GB1383651A - Jet propulsion nozzles - Google Patents

Jet propulsion nozzles

Info

Publication number
GB1383651A
GB1383651A GB4633871A GB4633871A GB1383651A GB 1383651 A GB1383651 A GB 1383651A GB 4633871 A GB4633871 A GB 4633871A GB 4633871 A GB4633871 A GB 4633871A GB 1383651 A GB1383651 A GB 1383651A
Authority
GB
United Kingdom
Prior art keywords
flaps
nozzle
flow
pass
outer surfaces
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
GB4633871A
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.)
UK Secretary of State for Defence
Original Assignee
UK Secretary of State for Defence
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 UK Secretary of State for Defence filed Critical UK Secretary of State for Defence
Priority to GB4633871A priority Critical patent/GB1383651A/en
Priority to DE19722248301 priority patent/DE2248301A1/en
Priority to JP10025572A priority patent/JPS4844615A/ja
Priority to FR7235301A priority patent/FR2156065B3/fr
Publication of GB1383651A publication Critical patent/GB1383651A/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
    • F02K1/1207—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
    • 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
    • F02K1/123—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, both having their 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)
  • Exhaust Silencers (AREA)

Abstract

1383651 Jet propulsion nozzles DEFENCE SECRETARY OF STATE FOR 27 Sept 1972 [5 Oct 1971] 46338/71 Heading F1J The invention relates to a jet propulsion nozzle of a gas turbine by-pass jet engine comprising a series of pivotally mounted flaps for varying the area of the nozzle outlet, there being discharge means arranged to direct a portion of the by-pass air-flow over outer surfaces of the flaps. The nozzle shown in Fig. 1 is the nozzle of a gas turbine by-pass type engine and comprises a duct I having a series of flaps 6 pivotally mounted at the downstream end thereof. The turbine exhaust flow is indicated at B and the by-pass flow at A. A cylindrical member 10 is disposed around the duct 1 to define an annular passage therewith through which a stream of air taken from the bypass flow A flows, being discharged at 12 over the outer surfaces of the pivotal flaps 6, thereby re-energizing the boundary layer so as to maintain flow attachment at the flap outer surfaces. In a second embodiment, the nozzle is of convergentdivergent form and comprises primary flaps 6 and by-pass air-flow means as in Fig. 1 and secondary flaps 16 pivotally mounted on a structure comprising walls 13, 14. Air flows into the nozzle through inlets 15 in the outer wall 3 as indicated by arrow D when the primary nozzle flaps 6 are moved to the reduced area position, the flaps 6 serving to close-off the openings 15 when in their outer positions. Air under pressure is discharged through a duct 17 to flow over the outer surfaces of the flaps 16 when the latter are in the reduced area position shown in chaindot lines.
GB4633871A 1971-10-05 1971-10-05 Jet propulsion nozzles Expired GB1383651A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
GB4633871A GB1383651A (en) 1971-10-05 1971-10-05 Jet propulsion nozzles
DE19722248301 DE2248301A1 (en) 1971-10-05 1972-10-02 THROTTLE JET
JP10025572A JPS4844615A (en) 1971-10-05 1972-10-05
FR7235301A FR2156065B3 (en) 1971-10-05 1972-10-05

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4633871A GB1383651A (en) 1971-10-05 1971-10-05 Jet propulsion nozzles

Publications (1)

Publication Number Publication Date
GB1383651A true GB1383651A (en) 1974-02-12

Family

ID=10440841

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4633871A Expired GB1383651A (en) 1971-10-05 1971-10-05 Jet propulsion nozzles

Country Status (4)

Country Link
JP (1) JPS4844615A (en)
DE (1) DE2248301A1 (en)
FR (1) FR2156065B3 (en)
GB (1) GB1383651A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2143280A (en) * 1983-06-24 1985-02-06 John Bernard Attkins Propulsion device
GB2236804A (en) * 1989-07-26 1991-04-17 Anthony Reginald Robins Compound nozzle
JPH06159137A (en) * 1992-08-03 1994-06-07 General Electric Co <Ge> Exhaust system lowering noise level, exhaust nozzle system, method of lowering noise level and noise suppressing chute assembly
WO2008045050A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2143280A (en) * 1983-06-24 1985-02-06 John Bernard Attkins Propulsion device
GB2236804A (en) * 1989-07-26 1991-04-17 Anthony Reginald Robins Compound nozzle
JPH06159137A (en) * 1992-08-03 1994-06-07 General Electric Co <Ge> Exhaust system lowering noise level, exhaust nozzle system, method of lowering noise level and noise suppressing chute assembly
WO2008045050A1 (en) 2006-10-12 2008-04-17 United Technologies Corporation Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle
US8365515B2 (en) 2006-10-12 2013-02-05 United Technologies Corporation Gas turbine engine with fan variable area nozzle, nacelle assembly and method of varying area of a fan nozzle

Also Published As

Publication number Publication date
FR2156065B3 (en) 1975-10-31
DE2248301A1 (en) 1973-04-12
FR2156065A1 (en) 1973-05-25
JPS4844615A (en) 1973-06-27

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee