US3739987A - Arrangement of jacks for controlling flaps and its application to the control of a jet pipe - Google Patents

Arrangement of jacks for controlling flaps and its application to the control of a jet pipe Download PDF

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Publication number
US3739987A
US3739987A US00216195A US3739987DA US3739987A US 3739987 A US3739987 A US 3739987A US 00216195 A US00216195 A US 00216195A US 3739987D A US3739987D A US 3739987DA US 3739987 A US3739987 A US 3739987A
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US
United States
Prior art keywords
flaps
control device
jacks
piston
cylinder
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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
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US00216195A
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English (en)
Inventor
G Servanty
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.)
RECH APPLIQUEES SERAP SOC ET
SOC D ETUDES RECHERCHES APPLIQUEES SERAP FR
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RECH APPLIQUEES SERAP SOC ET
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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
    • F02K1/1223—Varying effective area of jet pipe or nozzle by means of pivoted flaps of two series of flaps, the upstream series having its flaps hinged at their upstream ends on a fixed structure and the downstream series having its flaps hinged at their upstream ends on the downstream ends of the flaps of the upstream series
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15B—SYSTEMS ACTING BY MEANS OF FLUIDS IN GENERAL; FLUID-PRESSURE ACTUATORS, e.g. SERVOMOTORS; DETAILS OF FLUID-PRESSURE SYSTEMS, NOT OTHERWISE PROVIDED FOR
    • F15B15/00—Fluid-actuated devices for displacing a member from one position to another; Gearing associated therewith
    • F15B15/08—Characterised by the construction of the motor unit
    • F15B15/12—Characterised by the construction of the motor unit of the oscillating-vane or curved-cylinder type
    • F15B15/125—Characterised by the construction of the motor unit of the oscillating-vane or curved-cylinder type of the curved-cylinder type

