US3643868A - Jet nozzle - Google Patents

Jet nozzle Download PDF

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Publication number
US3643868A
US3643868A US45526A US3643868DA US3643868A US 3643868 A US3643868 A US 3643868A US 45526 A US45526 A US 45526A US 3643868D A US3643868D A US 3643868DA US 3643868 A US3643868 A US 3643868A
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US
United States
Prior art keywords
flaps
shroud
walls
throat
jet nozzle
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 - Lifetime
Application number
US45526A
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English (en)
Inventor
David Roberts Mcmurtry
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.)
Rolls Royce PLC
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Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Application granted granted Critical
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    • 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
    • F02K1/1253—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 and of a substantially axially movable external member
    • 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

Definitions

  • ABSTRACT [30] Foreign Application Priority Data
  • the disclosure of this invention pertains to a jet nozzle for a gas turbine engine wherein the throat diameter of the nozzle is Sept. 6, 1969 Great Britain ..30,997/69 defined by the downstream and of an annular arrangement of flaps connected to a jet pipe and pivoted by a shroud surrounding the flaps being moved axially along the jet pipe.
  • E d 39 265 43 Between the shroud and each of the flaps there is provided a o are cam and roller device to convert the movement of the shroud into that of the flaps.
  • the shroud comprises walls extending at [56] Reierenoes cued a boat tail angle and in relatively close proximity to the flaps, UNITED STATES PATENTS from the position of maximum throat diameter to a larger diameter upstream thereof, each wall extending between two Dl'elfke X adjacent said cam and roller devices and each of these 3,024,599 3/1962 Keen ..239/265.37 devices is housed by a Snake connected to the adjacent walk 2,927,424 3/1960 y
  • the arrangement of the walls and the strakes ensures low-base 2,806,349 9/1957 Yeager ..239/265.39 X drag 1 2,926,489 3/1960 Halford et al..
  • the flow area or throat of the nozzle is varied by an annular arrangement of flaps whose downstream ends lie in an annulus defining said throat and which are pivoted at their upstream ends to a jet pipe, and in respect of each flap there is provided a mechanism connecting the flaps to a shroud surrounding the flaps such that if the shroud is moved axially the flaps are pivoted to vary the diameter of said throat.
  • a jet nozzle for a gas turbine engine wherein the minimum flow area or throat of the nozzle is varied by an annular arrangement of flaps whose downstream ends lie in an annulus defining said throat and which are pivoted at their upstream ends to a jet pipe, and wherein there is provided in respect of each flap a mechanism connecting the flaps to a shroud surrounding the flaps such that if the shroud is moved axially the flaps are pivoted to vary the diameter of said throat, characterized in that the shroud comprises a conical arrangement of walls extending at a boat tail angle from the position of maximum throat diameter to a larger diameter upstream thereof, each of the walls extending between two adjacent said mechanisms, and wherein there
  • Said walls may be adapted to be extensible in the downstream direction for the purpose of compensating at least partially for an increase in base drag when the shroud is moved to pivot the flaps radially inwards from the position of maximum throat area.
  • FIG. 1 is a side elevation of the nozzle.
  • FIG. 2 is a fragmentary plan view of FIG. 1.
  • FIG. 3 is an end view of FIG. 1.
  • FIG. 4 is a section on the line lVlV in FIG. 3.
  • FIG. 5 shows FIG. 4 in a different operational position.
  • FIG. 5a is a section on the line Va-Va in FIG. 4.
  • FIG. 6 is a section on the line VI-VI in FIG. 3 and embodies a modification.
  • FIG. 7 shows FIG. 6 in a different operational position.
  • a jet engine 10 has a jet pipe 11 terminating in a nozzle 12 situated downstream of a cowl or nacelle 13 enclosing the engine.
  • the nozzle includes an annular arrangement of flaps 14 whose downstream ends lie in an annulus defining the minimum flow area or throat, denoted 16, of the nozzle.
  • each flap is connected at its upstream end to the jet pipe by pivots 15.
  • FIGS. 4 and 5 show the maximum and minimum throat positions of the flaps denoted 14A and 14B respectively.
