US3041829A - Improvements to jet deflecting devices, particularly for discharge nozzles of propulsion units - Google Patents

Improvements to jet deflecting devices, particularly for discharge nozzles of propulsion units Download PDF

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Publication number
US3041829A
US3041829A US816156A US81615659A US3041829A US 3041829 A US3041829 A US 3041829A US 816156 A US816156 A US 816156A US 81615659 A US81615659 A US 81615659A US 3041829 A US3041829 A US 3041829A
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US
United States
Prior art keywords
jet
blades
jack
axes
discharge nozzles
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
US816156A
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English (en)
Inventor
Gelin Paul
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.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
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Publication of US3041829A publication Critical patent/US3041829A/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
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds

Definitions

  • the present invention relates to an improvement in deflectors of this kind using streamlined blades adapted to pivot about their axes, the said improvement consisting in that each of the blades is divided into two half-blades which, by pivoting about axes perpendicular to the axis of the discharge nozzle, can be situated in a withdrawn position out of the jet during non-deflecting periods, each of the half-blades thus being capable of a double pivoting movement, one about axes perpendicular to that of the nozzle, the other about their own axis.
  • the introduction of the half-blades into the jet in order to bring them from the completely withdrawn position to the non-active waiting position within the jet, is effected without great effort, the blades remaining parallel to the direction of the jet during this operation.
  • FIG. 1 is an axial sectional view of a discharge nozzle provided with a device according to the invention, the upper half of this figure showing the device withdrawn outside the deflecting periods, whereas the lower half of this figure shows the device in position for the purpose of deflecting the jet.
  • FIG. 2 is an end view of the nozzle with the same division of the figure as above.
  • FIG. 3 is a view on a larger scale showing one of the ends of the blades in the pre-deflecting position.
  • FIG. 5 is a similar view showing the blades in the jetdeflecting position.
  • FIGS. 4 and 6 are respectively sectional views taken on IV-IV and VIVI of FIGS. 3 and 5.
  • FIG. 7 is a view from above, the blades being withdrawn.
  • FIG. 8 is a view from above, the blades being in a pre-deflecting or deflecting position.
  • FIG. 9 shows a constructional detail of the jack means controlling the movement of the blades.
  • FIG. 10 is a sectional view taken on line X-X of FIG. 3.
  • a jet deflecting device which comprises: a collar or sleeve 2 constituting an ejector for drawing in outside air and terminating in a flared rim 2a, a retractable obstacle constituted by four streamlined half-blades 4, 5, 6 and 7, and a grid of vanes 3.
  • each of the blades such as 4 is articulated to a strap 8 by means of a pin 9.
  • the introduction of the blades 4 and '5 into the jet is effected by operating the rack 10 entraining the toothed sector 11 on which is fixed a fork 12.
  • This fork 12, engaged in a recess 13 formed in the blades such as 4, moves the latter into the desired position.
  • the blade 4 comprises a cylindrical portion of revolution 4a.
  • the rack 10 is operated by a jack 14 of the screw and nut kind and therefore irreversible, which ensures locking of the blades in the desired position.
  • the jack 14 is of the nut and screw type. By rotating the gear wheel 20, the gear wheel-nut 21 drives in translational movement the rack 10 which operates the gear wheel 11 of the fork 12.
  • the jack 1? is also of the nut and screw type and is incorporated in the same casing as the jack 14.
  • the gear wheel-nut 23 drives in rotational movement the screw 24 which, by means of a rocker arm 17 and rods 18 permits the rotation of the levers 15.
  • the device in the arrangement corresponding to the normal working state, the blades being in a position parallel to the axis of the nozzle and the grid of vanes in the withdrawn position (upper half of FIG. 1), the device is entirely out of the jet and thus causes neither drag nor loss of thrust.
  • the blades pivot about the pins 9 and penetrate into the jet. These blades are driven by the fork 12 whose movement is controlled by the jack 14 through the agency of the rack 10. Thus, the blades 4 progressively come into the pre-deflecting position, offering the jet the minimum resistance by their streamlined frontal surface.
  • the jack 19 causes the blades to pivot about the axes 0 by means of the elements 15, 16, 17, 18.
  • the blades in pivoting on themselves through an angle which may be as much as cease to present their streamlined frontal surface to the jet and gradually present their lateral surface, forming an obstacle to the flow of the jet.
  • the devices described hereinbefore permit the manipulation of the blades with only slight force since the blades are introduced into the jet by their streamlined face. This makes it possible to have a small jack installation and the entire installation can easily be arranged in an aircraft.
  • a device comprising a concealable set of guide vanes disposed externally of the nozzle and arranged, when exposed, to define successive, laterally directed passages for the jet, half-blades intended to deflect the jet.
  • said half-blades having flat surfaces and tapered edges and being rotatable about first axes of rotation normal to the axis of said nozzle outside said jet and about second axes of rotation coinciding with the geometrical axes of said half-blades, said second axes intersecting the nozzle axis normally thereto and also being normal to said respective first aXes, first operating means for moving said half-blades about said first axes of rotation from a withdrawn position outside the jet into a non-active position within the jet for which said half-blades offer their tapered edges to the jet, and second operating means for moving said half-blades on themselves about said second axes of rotation so that said half-blades gradually present their flat surfaces perpendicularly to the jet and deflect said jet into said passages of said set of guide vanes.
  • the second operating means comprise a jack, and levers fast with said half hlades and actuated by said jack through a rocker arm.
  • a device according to claim 1 wherein the first and second operating means comprise jacks of the nut and screw kind effecting irreversible drive and therefore locking of the half-blades in the desired position.
  • a device comprising a concealable set of guide vanes disposed externally of the nozzle and arranged, when exposed, to define successive, laterally directed passages for the jet, half-blades having cylindrical end portions and intended to deflect the jet from the axis'of said nozzle into said passages, said half-blades having fiat surfaces and tapered edges and being rotatable about first axes of rotation norm-a1 to the axis of said nozzle outside said jet and about second axes of rotation coinciding with the geometrical axes of said half-blades, a jack and a fork member operated by said jack, said fork member cooperating with said cylindrical end portions for moving said half-blades about said first axes'of rotation from a withdrawn position outside the jet into a non-active position within the jet for which said half-blades offer their tapered. edges to the jet, and operating means for moving said
  • a device wherein said operating means comprise a second jack, and levers fast with said half-blades and actuated by said second jack through a rocker-arm.
  • a device wherein said second jack as well as said jack operating said fork are of the nut and screw kind effecting irreversible drive and therefore locking of the half-blades in the desired position.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
US816156A 1958-06-05 1959-05-27 Improvements to jet deflecting devices, particularly for discharge nozzles of propulsion units Expired - Lifetime US3041829A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1198179T 1958-06-05

