US3045705A - Variable nozzles, in particular laval nozzles for wind tunnels - Google Patents

Variable nozzles, in particular laval nozzles for wind tunnels Download PDF

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US3045705A
US3045705A US609314A US60931456A US3045705A US 3045705 A US3045705 A US 3045705A US 609314 A US609314 A US 609314A US 60931456 A US60931456 A US 60931456A US 3045705 A US3045705 A US 3045705A
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nozzle
wall
nozzles
roller
rollers
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Hausammann Werner
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
    • G01M9/02—Wind tunnels
    • G01M9/04—Details

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  • My present invention relates to improvements in variable nozzles, in particular Laval nozzles for wind tunnels, and the main object of the invention is to make provision for adjusting a nozzle form calculated for all the desirable Mach numbers in a certain range more accurately and more quickly than has been attainable with means known so far.
  • Adjustable Laval nozzles are used generally for the most eflicient exploitation of large supersonic wind tunnels, being charged with the task of producing a parallel and shockfree supersonic flow in the test section proper, i.e. in the vicinity of the model to be tested.
  • the sliding nozzle block has attained some importance.
  • a one-sided nozzle block is shifted in the flow direction so that the block is situated in a different position for each Mach number.
  • Such nozzles have the disadvantage that their contours afford a uniform Mach number distribution in the test section only in two or three positions and give only an approximate flow in the intermediate positions.
  • Such a solution is never quite satisfactory.
  • the sliding nozzle block leads to inconveniently long nozzle structures which, furthermore, are unfavorable as to friction losses and lead to excessively thick boundary layers on the walls. The nozzle quality thereby is impaired and substantial corrections are required on the contours which are correspondingly unreliable and only empirically definable.
  • Nozzles having deformable contours also are known. These nozzles comprise flexible plates on two opposite sides, which are movable between the other walls which are substantially parallel to each other. Within certain limits, defined by the permissible elastic deformation of these plates, the latter may be continuously deformed for all Mach numbers of the tunnel range.
  • the mechanism used for deformation so far comprises a great number of threaded spindles standing essentially at right angles to the plate contours, which spindles are individually adjustable in dependence on the Mach number. Smooth, nonthreaded spindles controlled by individual cams may also be used.
  • the flexible plates are supported only at discrete points, which entails unfavorable consequences. With respect to the plate thickness, a compromise always has to be made. In the case of a very thin plate, it may become wavy between the supporting spindles, whereas thick plates, on account of the permissible curvatures, lead to long nozzles and a great number of spindles.
  • said spindle design is expensive and very complicated, in particular with regard to the adjustment to different Mach numbers.
  • Such adjustment in the case Patented July 24, 1962 of manual spindle setting, requires a repetitious procedure in several steps in order to avoid local overstressing of the plates, for which purpose, by the way, safety features have been incorporated in known designs, but which again are costly and complicated and may cause difficulties. When these safety features fail in operation, there is the risk of a permanent plate deformation.
  • the repetitious procedure when changing the Mach number is, of course, correspondingly slow, requiring approximately 15 to 30 minutes for passing through a somewhat larger Mach number range.
  • the present invention aims to overcome said disadvantages.
  • the present nozzle comprises adjustable supportingmeans with the aid of which at least one nozzle wall is supported, and is characterized by the fact that the adjustable supporting means extend along the flexible nozzle wall and are in contact with this wall along at least one predetermined supporting curve so that the geometrical nozzle shape is continuously changed in a predetermined manner by the adjustment of the supporting means.
  • FIG. 1 shows schematically the adjustable walls of a nozzle in section
  • FIG. 2 depicts the adjustable Laval nozzle without sidewalls
  • FIG. 3 is a fragmentary partly sectional side elevational view of another embodiment of a nozzle according to the present invention.
  • FIG. 4 is a transverse sectional view of the upper half of the nozzle showing structure located adjacent the front end thereof;
  • FIG. 5 shows a fragmentary transverse sectional view of driving structure adjacent the right end of FIG. 3 for driving the adjusting rollers.
  • FIG. 1 The parts essential, from the aerodynamic point of view, to a Laval nozzle are schematically shown in FIG. 1.
  • the fluid is further accelerated to supersonic velocity (Mach number 1).
  • Super-sonic portion 4 is made up of an expansion portion 5, an extinguishing portion 8 and an intermediate transition portion 7 which commences at the point of inflexion 6.
  • the nozzle portions '7 and 8 lying downstream of point 6 serve for extinguishing the so-called expansion waves. Only by cancelling or extinguishing the Mach waves originating in expansion portion 5' on the wall contours, i.e. preventing the reflection thereof, can a shockfree and parallel flow arise in a test rhonrbus 14.
  • Shaping of the extinguishing portion 8 in dependency on the wall contour of expansion portion 5, which contour may be freely chosen within certain limits, is done according to known methods of aerodynamics. With each Mach number there is associated in the test rhombus 14 another nozzle contour having another cross-sectional ratio between least cross-section 3 and test crosssection 9.
  • variable nozzle contour is attained according to FIG. 2 as follows:
  • the expansion portion up to the point of inflexion 6 comprises a non-deformable inlet section 20.
  • section 24 ⁇ When changing the Mach number, section 24 ⁇ is turned about an axis of instantaneous rotation which moves along a curve for the entire Mach number range.
