GB1166292A GB4901266A GB4901266A GB1166292A GB 1166292 A GB1166292 A GB 1166292A GB 4901266 A GB4901266 A GB 4901266A GB 4901266 A GB4901266 A GB 4901266A GB 1166292 A GB1166292 A GB 1166292A
Authority
GB
United Kingdom
Prior art keywords
nozzles
jet
gas
engine
pair
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.)
Expired
Application number
GB4901266A
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.)
MAN Turbo GmbH
Original Assignee
MAN Turbo GmbH
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 MAN Turbo GmbH filed Critical MAN Turbo GmbH
Publication of GB1166292A publication Critical patent/GB1166292A/en
Expired legal-status Critical Current

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/002—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector
    • F02K1/006—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto with means to modify the direction of thrust vector within one plane only
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

1,166,292. Propulsion Jet deflection. M.A.N. TURBO G.m.b.H. 1 Nov., 1966 [2 Dec., 1965], No. 49012/66. Heading B7G. A by-pass jet engine for a VTOL or STOL aircraft has two pairs of rotatable jet deflecting nozzles, 9, 12, one pair 9 being fed with low pressure fan air, the other pair with exhaust gas from a bifurcated jet pipe 10 characterized in that the nozzles pivot about axes normal to the flow at nozzle entry. The ducts 7, 10 feeding the nozzles have enlargements 8, 11 at their downstream ends containing vanes 14, which deflect the gas entering the nozzles when the nozzles are tilted for vertical thrust. The nozzles 9, 12 may carry burners 21 to further expand the gas passing through. Each nozzle 9, 12, may be mounted in a spherical or cylindrical part 15 which rotates within mountings 16, 17 containing gas seals. The nozzles 9, 12 rigidly mounted on shafts 26, 27 may be rotated by the movement of the piston in a pneumatic ram 23 mounted beneath the engine, through links 24, 24a, lever arms 25 and, where necessary, universal joints 28.
GB4901266A 1965-12-02 1966-11-01 By-Pass Turbojet Engine for STOL or VTOL Aircraft. Expired GB1166292A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DEM0067497 1965-12-02

Publications (1)

Publication Number Publication Date
GB1166292A true GB1166292A (en) 1969-10-08

Family

ID=7312223

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4901266A Expired GB1166292A (en) 1965-12-02 1966-11-01 By-Pass Turbojet Engine for STOL or VTOL Aircraft.

Country Status (1)

Country Link
GB (1) GB1166292A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3317378A1 (en) * 1983-05-13 1984-11-15 Wilhelm Fritz 4006 Erkrath Morschheuser FLOW CHANNEL SHORT LENGTH

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3317378A1 (en) * 1983-05-13 1984-11-15 Wilhelm Fritz 4006 Erkrath Morschheuser FLOW CHANNEL SHORT LENGTH
EP0126399A1 (en) * 1983-05-13 1984-11-28 Robertson GAL Gesellschaft für angewandte Lufttechnik mbH Fluid duct presenting a reduced construction

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees