US3098352A - Adjustable jet propulsion nozzle with secondary air flow control - Google Patents

Adjustable jet propulsion nozzle with secondary air flow control Download PDF

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Publication number
US3098352A
US3098352A US19421A US1942160A US3098352A US 3098352 A US3098352 A US 3098352A US 19421 A US19421 A US 19421A US 1942160 A US1942160 A US 1942160A US 3098352 A US3098352 A US 3098352A
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United States
Prior art keywords
nozzle
primary
duct
flow
section
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Expired - Lifetime
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US19421A
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English (en)
Inventor
Taub Alvin
Feldman Martin Mayer
Bell Clarence Edgar Le
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
Priority to NL262125D priority Critical patent/NL262125A/xx
Priority to US776387A priority patent/US3044258A/en
Application filed by General Electric Co filed Critical General Electric Co
Priority to US19421A priority patent/US3098352A/en
Priority to GB4336160A priority patent/GB896484A/en
Priority to FR848733A priority patent/FR1280852A/fr
Priority claimed from CH37161A external-priority patent/CH391385A/de
Priority to GB5246/61A priority patent/GB907526A/en
Priority to FR852618A priority patent/FR79220E/fr
Priority to CH381961A priority patent/CH412474A/de
Priority to BE602122A priority patent/BE602122R/fr
Application granted granted Critical
Publication of US3098352A publication Critical patent/US3098352A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F02K1/1261—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
    • 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
    • F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
    • 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

