GB1363174A – Variable convergent-divergent jet propulsion nozzle
– Google Patents
GB1363174A – Variable convergent-divergent jet propulsion nozzle
– Google Patents
Variable convergent-divergent jet propulsion nozzle
Info
Publication number
GB1363174A
GB1363174A
GB4380672A
GB4380672A
GB1363174A
GB 1363174 A
GB1363174 A
GB 1363174A
GB 4380672 A
GB4380672 A
GB 4380672A
GB 4380672 A
GB4380672 A
GB 4380672A
GB 1363174 A
GB1363174 A
GB 1363174A
Authority
GB
United Kingdom
Prior art keywords
flaps
divergent
convergent
nozzle
pivotally connected
Prior art date
1971-10-01
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
GB4380672A
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.)
Motors Liquidation Co
Original Assignee
Motors Liquidation 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.)
1971-10-01
Filing date
1972-09-21
Publication date
1974-08-14
1972-09-21
Application filed by Motors Liquidation Co
filed
Critical
Motors Liquidation Co
1974-08-14
Publication of GB1363174A
publication
Critical
patent/GB1363174A/en
Status
Expired
legal-status
Critical
Current
Links
Espacenet
Global Dossier
Discuss
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
F02K1/1292—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, the internal downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series and at their downstream ends on the downstream ends of the flaps of the external downstream series hinged at their upstream 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
F02K1/1223—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 upstream ends on the downstream ends of the flaps of the upstream series
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
1363174 Variable area jet propulsion nozzles GENERAL MOTORS CORP 21 Sept 1972 [1 Oct 1971] 43806/72 Heading F1J The invention relates to a variable convergentdivergent jet propulsion nozzle, the nozzle assembly comprising a set of convergent flaps 24 and a set of divergent flaps 32, the divergent flaps being pivotally connected to the convergent flaps at 31. The nozzle comprises a jet pipe 2 comprising an outer wall 3 and an inner wall 4, also a nozzle support ring 8. A ring member 15 is supported for axial movement by means of pairs of rollers 16 each pair of which engages within a channel section track 19 secured to the support ring 8. The ring member 15 is movable in a downstream direction (so as to move the flap members 24, 32 to the minimum area position shown in chain-dotted lines Fig.1) by means of actuators 22 which are pivotally mounted to fixed structure at 23. The convergent flap members 24 are pivotally connected at their upstream ends 26 to the ring member 15. The divergent flap members 32 are pivotally connected to the convergent members at the downstream ends of the latter at 31. Cam members 39 are pivotally connected to the divergent flap members at 38, each cam member being formed with pairs of cam grooves 42 which are engaged by rollers 43 carried by a member 44, each carrier member being secured to a rod member 46 which is pivotally mounted at its upstream end 48 to fixed structure. Thus as the convergent flaps together with the divergent flaps pivotally connected thereto at 31 are moved in a downstream direction by means of the actuators 22 acting on the ring member 15, the divergent flaps and so the downstream ends of the convergent flaps are caused to move inwardly to the position indicated by chain-lines in Fig. 1. The flap members move outwardly by the gaspressure within the nozzle when the actuators are retracted. The nozzle assembly comprises also a number of fairing flaps 50 each of which is secured to a box-section portion 35 of a divergent flap 32 by flanges 51. The forward end of each fairing flap 50 is received within the fixed annular fairing 12 being guided by means of rollers 52 engaging in tracks 54.
GB4380672A
1971-10-01
1972-09-21
Variable convergent-divergent jet propulsion nozzle
Expired
GB1363174A
(en)
Applications Claiming Priority (1)
Application Number
Priority Date
Filing Date
Title
US18552571A
1971-10-01
1971-10-01
Publications (1)
Publication Number
Publication Date
GB1363174A
true
GB1363174A
(en)
1974-08-14
Family
ID=22681340
Family Applications (1)
Application Number
Title
Priority Date
Filing Date
GB4380672A
Expired
GB1363174A
(en)
1971-10-01
1972-09-21
Variable convergent-divergent jet propulsion nozzle
Country Status (3)
Country
Link
US
(1)
US3712547A
(en)
CA
(1)
CA955410A
(en)
GB
(1)
GB1363174A
(en)
Cited By (1)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2456386A
(en)
*
1985-04-17
2009-07-22
Snecma
Nozzle assembly for a turbo-jet engine
Families Citing this family (5)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US4176792A
(en)
*
1977-07-11
1979-12-04
General Electric Company
Variable area exhaust nozzle
US4892254A
(en)
*
1988-03-09
1990-01-09
United Technologies Corporation
Aircraft engine interface fairing support
US6347510B1
(en)
*
1998-12-18
2002-02-19
United Technologies Corporation
Axi-nozzle ejector seal
US6415599B1
(en)
*
2001-05-11
2002-07-09
General Electric Company
Engine interface for axisymmetric vectoring nozzle
US7770399B2
(en)
*
2006-09-29
2010-08-10
United Technologies Corporation
Gas turbine engine nozzle liner with thermally compliant attachment brackets
Family Cites Families (3)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
US3048973A
(en)
*
1959-10-29
1962-08-14
Marcus C Benedict
Exhaust nozzle
US3367579A
(en)
*
1965-12-08
1968-02-06
Air Force Usa
Supersonic convergent-divergent jet exhaust nozzle
US3454227A
(en)
*
1966-08-19
1969-07-08
United Aircraft Corp
Free floating articulate ejector nozzle
1971
1971-10-01
US
US00185525A
patent/US3712547A/en
not_active
Expired – Lifetime
1972
1972-08-16
CA
CA149,536A
patent/CA955410A/en
not_active
Expired
1972-09-21
GB
GB4380672A
patent/GB1363174A/en
not_active
Expired
Cited By (2)
* Cited by examiner, † Cited by third party
Publication number
Priority date
Publication date
Assignee
Title
GB2456386A
(en)
*
1985-04-17
2009-07-22
Snecma
Nozzle assembly for a turbo-jet engine
GB2456386B
(en)
*
1985-04-17
2010-01-13
Snecma
Jet Nozzle
Also Published As
Publication number
Publication date
US3712547A
(en)
1973-01-23
CA955410A
(en)
1974-10-01
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Legal Events
Date
Code
Title
Description
1974-12-27
PS
Patent sealed [section 19, patents act 1949]
1979-04-25
PCNP
Patent ceased through non-payment of renewal fee
