US3582231A - Bearing mount for vane rings of turboengines - Google Patents

Bearing mount for vane rings of turboengines Download PDF

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Publication number
US3582231A
US3582231A US779545A US3582231DA US3582231A US 3582231 A US3582231 A US 3582231A US 779545 A US779545 A US 779545A US 3582231D A US3582231D A US 3582231DA US 3582231 A US3582231 A US 3582231A
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United States
Prior art keywords
blade carrier
blade
combination
wall
set forth
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
US779545A
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English (en)
Inventor
Ferdinand Zerlauth
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Sulzer AG
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Sulzer AG
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Filing date
Publication date
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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

  • ng are supported in an tside of the blade carrier.
  • the inner wall e outer wall to form an open-ended from the working medim m u e mw h f 8m 0 &0 w f M 0d a e hme ew h d o asdn g MMummn 0 m mkmowu ic m Sm mm m A wpflilr. w dm h hm C m B mmmm Am who 5 68 3nwm97 ll W i-l s 25 1 96 l d/ 4 0 1..
  • This invention relates to a bearing mount for vane rings of turboengines. More particularly, this invention relates to a bearing mount for vane rings having rotatably adjustable blades.
  • Turboengines have been known to employ vane rings in which a plurality of blades have been mounted for angular adjustment with respect to the plane of the vane rings by rotation about the longitudinal axes of the respective blades. Because of the adjustability of the blades, such turboengines, and in particular turbines, have advantageously been adapted during operation to heavy load changes within wide limits without undergoing any substantial loss in efficiency and flow disturbances. Conversely, however, with the use of adjustable blades, particularly at elevated temperatures, troubles have occurred in many instances in the blade bearings. For example, such blade bearings have been exposed to the detrimental effects as well as the heat of the working medium of the turboengines.
  • the invention provides a bearing mount for each blade of a turboengine vane ring wherein the bearing mount is fixed to the outside of a blade carrier of the vane ring remote from the working medium of the turboengine.
  • the bearing mount includes an axle housing having an inner tubular wall which carries bearings for rotatably mounting an axle of a blade and an outer wall which closes off the housing.
  • the inner wall is formed with respect to the outer wall so as to define a hollow space therebetween.
  • the inner wall can be cylindrical and supported on the outer wall by at least two spaced annular supports.
  • the support closest the blade carrier is preferably disposed at a distance from the end of the inner and outer walls to form a second hollow space which, however, is open ended in the direction of the blade carrier.
  • the inner tubular wall accommodates, at least in the areas at the two extremities, a bearing bushing having a cylindrical bore.
  • bearing bushings are preferably formed of a plastic suitable for dry operation without any special supply of lubricant and suitable for elevated temperatures, for example, the commercially available plastic known under the name DU which is resistant up to temperatures of 280 C.
  • At least one group of bearing mounts have a distributor line connected into the respective closed hollow spaces for circulating a coolant, such as air, through the closed hollow space in order to cool the bearings and axle housing.
  • a coolant such as air
  • One or more bores are also provided in the annular support of these bearing mounts between the closed hollow spaces and open hollow spaces in order to introduce the coolant into the open hollow spaces. This allows the part of the axle housing most exposed to a rise in temperature to be supplied from the distributor line with a required amount of coolant.
  • This embodiment can be further simplified by having the closed hollow spaces form a part of the distributor line, for example, by having the hollow spaces of each pair of adjoining housings interconnected by tube sections of the distributor line.
  • a seal is mounted at a point outside of the bearing remote from the blade between the axle journal of the blade and the axle housing.
  • the axle housing is supported only with the outer wall on the blade carrier so that the inner wall and bearings are not directly supplied with heat by the blade carrier. Also,
  • the axle housing can be attached to the blade carrier by means of a flange which preferably surrounds the axle housing at a point distant from the blade carrier.
  • a displacement body can be placed in the open hollow space of an axle housing to define a flat flow path of narrow cross section with the opposite surfaces of the inner and outer walls for the coolant.
  • a displacement body can be made of sheet metal with a U-shaped cross section, the outer leg of which is of greater length than the inner leg so as to rest on the blade carrier. Bores can also be arranged in the extended length of the outer leg to permit the coolant to flow against the neck of the blade passing through the blade carrier.