  • the inlet section is guided in predetermined tracks by rails 21 when changing the Mach number, and it is adjusted for example by means of spindles 22.
  • the shape of extinguishing section 8 is imparted to a relatively thin plate 23 by means of parallel rollers 24 of appropriate shape.
  • the configuration of the rollers 24 is chosen so that each of the curves along the lines of contact of the rollers with the walls or plates 23 corresponds to a predetermined Mach number.
  • inlet section 20 When the rollers 24 are rotated, inlet section 20 has to be adjusted synchronously. Since the first bearing 26 is fixed in space and the roller axle is self-aligning, a second bearing of the roller mounted in section 20 and not movable in the direction of the roller axis normally moves along the periphery of a circle. If, however, the second bearing is arranged so as to be movable in direction of the roller axis, it follows a track of which the envelopes are circles having their centers on the instantaneous transverse axis of the inlet section.
  • the active range of the rollers suitably lies in a rotary angle range of zero to approximately 360.
  • the plates 23 are clamped in front in said section 20 and, in the rear, at the commencement of test section 9.
  • the flexible plates 23 thus are continuously supported over their entire free length so that no waviness arises. Therefore, thinner plate material of uniform thickness may be used and flexed to a correspondingly greater extent, which leads to short and cheaper nozzles. Some narrow cross-webs for which corresponding recesses (not shown) are provided in the rollers 24, stiffen the thin plates transversely. In place of a long roller, a plurality of rollers may be used, which are interconnected by Cardan joints, with one of the rollers, however, having an axis fixed in space, as described below in connection with FIGS. 3-5.
  • the rollers may rotate in individual bearings, but have to be synchronously driven.
  • a compression load acting on the plates 23 in the axial direction of the rollers also may further the contact.
  • Such compression forces may be brought about by tension springs engaging the ends of the adjustable nozzle wall and extending across the latter, or by means of hydraulically actuated pistons (not shown) secured to the nozzle wall.
  • Vacuum application has two advantages: the contact pressure is continuous and distributed over the entire plate surface.
  • a contact pressure may be set up or controlled which is the same for all the plate positions. It is further possible to still further reduce the disturbing influence of the boundary layer in the corners between flexible plates and fixed walls by evacuating said layer.
  • the nozzle-adjusting mechanism 22, 25 may be hydraulically, pneumatically or electrically actuated, the position of the rollers and thus the nozzle shape and Mach number always being indicated to substantially facilitate the accurate adjustment to a desired Mach number.
  • To adjusting means 25 are connected the two rollers 24.
  • the rollers 24 When turning the spindle of means 25, the rollers 24 also are turned via eccentrically located setting levers.
  • a hydraulic or pneumatic control is especially suitable, as it permits in a particularly simple way to preselect the Mach number to be adjusted next and to set thereby the nozzle quickly and accurately, which constitutes a further advantage of this solution.
  • the rollers can be quickly turned so that in a few seconds the entire Mach number range may be traversed.
  • each of the rollers instead of being in the form of a one-piece elongated roller is composed of a pair of roller portions.
  • FIGS. 3-5 show the upper pair of rollers which cooperate with the upper flexible wall 23, and each of these rollers has a rear portion 30, 30a and a front portion 31, 31a inclined with respect to the rear portion.
  • the rear roller portions 30 and 3011 are each carried by a pair of stationary bearings 26 and 32 which provide each rear roller portion with a stationary turning axis.
  • the front roller portions 31 and 31a are connected with the rear roller portions by universal joints 33, respectively.
  • the end of each front roller portion which is distant from the universal joint is supported for rotation by a bearing 27 which cannot shift axially but which is capable of turning about the universal joint.
  • Each bearing 27 is carried by a pin 34 which is pivotally connected to one end of a link 35 whose opposite end is pivotally connected with the non-deformable inlet section 20.
  • the pair of rollers 30, 31 and 30a, 31a are turned in synchronism in opposite directions, and this turning is derived from a motor 36 (FIG. 4) which drives a pair of sprocket wheels one of which cooperates with the chain 37 which serves to transmit the drive to the upper pair of rollers and the other of which cooperates with the chain 37b to transmit the drive to the lower pair of rollers.
  • the structure which controls the curvature of the lower flexible wall is identical with that shown in the drawing for controlling the curvature of the upper flexible wall 23.
  • the chain 37 actuates a transmission 38 which in turn actuates a spindle drive 22 for axially shifting the spindle 39.
  • the shaft extending from the drive 38 to the drive 22 may be connected in the housing of the drive 22 to a bevel gear meshing with a second bevel gear provided with inner threads which are in threaded engagement with the threads of the spindle 39 so that rotation of the second bevel gear will serve to axially shift the spindle 39, and in this way the nozzle section 20 will move up and down.
  • An extension of nozzle section 20 rises in the curved guideway of the guide 21, so that in this way axial shifting of the spindle 39, which is pivotally connected at its bottom end to nozzle section 20, results in tilting as well as raising and lowering of the section 20.
  • the drive 22 additionally serves to drive a chain 40 which actuates a drive 41 for turning the pairs of rollers simultaneously in opposite directions.
  • the transmission 41 operates through a pair of intermediate gears 42 on gears fixed coaxially to the rear ends of the rollers. The simultaneous turning of the pairs of rollers in opposite directions serves to prevent lateral shifting of the flexible nozzle walls 23.