Definitions

  • the piston has an external torus-shaped surface for co-operation with the wall of the cylinder whereby relative travel between the cylinder and the torus-shaped piston follows a curved line centered on the said external point.
  • This invention relates to a device for controlling flaps by means of jacks of toroidal shape with curved path of movement, and more particularly with movement along the arc of a circle.
  • Such jacks or servo mechanisms with circular movements are needed every time where parts or elements are to be actuated or controlled, the movement of which takes place along a limited angular vector about a hinge. These situations are met with frequently in the control of machine elements, and more particularly in the controls of aircraft and ships and in the operation of various elements, such as air brakes, the controls for opening and closing doors etc.
  • the conventional solution which consists in acting on a control lever by means of a jack or servo mechanism with conventional rectilinear movement, has the drawback of requiring at least two additional hinges over and above the main hinge of the controlled element. It presents difficult problems of bulk and necessitates frequently the use of intermediate connecting rods for the transmission of forces.
  • Servo motors with circular movements have, therefore, in many fields substantial advantages over conventional devices with rectilinear movements, but their generalization requires the possibility of providing an industrial construction suitable to give them a very precise geometrical shape combined with a surface which is compatible with the absolutely necessary degree of tightness.
  • the object of the present invention is to provide the tandem assembly of two torus-type jacks for controlling two hinged elements in sequence, wherein the curved trol device for controlling two hinged elements arranged one behind the other by means of a tandem assembly of fluid operated jacks, wherein each jack has a cylinder in the form of a torus with an axis in the arc of a circle centered on a point located outside of the said cylinder, a piston being mounted in the cylinder having an external torus-shaped surface for cooperation with the wall of the said cylinder, whereby relative travel between the cylinder and the torusshaped piston follows a curved line centered on said external point.
  • the bodies of the two jacks with toroidal bores are constructed together and are integrated in'a rigid structure pivoting about one of the hinges, and incorporating the corresponding hinged element.
  • the piston rod of the torusshapedjack centered on this hinge rests on a fixed part, whilst the piston rod of the other torus-shaped jack acts on the secondhinged element.
  • the two jacks in tandem may be arranged either near each other on the same side of the hinge of the said rigid structure, or they may be spaced apart on opposite sides of this hinge.
  • the present invention may be applied particularly advantageously to the control of a flow path of convergent-divergent profile, and more particularly to the control of an outlet jet pipe or of the collecting conduit of a jet propulsion unit, wherein such a jet pipe or the like is generally formed by a circular juxtaposition with partial covering of the upstream flaps, followed by a similar juxtaposition of the downstream flaps hinged to the former.
  • one of the two torus-shaped jacks mounted in tandem controls simultaneously two consecutive flaps belonging to the said upstream juxtaposition, and located on either side of the body of the jack, whilst the other jack controls simultaneously two consecutive flaps forming part of the downstream juxtaposition, and also located on-either side of the body of this other jack.
  • every jack acts on the two consecutive flaps it controls through the intervention of a double linkage leading to the respective flaps.
  • the bodies of the two toroidal bores of the two jacks are preferably integrated in the fixed structure of the said jet pipe or the like, and the piston rods are connected to the flaps by the said double linkage.
  • FIG. 1 is a partial longitudinal cross-section of an adjustable jet pipe equipped with a control device according to a first embodiment of the invention
  • FIG. 2 is a partial end elevation of the embodiment shown in FIG. 1 with the cover removed for clarity;
  • FIG. 3 is a cross-section similar to FIG. 1, but showing a second embodiment of a control device according to the invention
  • FIG. 4 is a partial plan view of a third, preferred, embodiment of the control device according to the invention.
  • FIGS. 5, 6 and 7 are respectively, cross-sections along the lines V-V, Vl-VI, and VII-V II in FIG. 4.
  • FIGS. 1 and 2 show the fixed end portion ofajet pipe 1 having a flange 2 to which is fixed a bracket 3 carrying a hinge pin 4 near the fixing point to the jet pipe 1.
  • the adjustable end part of the jet pipe comprises two flaps. On the one hand, an upstream flap 5 hinged at 4 to the fixed bracket 3, and on the other hand a downstream flap 6 hinged at 7 to the upstream flap 5. It can be seen that the latter defines an adjustable convergent portion between the hinges 4 and 7 located respectively with constant cross-section near the inlet zone of the convergent portion and with variable cross-section at its geometrical neck.
  • downstream flap 6 forms a potentially divergent extension of the convergent section, and is also adjustable, extending from the geometrical variable neck to an equally variable outlet section of the jet pipe.
  • the upstream flap 5 forms part of a strong box structure 8 having lightening holes 9 and two jack bodies in pairs or in tandem 10 and 11.
  • the assembly of the box structure 8 with its flap 5 and the jack bodies 10 and 11 can pivot together on the hinge 4 mounted on the bracket 3, which may be extended by a rear cover 12 formed to reduce the drag of the base of the reaction engine.
  • the bodies of the jacks 10 and 11 have bores in the shape of circular sectors of torii with their axes centered respectively on the hinge axes 4 and 7.
  • Pistons 13 and 14 are located in the bores of the bodies of the jacks l0 and 11 and are also in the form of circular sectors of torii and are integral with curved rods 15 and 16, fixed respectively to the bracket 3 and the downstream flap 6.
  • the jacks l0 and 11 are double-acting and the conduits for the hydraulic fluid for the jack 10 are shown diagrammatically at 17a and 17b.
  • the pistons 13 and 14 are preferably mounted floatingly on the rods 15 and 16 and, together with said rods are equipped with sealing joints permitting a certain play.
  • the control of the primary jack 10, whose rod 15 is connected to the bracket 3, has the effect of causing the body of the jack to slide relative to the piston 13, and consequently to pivot the box structure 8 and, therefore, the upstream flap 5 which is integral therewith, about the hinge 4, thereby modifying the convergence and the cross-section of the neck of the jet pipe.
  • the control of the secondary jack 11 has the effect of causing the piston 14 to slide and thereby to modify the angular setting of the downstream flap 6, which is acted upon by the rod 16, relative to the box structure 8 and, therefore to the upstream flap S.
  • the divergence of the latter (which may also be zero or even negative, in which case the configuration is convergent from end to end), as well as the outlet cross-section of the jet pipe, can be modified.