Publications (1)

Publication Number Publication Date
US3041829A true US3041829A (en) 1962-07-03

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US816156A Expired - Lifetime US3041829A (en) 1958-06-05 1959-05-27 Improvements to jet deflecting devices, particularly for discharge nozzles of propulsion units

Country Status (4)

Country Link
US (1) US3041829A (de)
DE (1) DE1095676B (de)
FR (1) FR1198179A (de)
GB (1) GB886198A (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10040563B1 (en) * 2013-04-11 2018-08-07 Geoffrey P. Pinto Dual panel actuator system for jet engines

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1206731B (de) * 1962-10-18 1965-12-09 Gen Electric Strahlrohr, insbesondere fuer Flugzeuge, mit seitlichen Austrittsoeffnungen und Umlenkschaufelgittern
DE1260320B (de) * 1963-12-30 1968-02-01 Gen Electric Strahlduese, insbesondere fuer den Flugzeugantrieb, mit schwenkbarem Kruemmersegment

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1818067A (en) * 1929-10-28 1931-08-11 Frederic F Kookogey Aeroplane
FR1092654A (fr) * 1952-11-25 1955-04-26 Rolls Royce Perfectionnements aux unités et installations de propulsion à réaction d'aérodynes
US2723091A (en) * 1951-02-01 1955-11-08 Roe A V & Co Ltd Air or dive brakes for aircraft
US2797547A (en) * 1954-11-29 1957-07-02 Snecma Jet deflecting device, especially intended for discharge nozzles or propulsion units
US2797548A (en) * 1952-02-16 1957-07-02 Snecma Thrust spoiler for propelling nozzles
GB778008A (en) * 1954-06-01 1957-07-03 United Aircraft Corp Improvements in or relating to a device for reversing the thrust in a jet propulsionengine
US2841954A (en) * 1954-12-23 1958-07-08 Armstrong Siddeley Motors Ltd Means for reversing the thrust of a jet engine
US2846164A (en) * 1955-11-22 1958-08-05 Snecma Vertical take-off and landing aircraft
US2850977A (en) * 1956-03-13 1958-09-09 Richard J Pollak Self energized stabilizing control

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1818067A (en) * 1929-10-28 1931-08-11 Frederic F Kookogey Aeroplane
US2723091A (en) * 1951-02-01 1955-11-08 Roe A V & Co Ltd Air or dive brakes for aircraft
US2797548A (en) * 1952-02-16 1957-07-02 Snecma Thrust spoiler for propelling nozzles
FR1092654A (fr) * 1952-11-25 1955-04-26 Rolls Royce Perfectionnements aux unités et installations de propulsion à réaction d'aérodynes
GB778008A (en) * 1954-06-01 1957-07-03 United Aircraft Corp Improvements in or relating to a device for reversing the thrust in a jet propulsionengine
US2797547A (en) * 1954-11-29 1957-07-02 Snecma Jet deflecting device, especially intended for discharge nozzles or propulsion units
US2841954A (en) * 1954-12-23 1958-07-08 Armstrong Siddeley Motors Ltd Means for reversing the thrust of a jet engine
US2846164A (en) * 1955-11-22 1958-08-05 Snecma Vertical take-off and landing aircraft
US2850977A (en) * 1956-03-13 1958-09-09 Richard J Pollak Self energized stabilizing control

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10040563B1 (en) * 2013-04-11 2018-08-07 Geoffrey P. Pinto Dual panel actuator system for jet engines

Also Published As

Publication number Publication date
FR1198179A (fr) 1959-12-04
GB886198A (en) 1962-01-03
DE1095676B (de) 1960-12-22
DE1095676C2 (de) 1961-06-29

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