  • the chamber 43 (FIG. 3) in which. the pair of rollers are located is sealed at its front end by sealing plate 44 and at its rear end by the fixing of the rear end of the plate 23 to the support 45.
  • the side edges of each plate or wall 23 can slide up and down with respect to the vertical nozzle walls.
  • the chamber 43 is evacuated by being placed in communication with the vacuum pump or the like, and by this evacuation each plate or wall 23 is continuously maintained along substantially its entire length in engagement with the pair of rollers which control its curvature.
  • the plate 23 (FIG. 3) is provided with transverse ribs 46 which serve to stiifen relatively thin flexible wall 23, and the rollers have annular grooves which receive the ribs.
  • the use of vacuum to maintain the flexible walls in engagement with the rollers is of advantage since in this Way the pressing of the walls against the rollers takes place continuously along the entire flexible wall.
  • the vacuum serves in addition to remove the boundary layer from the interior of the nozzle.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall having an inner surface defining part of a wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle; and means extending longitudinally along said flexible wall and engaging said outer surface thereof for controlling the curvature of said wall, said means being turnable about at least one axis which extends longitudinally with respect to said wall and said means having an outer surface engaging said outer surface of said wall and provided with different longitudinal contours in different radial planes, respectively, which include said axis so that the curvature of said wall will change when the angular position of said means with respect to said axis changes.
  • said means including a pair of roller portions arranged in end to end relation and inclined one with respect to the other.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall having an inner surface defining part of a wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle; and elongated roller means extending longitudinally along said flexible wall and engaging said outer surface thereof for controlling the curvature of said wall, said roller means being turnable about its axis and having an outer surface engaging said outer surface of said wall and provided with different longitudinal contours in different radial planes, respectively, so that when said roller means is in different angular positions it will have different longitudinal contours in engagement with said outer wall surface for giving the latter different curvatures.
  • roller means providing a gradual change in the curvature of said wall during turning of said roller means from one angular position to another angular position.
  • suction means acting on said wall for maintaining the latter in engagement with said roller means.
  • said suction means also removing a boundary layer from the nozzle.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall having an inner surface defining part of a wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle; and a pair of elongated parallel roller means extending longitudinally along said flexible wall and engaging said outer surface thereof for controlling the curvature of said wall, said pair of roller means having outer surfaces engaging said outer surface of said wall, the outer surface of one roller means being symmetrical with respect to the outer surface of the other roller means and each of said roller means being provided at its outer surface with different longitudinal contours in different radial planes, respectively, and said pair of roller means being substantially coextensive and located beside each other; and turning means operatively connected to said roller means for turning the same simultaneously in opposite directions through equal angles, said pair of roller means having at any instant identical longitudinal contours in engagement with the outer surface of said flexible wall, so that the curvature of the latter will be different at different angular positions of said pair of roller means.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall whose curvature is to be controlled, said Wall having an inner surface defining part of a Wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle; at least one elongated roller of substantially the same length as said wall extending along said wall and longitudinally engaging the outer surface thereof along almost the entire length thereof without interruption between the ends of said roller, the outer surface of the latter having different longitudinal contours in different radial planes; and turning means operatively connected to said roller for turning the same to a predetermined angular position to place a predetermined longitudinal contour of said outer surface thereof in engagement with said outer surface of said Wall to control the curvature thereof.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall whose curvature is to be controlled, said wall having an inner surface defining part of a wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle; elongated roller means extending longitudinally along the outer surface of said wall and engaging the latter outer surface for controlling the curvature of said wall, said outer surface of said roller means having dilferent longitudinal contours in different radial planes so that the curvature of said Wall will be different in different angular positions of said roller means; and means operatively connected to said roller means for changing the inclination thereof while said wall remains in engagement with the outer surface of said roller means.
  • an adjustable wind tunnel nozzle in combination, at least one elongated flexible wall having an inner surface defining part of a wind tunnel nozzle and having an outer surface opposite from said inner surface, said wall extending longitudinally along the nozzle, said wall being thin and having stiffening ribs at its outer surface extending transversely across said wall; and an elongated roller extending longitudinally along said wall and engaging said outer surface thereof between said ribs, said roller being formed with annular grooves which respectively receive said ribs and said roller having at its outer surface different longitudinal contours in different radial planesso that said wall by engagement with said roller will have different curvatures in different angular positions of said roller, respectively.