Definitions

  • This invention relates to adjustable fluid nozzles for jet propulsion engines, and more particularly to improved means for controlling secondary air flow in a nozzle having an ejector passage [for introducing secondary air into a stream of working fluid.
  • the invention has particular utility in a nozzle of the type described and claimed in application Serial Number 776,387 to W. W. Carlton et al., now Patent No. 3,044,258, issued July 17, 1962, and assigned to the assignee of this application, but its application is not limited thereto.
  • a nozzle of the type described in the application to Carlton will hereinafter be referred to as a Carlton nozzle for convenience.
  • the Carlton nozzle is an adjustable converging-diverging nozzle whose effective discharge orifice area is not only mechanically, but also aerodynamically, variable in accordance with the pressure of working fluid discharged through the nozzle by a jet propulsion engine.
  • a primary convergent-divergent nozzle section is formed of slidably-mounted flaps, such that the throat area and discharge orifice area are adjustable in a predetermined relationship to accommodate a wide range of engine working fluid temperatures and pressure ratios.
  • the critical pressure ratio is that at which fluid velocity in the nozzle throat becomes sonic. At super-critical nozzle pressure ratios, a divergent nozzle portion becomes necessary to realize the hull thrust available from expansion of the working fluid.
  • a fixed secondary nozzle section forming a divergent extension of the adjustable primary section in an expanded condition of the latter.
  • An ejector passage is formed between the sections, and is thus spaced along a divergent portion of the combination nozzle.
  • a supply of subsonic secondary fluid to the ejector passage causes the working fluid to separate from the nozzle at points, which may be spaced upstream from the secondary discharge orifice, at which equilibrium with atmospheric pressure is reached.
  • the effective discharge orifice area is aerodynamically varied to prevent overexpansion and provide the correct nozzle form for realization of maximum thrust, over a wide range of super-critical working fluid pressure ratios.
  • the supply of secondary fluid may conveniently be air bled from a compressor of the associated jet propulsion engine, or may comprise ram air that is reduced to subsonic velocity.
  • the rate of flow of secondary air into the secondary section of a Carlton-type nozzle is determined by the area of the ejector passage, as determined by the adjusted position or the primary section, and by the pressure ratio of the secondary air across the passage.
  • the pressure of the secondary air supply depends upon flight velocity, being dependent upon ram effect. However, the rate of flow theoretically required depends upon nozzle position, and the latter is controlled in accordance with working fluid temperature and pres sure, rather than flight velocity.
  • the design requirements of the primary nozzle torm result in a variation in ejector passage area which does not directly conform to the variation in secondary air flow rate which is theoretically required.
  • the rate of secondary air flow in a Carltontype nozzle has been found to exceed the requirement tor proper nozzle operation under certain conditions, especially at super-sonic flight speeds.
  • the energy loss required to ram ambient air is substantial at high flight speeds, and a material loss in thrust results from a relatively small increase in the quantity of air rammed. For example, an increase of 1% in the mass flow rate of rammed air may produce a decrease in thrust of about 3 /2%. Therefore, any excess of ram air flow induced by a Carlton-type nozzle results in an appreciable loss of thrust.
  • an adjustable fluid nozzle with means [for adjustably throttling secondary air supplied to an ejector passage thereof. Since reduction in the pressure of secondary air due to throttling eflect is proportional to the ram pressure, the effect of flight velocity on the pressure is reduced.
  • the adjustable fluid nozzle includes a primary section which is movable by actuating means, the actuating means including an actuating member connected to the primary nozzle section.
  • the throttling means is comprised of at least one throttling duct having varying cross section along its length and a movable throttle body mounted therein to vary the flow area, the throttle body being fixed to the actuating member for movement therewith. The rate of flow of secondary fluid is thus more nearly limited to that necessary for proper operation of the nozzle, and the loss in thrust associated with excess flow is substantially reduced.
  • FIG. 1 is an elevation in section of a fluid nozzle made in accordance with our invention, shown in a first or closed position;
  • FIG. 2 is a similar view, showing the nozzle in a second or open position.
  • a fluid nozzle made according to the aforementioned Carlton et al. application Serial No. 776,387 is shown to illustrate our invention, which is not, however, necessarily limited in application to a nozzle of this specific type.
  • the Carlton-type nozzle [generally comprises an adjustable primary nozzle section 1, and a fixed secondary nozzle section 2. These nozzle sections define fluid passageways receiving a flow of working fluid, designated by broken arrows, from a jet propulsion engine through a conventional exhaust collector 3 of cylindrical form.
  • the working fluid is passed to the exhaust nozzle by the exhaust collector for the conversion of pressure and temperature energy internally contained therein into a kinetic or velocity form in the exhaust nozzle, thereby generating a useful thrust reaction upon the exhaust nozzle.
  • the jet propulsion engine, exhaust nozzle, and exhaust collector are enclosed by an aircrafit skin 4, in order to minimize the resistance of the atmosphere to their pasage therethrough.
  • the aircraft skin may follow any ctorm suitable to specific aircraft applications.
  • a cylindrical duct 5 is circumferentially spaced about exhaust collector 3, and extends axially therefrom into overlapping engagement with skin 4, for the purpose of supporting the nozzle structure and conducting secondary fluid (air) thereto.
  • Secondary nozzle section 2 is formed as a sheet metal annulus diverging in a downstream direction, and is supported in a fixed position by duct 5.
  • the secondary section includes a throat portion 6, defining a variable area secondary fluid ejector passage 7 in cooperation with adjustable primary section 1.
  • the secondary section forms a fixed-area secondary discharge orifice 8, whose diameter is designated DS in FIG. 2.
  • the adjustable primary nozzle section 1 is comprised of a circumferentially disposed set of overlapping flaps 9, which are relatively slidable axially and circumferentially. Flaps 9 are of convergent-divergent form, and include a throat portion 10 and a primary discharge orifice 11, both of whose areas are varied by sliding motion of the flaps. The diameters of throat 10 and orifice 11 are designated TP and DP, respectively, in the closed position of FIG. 1, and TP and DP, respectively, in the open position of FIG. 2.
  • Flaps 9 are mounted for sliding motion along predetermined curved paths upon a plurality of curved track elements 12, each of which is supported in rolling engagement by a pair of rollers 13 and 14.
  • a track element may be provided for each flap 9, or for alternate flaps only, as described in the aforementioned Carlton et al. application.
  • Rollers 13 and 14 are rotatably mounted in carriage frames 15 and 16, respectively, whose positions and lengths combine with the form of track elements 12 to determine the relative areas of throat 1t and primary orifice 11 over the range of movement of the flaps.
  • Frames 15 and 16 are stationarily mounted in duct 5.
  • a theoretically optimum nozzle form would require independent adjustability of the throat area in accordance with working fluid temperature, and of the primary orifice area in accordance with the pressure ratio of the working fluid to the ambient atmosphere.
  • the predetermined program of relative values of these areas established by a Carlton nozzle provides a satisfactory approximation to optimum nozzle form.
  • An annular sliding seal 17 of conventional type is interposed between flaps 9 and exhaust collector 3 to seal the working fluid passage while permitting sliding movement of the flaps relative thereto.
  • Means for adjusting flaps Q to vary the configuration of the primary nozzle section comprising a plurality of fluid actuating motors 18 mounted circumferentially about duct 5.
  • Each of motors 18 controllably actuates a drive rod 19 for axial reciprocation, and may comprise any suitable type of hydraulic, mechanical, or electric motor well known in the art.