  • the transmission is reduced to its simplest term: any transmission by connecting rods or the like is avoided, as well as any articulated kinematic chain other than the pivot of each flap, with the exception of systems which may be mounted at the points of application of the jacks for taking up any possible changes due to thermal expansion.
  • FIG. 1 and the right-hand side in FIG. 2 show in solid lines an intermediate configuration of the jet pipe in which the upstream flap 5 is at its smallest convergence, the cross-section of the neck is, therefore, at its maximum, and the downstream flap 6 is at its highest maximum fixing.
  • the secondary jack 11 controls the secondary jack 11, so as to move its piston 14 to its upper base, in which case the downstream flap will be at maximum divergence and the outlet cross-section of the jet pipe will have the highest value.
  • a second intermediate position of the jet pipe is shown in FIG. 1 and on the left side of FIG.
  • the piston 13 is at the upper end of the primary piston 10, fixing thereby the upstream flap 5 at its maximum convergence and reducing correspondingly the cross-section of the neck at the point of the hinge 7, whilst the piston 14 at the upper end of the secondary jack 11 reduces the fixing of the downstream flap 6 which has, therefore, only a small convergence. This may be accentuated by moving the piston 14 to the inner end of the secondary jack 11, thereby imparting to the jet pipe a configuration of extreme closure with minimum outlet cross-section.
  • the primary jack 10 is on the side of the primary hinge 4 remote from the secondary jack 11, whilst the general kinematic arrangement remains the same.
  • the embodiment shown in FIG. 3 can be controlled in like manner to that described with reference to FIGS. 1 and 2.
  • the invention provides a viable light and efficient so lution to problems encountered in steam pipelines, in the pipelines of high-speed aerodynamic blowers, ejection pipes of jet engines, such as rockets and turboreactors, and to problems for collecting air for high-speed aerobic engines, such as ram jets.
  • the invention is also applicable to the control of twodimensional flows and to the control of flows having a revolutional symmetry.
  • the flaps to be controlled can have the shape of cone segments, so as to form by circular repetition and partial overlaps continuous truncated cones.
  • control jacks are attached only to certain, so-called guide flaps which are separated by flaps without jacks, or guided flaps which act as intermediate connecting flaps, wherein the synchronization between the guide flaps is effected by the intermediate connecting flaps, wherein the forces transmitted by these intermediate flaps may be regarded only as small and only adapted to compensate the differential outputs which are possible between the various jacks equipping the whole crown.
  • FIGS. 4 to 7 meets these conditions and ensures additionally that, in the case of a total failure of one jack the defective control is immediately taken up by the adjacent jacks.
  • the same reference numerals have been used to indicate equivalent elements.
  • the bodies of the jacks and 11 are not integral with the flaps 5 and 6, are spaced from the outer surface of said flaps, which surface has a temperature of the order of 700 C, and are fully exposed to the flow of cooling air which has a temperature of the order of 350 C.
  • the structure 8 in which the bodies of the jacks 10 and 11 are incorporated, is arranged on both sides of and symmetrically to two upstream flaps 5-5, and this arrangement is repeated around the whole crown of upstream flaps.
  • the structure 8 is here integral with the fixed end portion of the jet pipe 1, and the body of the jack 10 is located upstream of the end flange 2.
  • the body of the jack 11 is close to the end flange 2 so that the assembly of the fixed structure is compact and overhang is reduced.
  • the rod of the piston 13 moves in its toroidal bore in the jack 10 by turning around a hinge axis 18.
  • the mechanical connection between this piston rod 15 and the axis 18 is ensured by a pair of double angled arms 19-19 integral with the end of the rod 15.
  • the axis 18 does not coincide with the hinge axes 4 of the upstream flaps 5-5 located on either side.
  • Each of the latter is extended by two angled arms 20-20 connected to the end of the piston rod 15 by connecting rods 21-21 equipped with swivel joints at the ends.
  • Each jack l0 acts simultaneously on two upstream flaps 5-5 located on either side thereof, and this double control is repeated over the whole circumference of the jet pipe.
  • the application of each jack 10 carries along directly the movement of two flaps 5-5 to which it is connected, and that of all the flaps 5 forming the upstream crown by means of the collaboration of successive linkages.
  • each toroidal jack 11 whose piston rod 16 moves about an axis 22 near the axis 18.
  • a double angled arm 23-23, integral with the rod 16, is hinged about the axis 22.
  • the mechanical connection between the jack l1 and the flaps 6-6 controlled thereby comprises a double connecting rod 24-24 connecting the end of the piston rod 16 to a double reversing lever 25-25 pivotingabout a pivot 26 and a double connecting rod 27-27 connected between the reversing lever 25-25 and a hinge 28 on each of two downstream flaps 6-6 controlled by the jack ll, swivel joints being provided at the end of each connecting rod 27.
  • control device is capable of modification without departing from the spirit and scope of the invention as defined by the appended claims.
  • a control device for controlling two hinged elements arranged one behind the other by means of a tandem assembly of fluid-operated jacks in which control device each of said jacks comprises a cylinder having a wall in the form of a torus with. an axis in the arc of a circle centered on a point located outside of the said cylinder and a piston mounted in said cylinder, said piston having an external torus-shaped surface for co operation with the wall of said cylinder whereby relative travel between said cylinder and said piston follows a curved line centered on said external point.
  • a control device as claimed in claim 2 including a fixed structure and in which one of said hinged elements having a hinge axis is incorporated in said fixed structure, said fixed structure being pivotable about said hinge axis.
  • a control device as claimed in claim 2 in which two said jacks are arranged near each other and on the same side of said hinge axis.
  • hinged elements comprise successive control flaps in the geometry of a conduit formed by circular juxtaposition with partial overlap of upstream flaps followed by a similar juxtaposition of hinged downstream flaps following said upstream flaps.
  • a control device as claimed in claim 8 including a double linkage connecting each of said jacks to the I flaps associated therewith.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Supports For Pipes And Cables (AREA)
  • Investigating Materials By The Use Of Optical Means Adapted For Particular Applications (AREA)
  • Transmission Devices (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
US00216195A 1971-01-08 1972-01-07 Arrangement of jacks for controlling flaps and its application to the control of a jet pipe Expired - Lifetime US3739987A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7100528A FR2123115B1 (enrdf_load_stackoverflow) 1971-01-08 1971-01-08