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  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
US609314A 1955-09-12 1956-09-11 Variable nozzles, in particular laval nozzles for wind tunnels Expired - Lifetime US3045705A (en)

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Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3099291A (en) * 1961-03-22 1963-07-30 Nat Drying Machine Company Adjustable nozzle
US3443598A (en) * 1964-12-04 1969-05-13 Technology Uk Fluid ducts
US3453878A (en) * 1967-06-22 1969-07-08 Garrett Corp Wind tunnel
US3461833A (en) * 1966-12-27 1969-08-19 Bendix Corp Fluid variable pressure device
US4398415A (en) * 1981-12-10 1983-08-16 The United States Of America As Represented By The Secretary Of The Air Force Swing link flexible wind tunnel nozzle
US5397062A (en) * 1992-11-21 1995-03-14 Zeppelin Schuettguttechnik Gmbh Device for setting a prescribed gas quantity
WO2002014728A1 (en) * 2000-08-10 2002-02-21 Halton Company, Inc. Flow-volume control device
US20060032492A1 (en) * 2001-01-23 2006-02-16 Rick Bagwell Real-time control of exhaust flow
US8734210B2 (en) 2007-05-04 2014-05-27 Oy Halton Group Ltd. Autonomous ventilation system
US8795040B2 (en) 2007-08-28 2014-08-05 Oy Halton Group Ltd. Autonomous ventilation system
CN104316287A (zh) * 2014-10-24 2015-01-28 中国人民解放军国防科学技术大学 二维变马赫数喷管及使用该喷管的超声速变马赫数风洞
US9494324B2 (en) 2008-12-03 2016-11-15 Oy Halton Group Ltd. Exhaust flow control system and method
US10184669B2 (en) 2004-07-23 2019-01-22 Oy Halton Group Ltd Control of exhaust systems
US20220120237A1 (en) * 2020-10-15 2022-04-21 Cfd Research Corporation Variable three dimensional convergent-divergent nozzle

Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2462953A (en) * 1946-02-05 1949-03-01 United Aircraft Corp Adjustable cone orifice
US2472949A (en) * 1947-10-31 1949-06-14 Pittsburgh Des Moines Company Flexible nozzle for supersonic wind tunnels
US2486287A (en) * 1947-03-13 1949-10-25 Pittsburgh Des Moines Company Sealing means for the joints between the movable and stationary walls of an adjustable wind tunnel nozzle
US2546673A (en) * 1946-07-13 1951-03-27 Emory D Mattix Flow control valve
US2570129A (en) * 1948-08-18 1951-10-02 Gen Electric Supersonic wind tunnel
US2590215A (en) * 1947-02-21 1952-03-25 Frank C Sausa Variable throat restricter valve
US2625008A (en) * 1951-02-28 1953-01-13 Curtiss Wright Corp Variable flow nozzle
US2696110A (en) * 1952-05-02 1954-12-07 Jr Alfred J Eggers Variable-constriction nozzle
US2709917A (en) * 1952-02-15 1955-06-07 United Aircraft Corp Transonic flow control