  • Each flap is adapted to be pivoted by a mechanism 20 operated by a shroud 21 surrounding the nozzle and supported 2 l l on the jet pipe for movement therealong under the action of fluid pressure motors 22.
  • each mechanism 20 comprises a cam 23 forming part of ⁇ the associated flap and a roller 24 supported by the shroud.
  • FIG. 4 shows the shroud in the extended or downstream position in which the flaps form the maximum throat diameter'while
  • FIG. 5 shows the shroud in the retracted or upstream position being the position corresponding to minimum throat diameter.
  • the shroud comprises an annularly continuous wall 30 surrounding the downstream end of the jet pipe with a clearance necessary, for example, to allow for'the presence of the flap pivots and of the connection between the shroud and the mo tors 22.
  • the shroud further comprises'an arrangement of walls 31 converging from the wall 30 and terminating at their downstream ends at a position close to the downstream ends of the flaps when the latter are in the position of maximum throat area. In this way it is possible to give the shroud an aerodynamically satisfactory boat tail angle a (FIG. 1) and substantially avoid the occurrence of base drag in the maximum throat diameter position of the flaps.
  • FIG. 5 position the walls 31 are virtually in line with the taper of the nacelle surface while in the FIG. 4 position the wall 30 defines the transition between the nacelle and the walls 31.
  • the walls 31 extend peripherally between the mechanisms 20, i.e., radially inwardly of the maximum radial extent thereof.
  • the strakes 32 projecting from between adjacent walls 31.
  • the strakes 32 are elongate in the direction of airflow.
  • the strakes are streamlined as particularly shown in FIG. 2 so as not to present any significant drag problem.
  • the walls 31 are connected at their downstream ends by an annular member 33 which provides the necessary hoop strength against the loads on the rollers 24.
  • the member 33 is polygonal, i.e., it is straight between successive rollers 24 so as to be stressed in tension only.
  • the walls 31 are correspondingly shaped to be flat at least towards their downstream ends.
  • the flaps 14 are shaped so as to form angles B fitting the shape of the walls 31. Gaps between adjacent flaps 14 are covered by auxiliary flaps 16 (FIGS. 1, 3).
  • Each plate 34 is connected to the jet pipe by a link 37 which controls the position of the plate so that when the shroud is in the FIG. 6 position the downstream ends of the wall 31 and the plate 34 coincide, but when the shroud is moved into the FIG. 7 position the plate does not participate in the upstream motion but is merely lowered from the position 34A into the position 34B.
  • the taper of the walls 31 is extended to a position relative to the flaps in which the base drag area of the nozzle is given by the dimension D as distinct from the larger dimension E which would apply if the walls 31 are not extended.
  • the plates 34 may be moved independently of the walls 31 by any appropriate mechanism and not necessarily by the links 37.
  • a jet nozzle for gas turbine engines wherein the minimum flow area or throat of the nozzle is varied by an annular arrangement of flaps whose downstream ends lie in an annulus defining said throat and which are pivoted at their upstream ends to a jet pipe, and wherein there is provided in respect of each flap a mechanism connecting the flaps to a shroud surrounding the flaps such that if the shroud is moved axially the flaps are pivoted to vary the diameter of said throat, characterized in that the shroud comprises a conical arrangement of walls extending at a boat tail angle from the position of maximum throat diameter to a larger diameter upstream thereof,
  • each of the walls extending between two adjacent said mechanisms, and wherein there is provided in respect of each mechanism an elongate housing connected between the adjacent walls and extending radially outwards therefrom to enclose the mechanism.
  • a jet nozzle according to claim 1 wherein the mechanism comprises a cam secured to the flap and a roller supported for rotation within the strake, the cam extending into the strake through a gap between the adjacent walls and cooperating to pivot the flap when the shroud is moved.
  • a jet nozzle according to claim 1 comprising in respect of

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Supercharger (AREA)
  • Exhaust Silencers (AREA)
US45526A 1969-06-19 1970-06-11 Jet nozzle Expired - Lifetime US3643868A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB30997/69A GB1278801A (en) 1969-06-19 1969-06-19 Jet nozzle for a gas turbine engine

