US2557435A - Regulating device for the outlet section of a reaction propeller tube or nozzle - Google Patents

Regulating device for the outlet section of a reaction propeller tube or nozzle Download PDF

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Publication number
US2557435A
US2557435A US643027A US64302746A US2557435A US 2557435 A US2557435 A US 2557435A US 643027 A US643027 A US 643027A US 64302746 A US64302746 A US 64302746A US 2557435 A US2557435 A US 2557435A
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US
United States
Prior art keywords
tube
nozzle
outlet section
regulating device
throttle
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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
US643027A
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English (en)
Inventor
Imbert Roger Jean
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Rateau SA
Original Assignee
Rateau SA
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Filing date
Publication date
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Publication of US2557435A publication Critical patent/US2557435A/en
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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
    • F02K1/08—Varying effective area of jet pipe or nozzle by axially moving or transversely deforming an internal member, e.g. the exhaust cone

Definitions

  • This invention relates to a regulating device for the outlet section of a reaction propeller tube or nomle.
  • the motive fluid may be air taking part in a thermal cycle, or it may comprise combustion gases.
  • the operating conditions provided for a reaction device permit of determining the maximum and minimum flow sections of the gases onleaving the of the orifice of the tube to be :-0.866.
  • the present invention permits of very substantially reducing these disadvantages; itconsist essentially in providing a throttle comprising one or more telescopic nozzles which can be displaced along the axis of the tube.
  • Figs. 1 and 2 illustrate in section a throttle for a nozzle of known type, Fig. 1 showing the position of the throttle for maximum opening and Fig. 2 the same throttle in the position of minimum opening.
  • Figs. 3 and 4 illustrate a throttle made according to the invention in the two positions corresponding respectively to Figs. 1 and 2.
  • the throttle in conformity with the invention comprises a different arrangement-am! is illustrated, in Fig. 3 in the position of maximum opening, and, in Fig. 4, in the position of minimum opening.
  • e is the external envelope of the tube, I the body of the throttle constituted by a nozzle or tube This nozzle is connected by profiled arms a to the control rod h slidably mounted in a guide i.
  • the frictional surface inside the tube, and more particularly in the region where the gases have the greatest velocities will be much more reduced and the output of the tube will be correspondingly increased.
  • the throttle may comprise several concentric nozzles in order to fractionate the throttling and thus reduce the longitudinal dimension of the device for regulating the outlet section of the tube.
  • Fig. 5 shows in two half sections, corresponding respectively to two diflerent operating positions a form of construction of this kind.
  • the throttle comprises two half section and the lower half section illusconcentric nozzles 11 and I: carried respectively by the control rods hi hr mounted one inside the other.
  • Thecontrolrodorrodsofthethrottleor throttles of thetelescopic device could be driven by any appropriate device, or servo-motor, in orderto provideagivenlawofopeningtothe reaction tube.
  • a tubular shell for conveying gas having a rear exit aperture and a rear, frusto-conical section with an inner surface that tapers rearwardly to said aperture
  • at least one axially movable, frusto-conical throttling ring in said shell having an outer surface which tapers throughout from its front end to its rear end at the same inclination as said inner surface of said shell rear section and has substantially the same diameter at its front end as has said inner surface of said shell rear section in the neighborhood of said exit aperture, so that the ring moved to maximum throttling position has the extreme forward portion of its outer surface fitting snugly against, and the remainder of its outer surface in prolongation of, said-inner'surface of said shell rear section, .means axially disposed in said shell, comprising an axially slidablc rod, for moving said ring, and an openwork rigid structure between said rod and said ring connecting the same to ther.
  • a tubular shell for conveying gas having a rear exit aperture and a rear, frusto-conical section with an inner surface that taper rearwardly to said aperture, at least one axially movable, frusto-conical throttling ring in said shell.
  • ring supportingmembers fast with said ring, arranged in spaced-apart radial planes with respect to'aaid ring, and an axially slidable member, fast with said ring supporting members to connect the same together, for controlling bodily axial movement? ofsaid ring.

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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)
  • Nozzles (AREA)
US643027A 1945-02-06 1946-01-24 Regulating device for the outlet section of a reaction propeller tube or nozzle Expired - Lifetime US2557435A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR994841T 1945-02-06

Publications (1)

Publication Number Publication Date
US2557435A true US2557435A (en) 1951-06-19

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ID=9556695

Family Applications (1)

Application Number Title Priority Date Filing Date
US643027A Expired - Lifetime US2557435A (en) 1945-02-06 1946-01-24 Regulating device for the outlet section of a reaction propeller tube or nozzle

Country Status (3)

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US (1) US2557435A (fr)
FR (1) FR994841A (fr)
GB (1) GB616349A (fr)

