GB1038854A - Nozzle assembly for a jet propulsion engine - Google Patents

Nozzle assembly for a jet propulsion engine

Info

Publication number
GB1038854A
GB1038854A GB13079/65A GB1307965A GB1038854A GB 1038854 A GB1038854 A GB 1038854A GB 13079/65 A GB13079/65 A GB 13079/65A GB 1307965 A GB1307965 A GB 1307965A GB 1038854 A GB1038854 A GB 1038854A
Authority
GB
United Kingdom
Prior art keywords
nozzle
shroud
convergent nozzle
jet
convergent
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
GB13079/65A
Inventor
Malcolm Roy Pike
Norman Arthur Kerridge
Thomas Herbert Frost
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 GB13079/65A priority Critical patent/GB1038854A/en
Priority to US531144A priority patent/US3386248A/en
Publication of GB1038854A publication Critical patent/GB1038854A/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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1246—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their downstream ends on a substantially axially movable structure
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • 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
    • F02K1/06—Varying effective area of jet pipe or nozzle
    • F02K1/12—Varying effective area of jet pipe or nozzle by means of pivoted flaps
    • F02K1/1207—Varying effective area of jet pipe or nozzle by means of pivoted flaps of one series of flaps hinged at their upstream ends on a fixed structure

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

1,038,854. Jet nozzles. ROLLS-ROYCE Ltd. March 26, 1965, No. 13079/65. Heading F1J. A nozzle assembly for a jet propulsion engine comprises a convergent nozzle which is mounted within a shroud having a fixed divergent nozzle at its downstream end, there being means for effecting relative axial movement between the shroud and the convergent nozzle so that the shroud may be placed both in an operative position in which it controls the expansion of jet gases leaving the convergent nozzle and in inoperative position in which it does not exercise such control. The invention is described with reference to a gas turbine by-pass type jet engine which comprises a jet pipe 14 having at its downstream end a convergent nozzle 15, the nozzle comprising a series of flap members 24 which are mounted at their upstream ends for pivotal movement about pivots 25 whereby the area of the convergent nozzle may be varied. Disposed around the nozzle 15 is a shroud member 21 which is axially movable by means of rams 22, Fig. 1, not shown, the shroud having at its downstream end a divergent nozzle portion 23. The shroud member 21 is movable axially between the operative position shown in Fig. 2 in which the divergent nozzle portion is effective to control the expansion of the jet gases leaving the convergent nozzle portion 15, and an inoperative position upstream of the position shown in Fig. 2. Each flap member 24 of the convergent nozzle portion has a curved portion 26 associated therewith and rollers 30 and 35 carried by the shroud member 21 by means of brackets 32 engage one above and one below the curved flange 26 so that as the shroud member 21 is moved axially downstream to the operative position shown in Fig. 2 the rollers act on the curved flanges 26 so as to pivot the flap members 24 of the convergent nozzle portion to their maximum area position. As the shroud member is moved axially upstream to the inoperative position the rollers act on the flap members 24 to move them to the minimum area position. The by-pass passage is indicated at 17 in Fig. 1. An outer casing 18 is disposed around the engine casing 16 to define therewith an annular passage 19 through which air may flow from the intake 10<SP>1</SP> to the annular space 20 around the convergent nozzle portion 15, the air then entering into the nozzle by ejector effect of the exhaust gases.
GB13079/65A 1965-03-26 1965-03-26 Nozzle assembly for a jet propulsion engine Expired GB1038854A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB13079/65A GB1038854A (en) 1965-03-26 1965-03-26 Nozzle assembly for a jet propulsion engine
US531144A US3386248A (en) 1965-03-26 1966-03-02 Nozzle assembly for a jet propulsion engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB13079/65A GB1038854A (en) 1965-03-26 1965-03-26 Nozzle assembly for a jet propulsion engine

Publications (1)

Publication Number Publication Date
GB1038854A true GB1038854A (en) 1966-08-10

Family

ID=10016432

Family Applications (1)

Application Number Title Priority Date Filing Date
GB13079/65A Expired GB1038854A (en) 1965-03-26 1965-03-26 Nozzle assembly for a jet propulsion engine

Country Status (2)

Country Link
US (1) US3386248A (en)
GB (1) GB1038854A (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3662957A (en) * 1970-10-28 1972-05-16 United Aircraft Corp Low friction track bearing assembly
US4141501A (en) * 1975-05-09 1979-02-27 Rolls-Royce (1971) Limited Nozzles for gas turbine engines
GB1533986A (en) * 1976-04-12 1978-11-29 Rolls Royce Nozzles for gas turbine engines
US4003201A (en) * 1975-07-31 1977-01-18 United Technologies Corporation Variable area flameholder duct
US4242865A (en) * 1978-01-25 1981-01-06 Curtiss-Wright Corporation Turbojet afterburner engine with two-position exhaust nozzle
GB2194597B (en) * 1986-08-29 1990-07-25 Rolls Royce Plc A variable area exhaust nozzle for a gas turbine engine
FR2789123B1 (en) * 1999-01-29 2001-04-27 Snecma ELASTIC RING-ORIENTED NOZZLE ACTIVATION SYSTEM FOR A REACTION PROPELLER

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2794317A (en) * 1951-11-08 1957-06-04 Westinghouse Electric Corp Jet propulsion nozzle apparatus
US3068645A (en) * 1955-07-11 1962-12-18 Gen Electric Aerodynamic nozzle
US2974480A (en) * 1957-12-04 1961-03-14 United Aircraft Corp Balanced exhaust nozzle
US3049873A (en) * 1958-02-04 1962-08-21 Westinghouse Electric Corp Exhaust nozzle having a flow area of variable convergency and divergency
US3044258A (en) * 1958-11-25 1962-07-17 Gen Electric Adjustable converging-diverging nozzle
US3153321A (en) * 1958-11-28 1964-10-20 Gen Motors Corp Thrust reversing mechanism
GB905534A (en) * 1960-07-27 1962-09-12 Rolls Royce Improvements in or relating to gas turbine engines
US3027710A (en) * 1960-10-10 1962-04-03 Stephen P Maytner Methods and apparatus for suppressing jet noise
US3157027A (en) * 1962-02-12 1964-11-17 Rolls Royce Propulsion nozzles

Also Published As

Publication number Publication date
US3386248A (en) 1968-06-04

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