Publications (1)

Publication Number Publication Date
US3643868A true US3643868A (en) 1972-02-22

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
US45526A Expired - Lifetime US3643868A (en) 1969-06-19 1970-06-11 Jet nozzle

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US (1) US3643868A (de)
DE (1) DE2029919C3 (de)
GB (1) GB1278801A (de)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785567A (en) * 1972-11-02 1974-01-15 Goodrich Co B F Movable wall for engine nozzle
US5476224A (en) * 1993-07-02 1995-12-19 Rolls-Royce Plc Variable area outlet of a gas turbine engine discharge nozzle
US20120199670A1 (en) * 2011-02-04 2012-08-09 Honeywell International Inc. Reduced drag afterburner nozzle actuation system
WO2014179114A3 (en) * 2013-04-29 2015-03-12 Dresser, Inc. Device for modifying flow parameters of working fluid exiting a compressor device
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

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1235755B (it) * 1975-03-12 1992-09-28 R0Lls R0Yce I97I Limited Perfezi0namenti in gruppi pr0puls0ri a turbina a gas
US4311276A (en) * 1978-06-24 1982-01-19 Rolls-Royce Limited Variable area nozzle for a gas turbine engine
GB2265668B (en) * 1981-02-28 1994-03-09 Rolls Royce Variable area nozzle for turbomachines

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2806349A (en) * 1952-12-24 1957-09-17 Solar Aircraft Co Sheet metal variable area nozzle
US2926489A (en) * 1954-05-18 1960-03-01 Havilland Engine Co Ltd Adjustable propulsion nozzles
US2927424A (en) * 1958-04-04 1960-03-08 Orenda Engines Ltd Variable area nozzle
US2970429A (en) * 1952-08-11 1961-02-07 Westinghouse Electric Corp Movable shroud for variable jet engine exhaust nozzles
US2976676A (en) * 1952-10-27 1961-03-28 Solar Aircraft Co Variable jet nozzle with coacting shroud
US3024599A (en) * 1958-07-14 1962-03-13 Rolls Royce Variable area jet propulsion nozzles
US3060681A (en) * 1958-03-13 1962-10-30 Rolls Royce Jet propulsion engine with adjustable nozzle
US3403858A (en) * 1967-03-31 1968-10-01 United Aircraft Corp Exhaust nozzle actuation system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2970429A (en) * 1952-08-11 1961-02-07 Westinghouse Electric Corp Movable shroud for variable jet engine exhaust nozzles
US2976676A (en) * 1952-10-27 1961-03-28 Solar Aircraft Co Variable jet nozzle with coacting shroud
US2806349A (en) * 1952-12-24 1957-09-17 Solar Aircraft Co Sheet metal variable area nozzle
US2926489A (en) * 1954-05-18 1960-03-01 Havilland Engine Co Ltd Adjustable propulsion nozzles
US3060681A (en) * 1958-03-13 1962-10-30 Rolls Royce Jet propulsion engine with adjustable nozzle
US2927424A (en) * 1958-04-04 1960-03-08 Orenda Engines Ltd Variable area nozzle
US3024599A (en) * 1958-07-14 1962-03-13 Rolls Royce Variable area jet propulsion nozzles
US3403858A (en) * 1967-03-31 1968-10-01 United Aircraft Corp Exhaust nozzle actuation system

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3785567A (en) * 1972-11-02 1974-01-15 Goodrich Co B F Movable wall for engine nozzle
US5476224A (en) * 1993-07-02 1995-12-19 Rolls-Royce Plc Variable area outlet of a gas turbine engine discharge nozzle
US20120199670A1 (en) * 2011-02-04 2012-08-09 Honeywell International Inc. Reduced drag afterburner nozzle actuation system
WO2014179114A3 (en) * 2013-04-29 2015-03-12 Dresser, Inc. Device for modifying flow parameters of working fluid exiting a compressor device
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
DE2029919C3 (de) 1974-01-17
GB1278801A (en) 1972-06-21
DE2029919A1 (de) 1971-01-07
DE2029919B2 (de) 1973-06-20

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