  • Each drive rod 19 is drivingly connected with one of track elements 12 by means of a pivotally-connected link 20.
  • a smaller number of motors than flaps may be provided, and driving connection may be established through a unison ring (not shown) circumferentially spaced about exhaust collector 3.
  • the rate of secondary air flow through the ejector passage 7 of the Carlton-type nozzle as thus far described is controlled by two factors: the area of the passage, as varied by movement of flaps 9, and the pressure ratio of the secondary air across the passage. Neither of these factors corresponds directly to the secondary air requirement of the nozzle, which is established by the position of the primary nozzle section relative to the secondary nozzle section.
  • the inherent form of flaps 9 does not permit control of the area of passage 7 in direct conformity to the varying flow requirements in the form of the primary nozzle section is adjusted.
  • the secondary air ram pressure is directly affected by flight velocity, which is not dependent upon nozzle position. We have found that the resulting secondary air flow in practice exceeds the nozzle requirements under certain conditions of flight speed and nozzle setting, resulting in loss of thrust caused by the excess ram effect.
  • Our invention is directed to the provision of means, in combination with an adjustable nozzle having an ejector passage, such as illustrated by the Carlton type nozzle, for controlling the secondary air flow in more direct conformity with nozzle requirements.
  • an adjustable nozzle having an ejector passage, such as illustrated by the Carlton type nozzle
  • our invention by providing a plurality of adjustable throttling means generally designated 21, each of which comprises a throttle body 22, and a throttling duct 23 arranged in serial flow relation with duct 5 for transmitting secondary air to ejector passage 7.
  • Duct 23 is generally frusto-conical as shown, and is mounted upon an end wall 24 of duct 5, in communication with an opening 25 therein.
  • Throttle body 22 is mounted upon drive rod 19 for reciprocating axial movement relative to passage 23, to provide a secondary air throttling area which is directly controlled by the nozzle setting.
  • both passage 23 and body 22 are frusto-conical in form, providing a throttling area variation which is linear with respect to nozzle movement.
  • any desired relationship between throttling area and nozzle position may be established by suitably forming passage 23, e.g. paraboloidally, hyper bolically, or according to any desired function.
  • the fully-closed position of primary nozzle section 1, shown in FIG. 1, is employed when the temperature of the working fluid is at a minimum, corresponding to a condition in which no afterburning is taking place, and the pressure ratio in the sub-critical range.
  • Optimum propulsive efficiency is achieved with a primary discharge orifice 11 which is only slightly larger than throat 10, so that the nozzle has a minimum divergency.
  • the working fluid expands substantially to atmospheric pressure in throat 10, developing maximum thrust with less than sonic flow velocity.
  • the primary discharge orifice 11 is located substantially in the plane of the secondary discharge orifice 8; overexpansion of the Working fluid in the base region down stream of orifice 8, and surrounding orifice 11 (known as base-drag"), is prevented by a maximum flow of secondary air through throttling means 21.
  • the flow area defined between throttle body 22 and duct 23 is therefore at a maximum in the position of FIG. 1, being determined experimentally for specific applications to provide a sufficient subsonic flow to permit transmission of atmospheric pressure into the base region, and thus prevent overexpansion of the working fluid.
  • the primary nozzle section is moved toward the fully open position of FIG. 2.
  • the secondary nozzle section cooperates with the divergent portion of the primary nozzle section to form an extended divergent nozzle section, along which is spaced the ejector passage 7.
  • the introduction of a subsonic flow of secondary air through passage 7 causes the Working fluid to separate from the diverging nozzle walls, and thus to discontinue the expansion process, at those points at which the pressure of the working fluid is in equilibrium with atmospheric pressure, with the result that overexpansion and resultant drag are prevented.
  • the effective discharge orifice area is thus aerodynamically varied between the adjusted area of primary orifice 11 and the fixed area of secondary orifice 8 as limits, converting the pressure of the working fluid most eflectively into useful thrust.
  • the Working fluid is shown in FIG. 2 to separate from the secondary nozzle section at points designated by diameter DE. While the theory of this separation phenomena is not fully understood, it is believed that the layer of subsonic velocity secondary air permits the transmission of atmospheric pressure upstream from orifice 8 forming an eddy 27 within nozzle section 2 and permitting the working fluid to separate as it reaches atmospheric pressure. Since the working fluid attains supersonic velocity after leaving throat 10', the upstream transmission of atmospheric pressure could not occur other than through a subsonic flow of secondary air surrounding the working fluid stream.
  • the rate of flow of secondary air through ejector passage 7, in the absence of our improved throttling means, would be determined by the cross-sectional area of passage 7, and by the pressure ratio of the secondary air entering and leaving this passage.
  • the area of the passage is determined in part by the form of the primary nozzle section 1, and consequently the air flow does not conform uniformly to the requirements for proper nozzle operation.
  • the ram pressure of the secondary air varies with flight speed, which bears no direct relationship to nozzle position.
  • throttling duct 23 is established to provide a correct flow restriction, in cooperation with throttle body 22, for all positions of the primary nozzle section intermediate those shown in FIGS. 1 and 2. In this manner, it is possible to insure a correct rate of secondary air fiow to establish separation of the Working fluid at an atmospheric equilibrium pressure over the entire range of movement of the primary nozzle section, while at the same time minimizing any excess secondary air flow induced by the ram effects of a varying flight speed.
  • a primary nozzle section receiving working fluid from said engine, means supporting said primary nozzle section and actuating means for moving said primary nozzle section to vary the form thereof and the area of discharge therefrom, said actuating means including an actuating member connected to said primary nozzle section, a secondary nozzle section circumferentially spaced about said primary nozzle section, said primary and secondary nozzle sections forming a circumferential ejector passage therebetween, duct means connected to said ejector passage to supply secondary fluid at subsonic velocity thereto, adjustable throttle means in said duct means upstream of said ejector passage for throttling the flow of secondary fluid, and means directing the entire flow of secondary fluid through said adjustable throttling means, said adjustable throttling means comprising at least one throttling duct having varying cross section along its length and a movable throttle body mounted therein to vary the flow area defined between said throttling duct and said throttle body in accordance with the position of said throttle body, said actuating means including an actuating member connected to
  • an exhaust nozzle for a reaction engine a set of circumferentially disposed flaps shaped to form a primary nozzle section receiving working fluid from said engine, said flaps formed successively, in the direction of working fluid flow therethrough, with a convergent portion, a throat portion, and a divergent portion, a secondary di vergent nozzle section circumferentially spaced about said primary nozzle section, means supporting said flaps and actuating means for moving said flaps along predetermined curved paths to a first position in which said working fluid is exhausted to atmosphere directly from said primary nozzle section and to a second position in which said working fluid is exhausted to atmosphere through said secondary nozzle section from said primary nozzle section, said actuating means including an actuating member connected to said flaps, said primary and secondary nozzle sections forming a circumferential ejector passage therebetween and said secondary nozzle section forming a divergent extension of said primary nozzle section in said second position of said flaps, duct means connected to said ejector passage to supply secondary fluid at subs