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2735264A (en) * 1956-02-21 jewett
US2793491A (en) * 1950-12-07 1957-05-28 Gen Motors Corp Variable area jet nozzle
US2880576A (en) * 1954-05-25 1959-04-07 Peter G Kappus Supersonic variable throat nozzle
US2928235A (en) * 1954-06-10 1960-03-15 Rolls Royce Jet propulsion nozzle for supersonic flight
US2931172A (en) * 1957-02-26 1960-04-05 United Aircraft Corp Thrust reversers
US2955414A (en) * 1957-09-03 1960-10-11 United Aircraft Corp Combined power plant
US2976681A (en) * 1957-09-17 1961-03-28 Boeing Co Clam shell thrust reversers with noise suppressors
US2976676A (en) * 1952-10-27 1961-03-28 Solar Aircraft Co Variable jet nozzle with coacting shroud
US3068642A (en) * 1959-11-17 1962-12-18 Forschungszentrum Der Luftfahr Drive means for land, water and aircraft
US3441218A (en) * 1966-11-07 1969-04-29 Paul Bucher Adjustable nozzle for jet propulsion engine
US4549847A (en) * 1982-11-04 1985-10-29 A.S. Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
US4573868A (en) * 1982-11-04 1986-03-04 A/S Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
US4678396A (en) * 1982-11-04 1987-07-07 A S Kongsberg Vapenfabrikk Movable spike, variable entrance geometry pipe diffuser with vibration suppression
DE3932791A1 (de) * 1989-09-30 1991-04-11 Mtu Muenchen Gmbh Gasturbinenstrahltriebwerk mit mindestens einem axial verfahrbar angeordneten schieber
US5398500A (en) * 1993-07-07 1995-03-21 Loral Vought Systems Corporation Convergent divergent jet engine nozzle
US20140175191A1 (en) * 2011-05-23 2014-06-26 Snecma System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine
US20160010590A1 (en) * 2014-07-09 2016-01-14 Rolls-Royce Plc Nozzle arrangement for a gas turbine engine
US20170306734A1 (en) * 2014-02-24 2017-10-26 Ge Oil & Gas Esp, Inc. Downhole wet gas compressor processor

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1007121B (de) * 1952-04-24 1957-04-25 Snecma Rueckstosstriebwerk
DE977738C (de) * 1957-12-11 1969-03-27 Josef Schaberger & Co G M B H Verfahren zum Betreiben eines Strahlantriebes, insbesondere fuer Raketen
DE1191178B (de) * 1959-06-11 1965-04-15 Bendix Corp Strahltriebwerk

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US658586A (en) * 1899-08-17 1900-09-25 Meinhard Reiling Fire-hose.
US2356557A (en) * 1939-12-19 1944-08-22 Anxionnaz Rene Reaction propelling device with supercharged engine
US2408099A (en) * 1943-04-07 1946-09-24 Sherman Albert Variable-area nozzle for jetpropelled aircraft

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US658586A (en) * 1899-08-17 1900-09-25 Meinhard Reiling Fire-hose.
US2356557A (en) * 1939-12-19 1944-08-22 Anxionnaz Rene Reaction propelling device with supercharged engine
US2408099A (en) * 1943-04-07 1946-09-24 Sherman Albert Variable-area nozzle for jetpropelled aircraft

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2735264A (en) * 1956-02-21 jewett
US2793491A (en) * 1950-12-07 1957-05-28 Gen Motors Corp Variable area jet nozzle
US2976676A (en) * 1952-10-27 1961-03-28 Solar Aircraft Co Variable jet nozzle with coacting shroud
US2880576A (en) * 1954-05-25 1959-04-07 Peter G Kappus Supersonic variable throat nozzle
US2928235A (en) * 1954-06-10 1960-03-15 Rolls Royce Jet propulsion nozzle for supersonic flight
US2931172A (en) * 1957-02-26 1960-04-05 United Aircraft Corp Thrust reversers
US2955414A (en) * 1957-09-03 1960-10-11 United Aircraft Corp Combined power plant
US2976681A (en) * 1957-09-17 1961-03-28 Boeing Co Clam shell thrust reversers with noise suppressors
US3068642A (en) * 1959-11-17 1962-12-18 Forschungszentrum Der Luftfahr Drive means for land, water and aircraft
US3441218A (en) * 1966-11-07 1969-04-29 Paul Bucher Adjustable nozzle for jet propulsion engine
US4549847A (en) * 1982-11-04 1985-10-29 A.S. Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
US4573868A (en) * 1982-11-04 1986-03-04 A/S Kongsberg Vapenfabrikk High area ratio, variable entrance geometry compressor diffuser
US4678396A (en) * 1982-11-04 1987-07-07 A S Kongsberg Vapenfabrikk Movable spike, variable entrance geometry pipe diffuser with vibration suppression
DE3932791A1 (de) * 1989-09-30 1991-04-11 Mtu Muenchen Gmbh Gasturbinenstrahltriebwerk mit mindestens einem axial verfahrbar angeordneten schieber
US5398500A (en) * 1993-07-07 1995-03-21 Loral Vought Systems Corporation Convergent divergent jet engine nozzle
US20140175191A1 (en) * 2011-05-23 2014-06-26 Snecma System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine
US9494110B2 (en) * 2011-05-23 2016-11-15 Snecma System for reducing the dynamic behavior of the movable segment of a deployable nozzle for a rocket engine
US20170306734A1 (en) * 2014-02-24 2017-10-26 Ge Oil & Gas Esp, Inc. Downhole wet gas compressor processor
US10753187B2 (en) * 2014-02-24 2020-08-25 Ge Oil & Gas Esp, Inc. Downhole wet gas compressor processor
US20160010590A1 (en) * 2014-07-09 2016-01-14 Rolls-Royce Plc Nozzle arrangement for a gas turbine engine
US10371094B2 (en) * 2014-07-09 2019-08-06 Rolls-Royce Plc Nozzle arrangement for a gas turbine engine

Also Published As

Publication number Publication date
FR994841A (fr) 1951-11-22
GB616349A (en) 1949-01-20

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