Publications (1)

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US3739987A true US3739987A (en) 1973-06-19

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US00216195A Expired - Lifetime US3739987A (en) 1971-01-08 1972-01-07 Arrangement of jacks for controlling flaps and its application to the control of a jet pipe

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US (1) US3739987A (enrdf_load_stackoverflow)
DE (1) DE2200656A1 (enrdf_load_stackoverflow)
FR (1) FR2123115B1 (enrdf_load_stackoverflow)
GB (1) GB1373553A (enrdf_load_stackoverflow)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4000611A (en) * 1975-07-01 1977-01-04 General Electric Company Variable area, load balancing nozzle
US5571262A (en) * 1983-01-13 1996-11-05 Societe Natinonale D'etude Ed De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle for a turbojet engine

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB538168A (en) * 1939-01-19 1941-07-23 Ganz & Company Ltd Improvements in control devices, especially suitable for controlling internal combustion engines
US2649077A (en) * 1951-07-30 1953-08-18 North American Aviation Inc Piston assembly for oscillatory hydraulic actuators
US2984068A (en) * 1958-06-30 1961-05-16 Orenda Engines Ltd Propulsive nozzle system for reaction propulsion units
US3570247A (en) * 1968-09-14 1971-03-16 Rolls Royce Jet nozzle thrust spoiling and thrust reversing mechanism

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB538168A (en) * 1939-01-19 1941-07-23 Ganz & Company Ltd Improvements in control devices, especially suitable for controlling internal combustion engines
US2649077A (en) * 1951-07-30 1953-08-18 North American Aviation Inc Piston assembly for oscillatory hydraulic actuators
US2984068A (en) * 1958-06-30 1961-05-16 Orenda Engines Ltd Propulsive nozzle system for reaction propulsion units
US3570247A (en) * 1968-09-14 1971-03-16 Rolls Royce Jet nozzle thrust spoiling and thrust reversing mechanism

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4000611A (en) * 1975-07-01 1977-01-04 General Electric Company Variable area, load balancing nozzle
US5571262A (en) * 1983-01-13 1996-11-05 Societe Natinonale D'etude Ed De Construction De Moteurs D'aviation S.N.E.C.M.A. Supersonic nozzle for a turbojet engine

Also Published As

Publication number Publication date
FR2123115B1 (enrdf_load_stackoverflow) 1975-01-17
FR2123115A1 (enrdf_load_stackoverflow) 1972-09-08
DE2200656A1 (de) 1973-10-31
GB1373553A (en) 1974-11-13

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