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)
US19421A 1958-11-25 1960-04-01 Adjustable jet propulsion nozzle with secondary air flow control Expired - Lifetime US3098352A (en)

Priority Applications (9)

Application Number Priority Date Filing Date Title
NL262125D NL262125A (zh) 1960-04-01
US776387A US3044258A (en) 1958-11-25 1958-11-25 Adjustable converging-diverging nozzle
US19421A US3098352A (en) 1960-04-01 1960-04-01 Adjustable jet propulsion nozzle with secondary air flow control
GB4336160A GB896484A (en) 1960-04-01 1960-12-16 Improvements in "adjustable converging-diverging jet propulsion nozzle"
FR848733A FR1280852A (fr) 1960-04-01 1961-01-04 Tuyère réglable convergente-divergente
GB5246/61A GB907526A (en) 1960-04-01 1961-02-13 Improvements in adjustable jet propulsion nozzle with secondary air flow control
FR852618A FR79220E (fr) 1960-04-01 1961-02-14 Tuyère réglable convergente-divergente
CH381961A CH412474A (de) 1960-04-01 1961-03-30 Einstellbare Schubdüse
BE602122A BE602122R (fr) 1960-04-01 1961-03-31 Tuyere convergente-divergente reglable

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US19421A US3098352A (en) 1960-04-01 1960-04-01 Adjustable jet propulsion nozzle with secondary air flow control
CH37161A CH391385A (de) 1961-01-12 1961-01-12 Einstellbare Schubdüse

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US3098352A true US3098352A (en) 1963-07-23

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US (1) US3098352A (zh)
CH (1) CH412474A (zh)
FR (1) FR1280852A (zh)
GB (1) GB907526A (zh)
NL (1) NL262125A (zh)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3186661A (en) * 1960-05-13 1965-06-01 Bristol Siddeley Engines Ltd Aircraft propulsion power plants
US3229457A (en) * 1962-10-15 1966-01-18 James R Rowe Variable area ratio rocket nozzle
US3258913A (en) * 1963-09-20 1966-07-05 Boeing Co Method and apparatus for varying the area of an air flow device
US3662957A (en) * 1970-10-28 1972-05-16 United Aircraft Corp Low friction track bearing assembly
US3897001A (en) * 1974-06-12 1975-07-29 Gen Electric Nozzle and auxiliary inlet arrangement for gas turbine engine
US4074523A (en) * 1976-12-08 1978-02-21 The United States Of America As Represented By The Secretary Of The Air Force Pressure actuated collapsible curtain liners for a gas turbine engine nozzle
US4587806A (en) * 1981-05-11 1986-05-13 United Technologies Corporation Area two-dimensional converging/diverging nozzle
US4778109A (en) * 1986-12-17 1988-10-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Adjustable two dimensional nozzle for aircraft jet engines
US5222692A (en) * 1990-12-05 1993-06-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing assembly between an aircraft fuselage and the outer nozzle flaps of a turbojet engine mounted in the rear end of the fuselage
US5351888A (en) * 1993-05-14 1994-10-04 General Electric Company Multi-axis vectorable exhaust nozzle
US5431344A (en) * 1993-11-12 1995-07-11 United Technologies Corporation Sliding throat gas turbine engine nozzle
US5494221A (en) * 1994-01-20 1996-02-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Variable geometry turbojet engine exhaust nozzle
EP1035316A1 (fr) * 1999-03-10 2000-09-13 Snecma Moteurs Tuyere d'éjection de turboréacteur axisymétrique et a orientation globale
US20110016880A1 (en) * 2009-07-27 2011-01-27 Roberts Steven D Retainer for suspended thermal protection elements in a gas turbine engine
AU2012222857B2 (en) * 2011-03-01 2016-02-25 Grollo Aerospace Engine for use in an aerial vehicle
US9581109B1 (en) * 2013-04-11 2017-02-28 Geoffrey P. Pinto Axially translating and radially tilting fan nozzle segments with combined actuation and position sensing
US10207812B2 (en) 2015-09-02 2019-02-19 Jetoptera, Inc. Fluidic propulsive system and thrust and lift generator for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
USD868627S1 (en) 2018-04-27 2019-12-03 Jetoptera, Inc. Flying car

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Publication number Priority date Publication date Assignee Title
DE1262682B (de) * 1963-08-22 1968-03-07 Rolls Royce Mantelstromgasturbinentriebwerk
GB1008322A (en) * 1964-08-04 1965-10-27 Rolls Royce Gas turbine engine
GB1068746A (en) * 1964-11-27 1967-05-10 Rolls Royce Jet propulsion engine
FR2637017B1 (fr) * 1988-09-28 1990-11-30 Snecma Structure de tuyere pour propulseur combine turbo-stato-fusee
GB2588652A (en) * 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588653A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle
GB2588651A (en) 2019-10-31 2021-05-05 Rolls Royce Plc An exhaust nozzle

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US2729937A (en) * 1951-03-20 1956-01-10 United Aircraft Corp Retractable flameholders for afterburners
US2770944A (en) * 1952-04-26 1956-11-20 United Aircraft Corp Variable area reaction nozzle movable from convergent to convergent-di-vergent form
FR1140440A (fr) * 1954-11-25 1957-07-22 Power Jets Res & Dev Ltd Perfectionnements apportés aux dispositifs de propulsion par réaction et à leurs tuyères de décharge
US2869321A (en) * 1953-02-05 1959-01-20 British Thomson Houston Co Ltd Fuel reaction chambers
US2910828A (en) * 1956-08-24 1959-11-03 United Aircraft Company Convergent-divergent variable area propulsion nozzle
US2974481A (en) * 1957-05-21 1961-03-14 English Electric Co Ltd Jet pipe ejector nozzles
US2984068A (en) * 1958-06-30 1961-05-16 Orenda Engines Ltd Propulsive nozzle system for reaction propulsion units
US3049873A (en) * 1958-02-04 1962-08-21 Westinghouse Electric Corp Exhaust nozzle having a flow area of variable convergency and divergency

Patent Citations (8)

