GB1083658A - Improvements in annular convergent-divergent exhaust nozzle - Google Patents

Improvements in annular convergent-divergent exhaust nozzle

Info

Publication number
GB1083658A
GB1083658A GB38140/65A GB3814065A GB1083658A GB 1083658 A GB1083658 A GB 1083658A GB 38140/65 A GB38140/65 A GB 38140/65A GB 3814065 A GB3814065 A GB 3814065A GB 1083658 A GB1083658 A GB 1083658A
Authority
GB
United Kingdom
Prior art keywords
nozzle
flap members
annular
convergent
downstream
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
GB38140/65A
Inventor
Dean Jordan Lennard
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Priority to GB38140/65A priority Critical patent/GB1083658A/en
Publication of GB1083658A publication Critical patent/GB1083658A/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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone
    • 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
    • F02K1/1261—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 substantially axially movable structure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/323—Arrangement of components according to their shape convergent
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • F05D2250/324—Arrangement of components according to their shape divergent
    • 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

Abstract

1,083,658. Jet propulsion nozzles. GENERAL ELECTRIC CO. Sept. 7, 1965, No. 38140/65. Heading F1J. The invention relates to an annular convergentdivergent exhaust nozzle for a jet propulsion engine which comprises a cylindrical shroud member which is movable axially between an upstream position in which it provides an annular convergent nozzle for subsonic operation, and a downstream position in which it provides an annular convergent-divergent nozzle for supersonic operation. The exhaust nozzle shown is for a gas turbine jet engine the turbine of which is indicated at 52 and the annular exhaust gas passage at 56. The nozzle assembly comprises a plug member 10 of double conical form having an upstream divergent surface 12 and a downstream convergent surface 14. The maximum diameter of the plug member may be varied by means of the flap members 17, 18 which are pivotally mounted at 19, 20, the flap members being movable by means of an actuator 30. The outer part of the nozzle comprises fixed generally cylindrical structure 42 which converges slightly at its downstream end 81, the structure being formed with an axially extending cam groove 85. Disposed around the structure 42 is an axially movable shroud member 64 which is movable between an upstream position as shown in Fig. 1, and a downstream position as shown in Fig. 2. To the downstream end of the shroud member 64 are pivotally mounted at 62 a series of flap members 60, the upstream ends of the flap members having pivotally connected thereto brackets 87 which are provided with rollers 86 which engage in the cam track 85 in the support structure 42. In the upstream position of the shroud member 64, Fig. 1, the flap members 60 are in an upstream position in which they provide an annular convergent nozzle for subsonic operation, the outer surfaces 74a of the flap members in this position forming together with the outer surface of the downstream end of the cylindrical support structure 42 a relatively small angle to the longitudinal axis of the nozzle. In the downstream position of the shroud member 64 shown in Fig. 2, the flap members 60 have pivoted about their pivotal mounting points 62 (due to the convergent shape at the downstream end of the cam track 85) so as to provide an annular convergent-divergent nozzle, the outer surfaces 74a of the flap members 60 in this position forming with the outer surface of the shroud 64 a cylindrical surface. The inner surface of the shroud member 64 is provided with cam tracks with which engage sliders secured to the support structure 42.
GB38140/65A 1965-09-07 1965-09-07 Improvements in annular convergent-divergent exhaust nozzle Expired GB1083658A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB38140/65A GB1083658A (en) 1965-09-07 1965-09-07 Improvements in annular convergent-divergent exhaust nozzle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB38140/65A GB1083658A (en) 1965-09-07 1965-09-07 Improvements in annular convergent-divergent exhaust nozzle

Publications (1)

Publication Number Publication Date
GB1083658A true GB1083658A (en) 1967-09-20

Family

ID=10401467

Family Applications (1)

Application Number Title Priority Date Filing Date
GB38140/65A Expired GB1083658A (en) 1965-09-07 1965-09-07 Improvements in annular convergent-divergent exhaust nozzle

Country Status (1)

Country Link
GB (1) GB1083658A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841091A (en) * 1973-05-21 1974-10-15 Gen Electric Multi-mission tandem propulsion system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3841091A (en) * 1973-05-21 1974-10-15 Gen Electric Multi-mission tandem propulsion system

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