GB851225A - Adjustable propulsion nozzles - Google Patents

Adjustable propulsion nozzles

Info

Publication number
GB851225A
GB851225A GB2267358A GB2267358A GB851225A GB 851225 A GB851225 A GB 851225A GB 2267358 A GB2267358 A GB 2267358A GB 2267358 A GB2267358 A GB 2267358A GB 851225 A GB851225 A GB 851225A
Authority
GB
United Kingdom
Prior art keywords
nozzle
petals
convergent
wall
divergent
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
GB2267358A
Inventor
John Wallace Hall
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.)
Bristol Siddeley Engines Ltd
Original Assignee
De Havilland Engine Co Ltd
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 De Havilland Engine Co Ltd filed Critical De Havilland Engine Co Ltd
Priority to GB2267358A priority Critical patent/GB851225A/en
Priority to DEH33817A priority patent/DE1121413B/en
Publication of GB851225A publication Critical patent/GB851225A/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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone

Abstract

851,225. Jet-propulsion nozzles. DE HAVILLAND ENGINE CO. Ltd. July 17, 1958 [July 17, 1957], No. 22673/58. Divided out of 851,224. Class 110 (3). A jet-propulsion nozzle comprising an upstream generally convergent tubular nozzle portion, a downstream generally divergent tubular nozzle portion which is incapable of axial movement relative to the upstream nozzle portion, a throat portion between the nozzle portions, a ring of petals for varying the cross-section of the throat portion and means for operating the petals, has a cooling air duct which surrounds the convergent nozzle portion and lies between the convergent portion and the nozzle-operating mechanism and which supplies a continuous flow of control gas into the downstream divergent portion from behind the petals. Jet-propulsion nozzle, Fig. 2, comprises a fixed convergent tubular nozzle portion 4, a series of circumferentially-spaced adjustable petals 6 and a fixed divergent rearwardly extending portion 5 leading to an exhaust orifice 8. The petals 6 are operated by mechanism 9 housed in the nacelle 10. When the petals are in the fully closed position shown in broken lines at 12, the nozzle acts as a wholly convergent nozzle. To avoid high drag losses in this position of the petals due to airflow over the engine casing 10 entering the region between the wall 5 of the fixed divergent nozzle and the propulsive jet, a controlled airflow 14 is fed from behind the petals to occupy the region. An annular control air duct 15 formed between a wall 16 forming the inner wall of a chamber 17 housing the operating mechanism 9 and the convergent wall 4 leads air from any suitable source, such as ram air from an auxiliary air intake or from the region between the aircraft and engine intakes to the region. The upstream end 18 of each petal co-operates with a sealing member 19 to ensure that the gas leaves on the rearward side of the petals. When the petals are in the fully divergent position they abut against a corrugated spacer strip 24 so that the control gas may be used to cool the petals and the wall of the nozzle. A further supply of cooling gas is supplied to the chamber 17 and is discharged through the nozzle 26. A heat shield 27 is provided to protect the wall 4. The duct 28 receives gas from the turbine exhaust. Heatresistant lagging 30 is also provided. In a modification, Fig. 3 (not shown), the petaloperating mechanism is of the type described in Specification 851,224.
GB2267358A 1957-07-17 1957-07-17 Adjustable propulsion nozzles Expired GB851225A (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
GB2267358A GB851225A (en) 1957-07-17 1957-07-17 Adjustable propulsion nozzles
DEH33817A DE1121413B (en) 1957-07-17 1958-07-16 Thrust nozzle for jet engines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB2267358A GB851225A (en) 1957-07-17 1957-07-17 Adjustable propulsion nozzles

Publications (1)

Publication Number Publication Date
GB851225A true GB851225A (en) 1960-10-12

Family

ID=10183253

Family Applications (1)

Application Number Title Priority Date Filing Date
GB2267358A Expired GB851225A (en) 1957-07-17 1957-07-17 Adjustable propulsion nozzles

Country Status (2)

Country Link
DE (1) DE1121413B (en)
GB (1) GB851225A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2367592A (en) * 1979-01-12 2002-04-10 Rolls Royce Variable area thrust nozzle
FR2835288A1 (en) * 2002-01-31 2003-08-01 Snecma Moteurs COOLING SYSTEM FOR A TURBOMACHINE POST-COMBUSTION NOZZLE
GB2588651A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
US11306680B2 (en) 2019-10-31 2022-04-19 Rolls-Royce Plc Exhaust nozzle
US11319896B2 (en) 2019-10-31 2022-05-03 Rolls-Royce Plc Exhaust nozzle

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5101624A (en) * 1989-09-07 1992-04-07 General Electric Company Exhaust nozzle hinge

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2778190A (en) * 1950-06-08 1957-01-22 Republic Aviat Corp Variable area nozzle for jet engines
US2770944A (en) * 1952-04-26 1956-11-20 United Aircraft Corp Variable area reaction nozzle movable from convergent to convergent-di-vergent form
NL194459A (en) * 1952-06-18
BE531848A (en) * 1953-09-17
US2746243A (en) * 1954-01-14 1956-05-22 Solar Aircraft Co Variable nozzle and sealing means therefor for jet engine
GB782494A (en) * 1954-03-26 1957-09-11 Rolls Royce Improvements in or relating to jet propulsion nozzle arrangements
BE537620A (en) * 1954-04-27
GB768014A (en) * 1955-03-07 1957-02-13 United Aircraft Corp Improvements in or relating to variable area propulsion nozzles

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2367592A (en) * 1979-01-12 2002-04-10 Rolls Royce Variable area thrust nozzle
GB2367592B (en) * 1979-01-12 2002-07-24 Rolls Royce Thrust nozzle for a gas turbine engine
FR2835288A1 (en) * 2002-01-31 2003-08-01 Snecma Moteurs COOLING SYSTEM FOR A TURBOMACHINE POST-COMBUSTION NOZZLE
US6792748B2 (en) 2002-01-31 2004-09-21 Snecma Moteurs Cooling system for a gas turbine engine post-combustion jet nozzle
GB2588651A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
US11306680B2 (en) 2019-10-31 2022-04-19 Rolls-Royce Plc Exhaust nozzle
US11319896B2 (en) 2019-10-31 2022-05-03 Rolls-Royce Plc Exhaust nozzle
US11473526B2 (en) 2019-10-31 2022-10-18 Rolls-Royce Plc Exhaust nozzle

Also Published As

Publication number Publication date
DE1121413B (en) 1962-01-04

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