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Publication number Priority date Publication date Assignee Title
US2729937A (en) * 1951-03-20 1956-01-10 United Aircraft Corp Retractable flameholders for afterburners
US2770944A (en) * 1952-04-26 1956-11-20 United Aircraft Corp Variable area reaction nozzle movable from convergent to convergent-di-vergent form
US2869321A (en) * 1953-02-05 1959-01-20 British Thomson Houston Co Ltd Fuel reaction chambers
FR1140440A (fr) * 1954-11-25 1957-07-22 Power Jets Res & Dev Ltd Perfectionnements apportés aux dispositifs de propulsion par réaction et à leurs tuyères de décharge
US2910828A (en) * 1956-08-24 1959-11-03 United Aircraft Company Convergent-divergent variable area propulsion nozzle
US2974481A (en) * 1957-05-21 1961-03-14 English Electric Co Ltd Jet pipe ejector nozzles
US3049873A (en) * 1958-02-04 1962-08-21 Westinghouse Electric Corp Exhaust nozzle having a flow area of variable convergency and divergency
US2984068A (en) * 1958-06-30 1961-05-16 Orenda Engines Ltd Propulsive nozzle system for reaction propulsion units

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3186661A (en) * 1960-05-13 1965-06-01 Bristol Siddeley Engines Ltd Aircraft propulsion power plants
US3229457A (en) * 1962-10-15 1966-01-18 James R Rowe Variable area ratio rocket nozzle
US3258913A (en) * 1963-09-20 1966-07-05 Boeing Co Method and apparatus for varying the area of an air flow device
US3662957A (en) * 1970-10-28 1972-05-16 United Aircraft Corp Low friction track bearing assembly
US3897001A (en) * 1974-06-12 1975-07-29 Gen Electric Nozzle and auxiliary inlet arrangement for gas turbine engine
US4074523A (en) * 1976-12-08 1978-02-21 The United States Of America As Represented By The Secretary Of The Air Force Pressure actuated collapsible curtain liners for a gas turbine engine nozzle
US4587806A (en) * 1981-05-11 1986-05-13 United Technologies Corporation Area two-dimensional converging/diverging nozzle
US4778109A (en) * 1986-12-17 1988-10-18 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) Adjustable two dimensional nozzle for aircraft jet engines
US5222692A (en) * 1990-12-05 1993-06-29 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Sealing assembly between an aircraft fuselage and the outer nozzle flaps of a turbojet engine mounted in the rear end of the fuselage
US5351888A (en) * 1993-05-14 1994-10-04 General Electric Company Multi-axis vectorable exhaust nozzle
US5431344A (en) * 1993-11-12 1995-07-11 United Technologies Corporation Sliding throat gas turbine engine nozzle
US5494221A (en) * 1994-01-20 1996-02-27 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Variable geometry turbojet engine exhaust nozzle
EP1035316A1 (fr) * 1999-03-10 2000-09-13 Snecma Moteurs Tuyere d'éjection de turboréacteur axisymétrique et a orientation globale
FR2790791A1 (fr) * 1999-03-10 2000-09-15 Snecma Tuyere d'ejection de turboreacteur axisymetrique et a orientation globale
US6276126B1 (en) 1999-03-10 2001-08-21 Societe Nationale D'etude Et De Construction De Moteurs D'aviation (S.N.E.C.M.A.) Axisymmetric, directable and adjustable turbojet-engine exhaust nozzle
US20110016880A1 (en) * 2009-07-27 2011-01-27 Roberts Steven D Retainer for suspended thermal protection elements in a gas turbine engine
US8572986B2 (en) 2009-07-27 2013-11-05 United Technologies Corporation Retainer for suspended thermal protection elements in a gas turbine engine
AU2012222857B2 (en) * 2011-03-01 2016-02-25 Grollo Aerospace Engine for use in an aerial vehicle
US9581109B1 (en) * 2013-04-11 2017-02-28 Geoffrey P. Pinto Axially translating and radially tilting fan nozzle segments with combined actuation and position sensing
US9803585B1 (en) * 2013-04-11 2017-10-31 Geoffrey P. Pinto Axially translating and radially tilting fan nozzle segments with combined actuation and position sensing
US10207812B2 (en) 2015-09-02 2019-02-19 Jetoptera, Inc. Fluidic propulsive system and thrust and lift generator for aerial vehicles
US10464668B2 (en) 2015-09-02 2019-11-05 Jetoptera, Inc. Configuration for vertical take-off and landing system for aerial vehicles
US10800538B2 (en) 2015-09-02 2020-10-13 Jetoptera, Inc. Ejector and airfoil configurations
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NL262125A (zh)
FR1280852A (fr) 1962-01-08
CH412474A (de) 1966-04-30
GB907526A (en) 1962-10-03

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