GB1111195A - Improvements in convergent-divergent plug nozzle - Google Patents

Improvements in convergent-divergent plug nozzle

Info

Publication number
GB1111195A
GB1111195A GB3182766A GB3182766A GB1111195A GB 1111195 A GB1111195 A GB 1111195A GB 3182766 A GB3182766 A GB 3182766A GB 3182766 A GB3182766 A GB 3182766A GB 1111195 A GB1111195 A GB 1111195A
Authority
GB
United Kingdom
Prior art keywords
flap members
nozzle
annular
divergent
series
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
GB3182766A
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
Publication of GB1111195A publication Critical patent/GB1111195A/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
    • F02K1/1269—Varying effective area of jet pipe or nozzle by means of pivoted flaps of three series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the internal downstream series having its flaps hinged at their downstream ends on the downstream ends of the flaps of the external downstream series hinged on a fixed structure at their upstream ends
    • 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
    • F02K1/1207—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
    • 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

Landscapes

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

Abstract

1,111,195. Jet propulsion nozzles. GENERAL ELECTRIC CO. July 15, 1966 [Dec.8, 1965], No.31827/66. Heading F1J. The invention relates to an annular convergentdivergent nozzle for a jet engine comprising a duct within which is disposed a central plug so as to define a convergent-divergent gas flow duct. Flap means are pivotally mounted radially outwardly of the throat so as to form the divergent nozzle portion, the flap members being freely mounted so that they take up a position in dependence on the pressure difference thereacross. In a first embodiment as applied to a gas turbine jet engine comprising an exhaust gas flow duct 14 and an air flow duct 17, the nozzle comprises a central plug member 20 having a double conical surface 36. A series of adjustable flap members 22 are mounted at the downstream end of the jet pipe and define with the plug member an annular convergent duct and an annular throat 28, the flap members 22 being movable by means of an actuator 26. The annular divergent portion is provided by a series of flap members 32 which are pivotally mounted at their downstream ends 34 to a further series of flap members 30 which are pivotally mounted at their upstream ends 31 to the outer wall 18 of the air flow duct 17. The flap members 32 and 30 are freely mounted although the flaps 32 are connected by links 44 to the flaps 22 so as to maintain an annular air flow passage 42 therebetween. The flap members 30, 32 are thus free to take up positions dependent on the pressures prevailing within the nozzle and externally thereof, Fig. 2 being the position taken up during non-reheat or subsonic operation while Fig. 3 is that taken up during reheat, supersonic operation. In Fig. 4 the central plug member may be adjusted so as to vary the diameter thereof, as indicated at 50. The outer wall 48 comprises a frusto-conical portion 54 which together with the plug member defines the nozzle throat. At the downstream end of the frusto-conical portion 54 a series of flap members 56 are freely mounted at 58 and take up position dependent on the pressure difference thereacross.
GB3182766A 1965-12-08 1966-07-15 Improvements in convergent-divergent plug nozzle Expired GB1111195A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US51241665A 1965-12-08 1965-12-08

Publications (1)

Publication Number Publication Date
GB1111195A true GB1111195A (en) 1968-04-24

Family

ID=24038988

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3182766A Expired GB1111195A (en) 1965-12-08 1966-07-15 Improvements in convergent-divergent plug nozzle

Country Status (3)

Country Link
BE (1) BE685446A (en)
DE (1) DE1526818A1 (en)
GB (1) GB1111195A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2243878A (en) * 1990-04-14 1991-11-13 Mtu Muenchen Gmbh Thrust nozzle for a hypersonic engine
CN114776462A (en) * 2022-04-14 2022-07-22 中国航发沈阳发动机研究所 Throat-adjustable unilateral expansion spray pipe
CN114776465A (en) * 2022-05-25 2022-07-22 厦门大学 An adjustable plug nozzle based on rotary detonation engine
CN116085139A (en) * 2022-12-23 2023-05-09 中国航天空气动力技术研究院 Spray pipe suitable for hypersonic continuous Mach number change

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2243878A (en) * 1990-04-14 1991-11-13 Mtu Muenchen Gmbh Thrust nozzle for a hypersonic engine
GB2243878B (en) * 1990-04-14 1994-05-04 Mtu Muenchen Gmbh A thrust nozzle for a hypersonic engine
CN114776462A (en) * 2022-04-14 2022-07-22 中国航发沈阳发动机研究所 Throat-adjustable unilateral expansion spray pipe
CN114776465A (en) * 2022-05-25 2022-07-22 厦门大学 An adjustable plug nozzle based on rotary detonation engine
CN116085139A (en) * 2022-12-23 2023-05-09 中国航天空气动力技术研究院 Spray pipe suitable for hypersonic continuous Mach number change

Also Published As

Publication number Publication date
DE1526818A1 (en) 1970-03-19
BE685446A (en) 1967-01-16

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