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GB890755A - Gas turbine vertical lift engines for aircraft - Google Patents

Gas turbine vertical lift engines for aircraft

Info

Publication number
GB890755A
GB890755A GB2809859A GB2809859A GB890755A GB 890755 A GB890755 A GB 890755A GB 2809859 A GB2809859 A GB 2809859A GB 2809859 A GB2809859 A GB 2809859A GB 890755 A GB890755 A GB 890755A
Authority
GB
United Kingdom
Prior art keywords
nozzle
annular portion
engine
aircraft
gas turbine
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
GB2809859A
Inventor
Robert William Corbitt
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB2809859A priority Critical patent/GB890755A/en
Publication of GB890755A publication Critical patent/GB890755A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B64C29/0058—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 with vertical jet
    • 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
    • F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)

Abstract

890,755. Direct lift aircraft. ROLLS-ROYCE Ltd. Aug. 9, 1960 [Aug. 17, 1959], No. 28098/59. Class 4. [Also in Group XXVI] An aircraft is provided with a gas turbine vertical lift engine having an exhaust nozzle comprising an annular portion arranged to receive the turbine exhaust gases and a plurality of separate nozzle members which communicate with the annular portion and through which the exhaust gases are discharged. A gas turbine vertical lift engine 12 has an exhaust nozzle 14 formed with an annular portion 15 which is aligned with the main annular fluid duct 16 of the engine and arranged downstream of the turbine blades 19. Six nozzle members 20 with convergent-divergent portions 21 communicate with the annular portion 15. The flow path through the duct 16, annular portion 15 and nozzles 20 is straight and parallel to the longitudinal axis of the engine. At the centre of the nozzle, a hollow easing 22 is provided having a cylindrical upstream portion 23 and a frustoconical downstream portion 24. A gap 25 permits some of the exhaust gases to pass into the interior of the casing 22. These gases leave the casing through a hole 28 in a removable plate 27. The total nozzle area may be adjusted changing the plate 27 for another having a different sized hole 28.
GB2809859A 1959-08-17 1959-08-17 Gas turbine vertical lift engines for aircraft Expired GB890755A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB2809859A GB890755A (en) 1959-08-17 1959-08-17 Gas turbine vertical lift engines for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2809859A GB890755A (en) 1959-08-17 1959-08-17 Gas turbine vertical lift engines for aircraft

Publications (1)

Publication Number Publication Date
GB890755A true GB890755A (en) 1962-03-07

Family

ID=10270232

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2809859A Expired GB890755A (en) 1959-08-17 1959-08-17 Gas turbine vertical lift engines for aircraft

Country Status (1)

Country Link
GB (1) GB890755A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115853677A (en) * 2023-01-10 2023-03-28 航天科工火箭技术有限公司 Turbine exhaust gas exhaust structure of liquid rocket engine

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115853677A (en) * 2023-01-10 2023-03-28 航天科工火箭技术有限公司 Turbine exhaust gas exhaust structure of liquid rocket engine

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