Patent Citations (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2462953A (en) * 1946-02-05 1949-03-01 United Aircraft Corp Adjustable cone orifice
US2546673A (en) * 1946-07-13 1951-03-27 Emory D Mattix Flow control valve
US2590215A (en) * 1947-02-21 1952-03-25 Frank C Sausa Variable throat restricter valve
US2486287A (en) * 1947-03-13 1949-10-25 Pittsburgh Des Moines Company Sealing means for the joints between the movable and stationary walls of an adjustable wind tunnel nozzle
US2472949A (en) * 1947-10-31 1949-06-14 Pittsburgh Des Moines Company Flexible nozzle for supersonic wind tunnels
US2570129A (en) * 1948-08-18 1951-10-02 Gen Electric Supersonic wind tunnel
US2625008A (en) * 1951-02-28 1953-01-13 Curtiss Wright Corp Variable flow nozzle
US2709917A (en) * 1952-02-15 1955-06-07 United Aircraft Corp Transonic flow control
US2696110A (en) * 1952-05-02 1954-12-07 Jr Alfred J Eggers Variable-constriction nozzle

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3099291A (en) * 1961-03-22 1963-07-30 Nat Drying Machine Company Adjustable nozzle
US3443598A (en) * 1964-12-04 1969-05-13 Technology Uk Fluid ducts
US3461833A (en) * 1966-12-27 1969-08-19 Bendix Corp Fluid variable pressure device
US3453878A (en) * 1967-06-22 1969-07-08 Garrett Corp Wind tunnel
US4398415A (en) * 1981-12-10 1983-08-16 The United States Of America As Represented By The Secretary Of The Air Force Swing link flexible wind tunnel nozzle
US5397062A (en) * 1992-11-21 1995-03-14 Zeppelin Schuettguttechnik Gmbh Device for setting a prescribed gas quantity
WO2002014728A1 (en) * 2000-08-10 2002-02-21 Halton Company, Inc. Flow-volume control device
US9909766B2 (en) 2001-01-23 2018-03-06 Oy Halton Group Ltd. Real-time control of exhaust flow
US20110174384A1 (en) * 2001-01-23 2011-07-21 Oy Halton Group Ltd. Real-time control of exhaust flow
US20110005507A9 (en) * 2001-01-23 2011-01-13 Rick Bagwell Real-time control of exhaust flow
US9335057B2 (en) 2001-01-23 2016-05-10 Oy Halton Group Ltd. Real-time control of exhaust flow
US20060032492A1 (en) * 2001-01-23 2006-02-16 Rick Bagwell Real-time control of exhaust flow
US11242999B2 (en) 2004-07-23 2022-02-08 Oy Halton Group Ltd. Control of exhaust systems
US10184669B2 (en) 2004-07-23 2019-01-22 Oy Halton Group Ltd Control of exhaust systems
US8734210B2 (en) 2007-05-04 2014-05-27 Oy Halton Group Ltd. Autonomous ventilation system
US9127848B2 (en) 2007-05-04 2015-09-08 Oy Halton Group Ltd. Autonomous ventilation system
US8795040B2 (en) 2007-08-28 2014-08-05 Oy Halton Group Ltd. Autonomous ventilation system
US9587839B2 (en) 2007-08-28 2017-03-07 Oy Halton Group Ltd. Autonomous ventilation system
US10302307B2 (en) 2007-08-28 2019-05-28 Oy Halton Group Ltd. Autonomous ventilation system
US9494324B2 (en) 2008-12-03 2016-11-15 Oy Halton Group Ltd. Exhaust flow control system and method
US10082299B2 (en) 2008-12-03 2018-09-25 Oy Halton Group Ltd. Exhaust flow control system and method
CN104316287A (zh) * 2014-10-24 2015-01-28 中国人民解放军国防科学技术大学 二维变马赫数喷管及使用该喷管的超声速变马赫数风洞
CN104316287B (zh) * 2014-10-24 2017-01-11 中国人民解放军国防科学技术大学 二维变马赫数喷管及使用该喷管的超声速变马赫数风洞
US20220120237A1 (en) * 2020-10-15 2022-04-21 Cfd Research Corporation Variable three dimensional convergent-divergent nozzle
US12121889B2 (en) * 2020-10-15 2024-10-22 Cfd Research Corporation Variable three dimensional convergent-divergent nozzle

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