  • FIG. I illustrates a fragmentary cross-sectional view of a vane ring according to the invention taken on line II-of FIGS.
  • FIG. 2 illustrates a view taken on line II-II of FIG. 1;
  • FIG. 3 illustrates a view taken in the plane of line III-III of FIG. 1 of two adjacent axle housings
  • FIG. 4 illustrates a view taken on line IV-IV of FIG. 1;
  • FIG. 5 illustrates a cross-sectional view of a modified blade design and coolant passageway according to the invention.
  • FIG. 6. illustrates a modified connection between adjacent bearing axle housings for the coolant flow.
  • the vane ring includes an annular blade carrier 1 and a plurality of blades, for example, 28, which are circumferentially spaced and carried on the blade carrier 1 substantially radially of the rotor shaft (not shown) in the ring plane III-III.
  • the blade carrier 1 is formed with a bore 2 for each blade as well as with a recess 3 about the bore 2 forreceiving an axle housing 4 of a bearing mount.
  • Each blade is formed with a part 5 which contacts the working medium, a neck 6 substantially within the plane of the blade carrier 1, a blade journal 7 and an axle journal 8 secured about the blade journal 7.
  • the part 5 merges into the neck 6 at the lower end while the neck 6 which is provided with cooling ribs 23 merges into the blade journal 7 to form a one-piece blade.
  • This blade is further either forced into the journal 8 or is shrunk on by undercooling.
  • the blade and journal 8 can be made as a compound cast element, for example, by precision casting and by forming part 5 of a heat resistant steel and by forming the other parts, particularly at the bearing surfaces, of a material having suitable dry operation properties.
  • Each axle housing 4 is individually secured to the blade carrier 1 and is formed with an inner wall 9 of tubular shape which carries a pair of bearings 10, 11 in supporting relation to the axle journal 8.
  • the axle housing 4 is also formed with an outer wall 20 by which the axle housing 4 is supported in the recess 3.
  • the outer wall 20 also supports the inner wall 9 at two spaced points via annular supports 12, 13 while forming an open hollow space 14 and a closed hollow space 15 between the walls 9, 20.
  • the open hollow space 14 is situated at a point closer to the blade carrier 1 than the closed hollow space 15 while being in facing relation to the blade carrier 1.
  • the closed hollow spaces 15 of at least one group of axle housings 4 are interconnected by means of pipes 17 and together constitute a distribution line.
  • a gaseous coolant for instance, air.
  • at least one of the housings 4 connected to the distribution line 16 is further connected with a supply line 19 (FIG. 2) which provides the total amount of gas required for the cooling of all the housings 4 connected to the distribution line 16.
  • a supply line 19 FIG. 2
  • two supply pipes can be attached to the lower half of the blade carrier and connected to the two axle housings 4 next to their respective axial separating planes.
  • an inherently closed distribution line 16 is produced with two substantially diametrically opposite supply connections. During inspection and cleaning operations of the vane rings, the supply lines need not be removed.
  • the open hollow space 14 and the closed hollow space 15 which forms a part of the distribution conduit 16 in each housing are interconnected by means of bores 18. These bores 18 allow the partial amount of the cooling gas required for each axle housing 4 to be branched off from the distribution line 16 to the individual cooling sites.
  • a displacement body 39 of U- shaped cross section and discontinuous length is mounted in the open space 14 in inverted manner to form a pair of narrow coolant flow passages with the walls 9, 20.
  • the outer leg of the body 39 is of greater length than the inner and rests on a plate 22in the recess 3 of the blade carrier 1. Bores 38 are provided in the lower end of this outer leg to permit coolant flow towards the blade neck 6.
  • the axle journal 8 designed for these bearings must be made of a material capable of sliding without wear and without a special supply of lubricants on a bearing plastic selected in this manner without either impairing itself or the bearings l0, l1.
  • Each axle housing 4 includes a peripheral flange 21 near the base of the outer wall which facilitates tightening of the housing 4 against the blade carrier 1 and the plate 22 positioned therebetween.
  • the flange 21 surrounds the axle housing 4 at a distance from the blade carrier 1 so as to minimize the transmission of heat from the blade carrier 1 to the axle housing 4.
  • the opposite end of the axle housing 4 has a thrust bearing mounted between the axle journal 8 and the housing 4.
  • the thrust bearing includes a rotor disc 24 secured to the journal 8, a pair of sliding discs 25 on opposite sides of the rotor disc 24, and a mounting plate 26 secured on the housing 4 over the discs 24, 25.
  • a sealing ring 55 is further mounted in a groove of the disc 26 to prevent an escape of cooling gas out of the axle housing 4 along the journal 8 into the space surrounding the blade carrier 1.
  • a hub 27 of an adjustable lever 28 is keyed over the end of the journal 8 to sealingly engage the sealing ring and to clamp the rotor disc 24 and the sliding discs 25 together against a shoulder 29 of the axle journal 8 so that the discs 24, 25 follow the rotational motions of the journal 8 and lever 28.
  • the cooling ribs 23 on the neck 6 of the blade are surrounded by a sleeve 30 mounted with a slight clearance within the plate 22.
  • the sleeve 30 is compressed at one end by means of the spring 31 against a recess 32 of a ring segment 33 of the blade carrier 1 and is prevented from falling out of the plate 22 by means of a circlip 34 in a groove at the other end.
  • the sleeve 30 is fitted tightly onto the cooling ribs 23 so as to be centered by the blade free of resistance in the plate 22.
  • a plurality of bores 39 are provided in the sleeve 30 to communicate the opposite sides of the sleeve with each other.
  • the cooling ribs 23 are provided with milled sections 35 alternating from rib to rib by a semicircumference and thereby face each other in two groups.
  • the cooling air supplied over the supply line 19, for instance at a temperature of approximately 130 C., and distributed into the open space 14 passes with increased speed in a thin layer between the displacement body 36 and the inner and outer walls 9 and 20, respectively, toward the blade neck 6; the cooling air flowing along the outer wall 20 being directed by means of the bores 38 in the displacement body leg toward the blade neck 6.
  • the cooling air is then subdivided into two halves between the cooling ribs 23 by means of the milled sections 35 and passes around the one and the other side of the blade neck. Opposite the input point at the first cooling rib 23, the two halves of coolant flow join again in the milled section 35 of the second cooling rib 23.
  • the air separates again into two halves and flows in this manner between the second and third ribs of the blade neck. After leaving the intermediary space bordering the last rib, the air passes on through the bores 39 of the sleeve 30 into the space surrounding these bores and flows then through ducts (not shown) into the flow passage of the work medium within the blade carrier 1.
  • the bearing points of the blades in particular the bearing 10 situated closest to the blade carrier 1 and, hence, to the flow of the work medium, can be kept at a temperature capable of insuring trouble-free operation.
  • the cooling gas also acts simultaneously as a blocking gas for the axle housing 4 in view of the fact that its pressure must always be greater than the pressure of the working medium in the rotor space. This prevents the penetrating of working medium or residues thereof into the axle housing 4 and, as a result of impurities or foreign substance that are carried along, in particular upon running in of the engine, the soiling of the bearing surfaces of the axle journal 8.
  • the seal 55 because of the seal 55, the space between the inner wall 9 and the axle journal 8 is sealed off with respect to the space surrounding the blade carrier 1 so that even in the case of a possible overpressure of the working medium, the working medium is prevented from passing through along the bearing surfaces.
  • the part 5 contacted by the working medium can have a temperature up to 600 C. and more.
  • a flow of heat can be produced over the blade neck 6, the blade journal 7, the axle journal 8, and the bearings 10, 11 against areas ofa lower temperature at the outside of the engine.
  • this heat flow is substantially reduced ahead of the bearing 10 as a considerable amount of heat is drawn off by the cooling air at the cooling ribs 23 before the heat reaches the blade journal 8.
  • An additional heat transmission loss of the heat flow can be achieved by reducing the cross section of the blade journal 8 and blade neck 6 by means of a central bore 40 in the blade and, as a result, the conduction cross section of the heat flow.
  • the bearing sleeve 10 cooled from the outside by means of the cooling air passing along at the free end of the inner wall 9.
  • the part of the cooling air passing along the inner side of the outer wall 20 reduces the influx of heat from the blade carrier 1 through the outer wall 20 onto the supports 12, 13 of the inner wall 9 and hence to the bearing sleeves 10, 11.
  • a metallurgical connection is produced between the blade part 5 contacted by the work medium and the axle journal 8 in the area of the blade neck 6, for instance at the point 41 as shown.
  • an alloy is produced along a short stretch of the two different parts so that, after completion of the cast element, the blade appears as a single workpiece that can be machined.
  • the compound casting is arranged in such a way that the alloy site is at a point at which at least the work medium cannot supply any additional heat to the blade and, conversely, at which the blade is not yet fitted in a bearing.
  • the axle journal 8 is reduced in diameter at the point 42 and a bearing tube 43 is slid over the reduced portion and welded to the axle journal 8 to form a hollow space 44 and receive the bearing sleeve 10.
  • This hollow space 44 is connected by bores 45 in the journal 8 to the space 46 surrounding the blade neck 6 and, in addition, by means of radial bores 47 in the journal 8 with a central bore 40 in the journal 8.
  • the central bore 40 leads into the open so that a partial amount of the flow of coolant determined by a dosing drum bore (as bore 55 in FIG. 1) is diverted in the space 46 and guided through the hollow space 44.
  • a dosing drum bore as bore 55 in FIG. 1
  • the expansion pipes 17 can be of a length that is greater than the spacing between adjoining housings 4. That is, the expansion pipes 17 can be installed between the bearing housings 4 by, means of a suitable tool and be then expended against the housings 4. The expansion tubes 17 are thus urged elastically against the openings 48 of the axle housings 4 and are also pressed against the openings 48 as a result of internal pressure.
  • connecting flanges 49 are connected to the ends of the expansion pipes 17 and are preferably provided with collars 50 to form gripping surfaces.
  • the bearings are removed, first, from the direct influence of the work medium. Second, so much heat is removed from the bearing housing and, indirectly from the bearings by means of a coolant that the bearing surfaces themselves will have a temperature that excludes their being subjected to damaging. Furthermore, the control of the various bearing points as well as possible replacement of defective elements is substantially simplified.
  • a vane ring having a blade carrier and a plurality of blades passing therethrough, each said blade having an axle journal extending outwardly through said blade carrier to the outside thereof; and a separate bearing mount for each blade radially removable therefrom, each bearing mount having an axle housing fixed to said blade carrier on the outside thereof, said axle housing rotatably supporting said axle journal therein with respect to said blade carrier, and including means for removably mounting each said bearing mount individually on a respective blade whereby each said bearing mount can be removed from said carrier.
  • a vane ring having a blade carrier and a plurality of blades passing therethrough, each said blade having an axle journal extending outwardly through said blade carrier to the outside thereof; and a bearing mount having an axle housing fixed to said blade carrier on the outside thereof, said axle housing rotatably supporting said axle journal therein with respect to said blade carrier and including an inner tubelike wall and an outer wall defining the exterior of said housing and which further includes at least one bearing mounted on said inner wall in supporting relation to said axle journal.
  • axle housing further includes at least two annular supports supporting said inner wall on said outer wall in spaced relation to define a closed hollow space therebetween, said annular support closest said blade carrier being spaced inwardly of the adjacent ends of said inner and outer walls to define an openended hollow space therebetween facing said blade carrier.
  • annular support closest saidblade carrier includes a dplurality of bores communicating said closed hollow space an said openended hollow space with each other for the flow of coolant therebetween.
  • each bearing sleeve is made of a heat resistant plastic material characterized in being free of a lubricant supply.
  • said inner and outer wall define an open-ended hollow space therebetween facing said blade carrier and which further comprises a displacement body in said hollow space forming a flat narrow passage along the surfaces thereof opposite each of said inner and outer walls and means for introducing a flow of coolant into said hollow space to flow through said flat narrow passages.
  • said displacement body is of U-shaped cross section, the outer leg of said body being of greater length than the inner leg and being supported on said blade carrier, said outer leg including bores adjacent the end thereof communicating opposite sides of said leg with each other for a flow of coolant towards said blade.
  • a vane ring having a blade carrier and a plurality of blades passing therethrough, each said blade having an axle journal extending outwardly through said blade carrier to the outside thereof; and a bearing mount having an axle housing fixed to said blade carrier on the outside thereof, said axle housing rotatably supporting said axle journal therein with respect to said blade carrier and including a peripheral flange spaced from said blade carrier for mounting of said axle housing on said blade carrier.
  • axle housing further includes means for conducting a coolant therethrough for cooling said axle journal therein.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Mounting Of Bearings Or Others (AREA)
  • Magnetic Bearings And Hydrostatic Bearings (AREA)
US779545A 1968-07-26 1968-11-27 Bearing mount for vane rings of turboengines Expired - Lifetime US3582231A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CH1127668A CH494895A (de) 1968-07-26 1968-07-26 Leitschaufelkranz für Turbomaschinen

Publications (1)

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US3582231A true US3582231A (en) 1971-06-01

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ID=4371878

Family Applications (1)

Application Number Title Priority Date Filing Date
US779545A Expired - Lifetime US3582231A (en) 1968-07-26 1968-11-27 Bearing mount for vane rings of turboengines

Country Status (7)

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US (1) US3582231A (de)
BE (1) BE731928A (de)
CH (1) CH494895A (de)
DE (1) DE1751812B2 (de)
FR (1) FR2013758A1 (de)
GB (1) GB1271822A (de)
NL (1) NL145635B (de)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3850544A (en) * 1973-11-02 1974-11-26 Gen Electric Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
US4025227A (en) * 1975-06-30 1977-05-24 United Technologies Corporation Variable area turbine
US4277221A (en) * 1976-04-22 1981-07-07 Dominion Engineering Works Limited Wicket gate bearing seal
US6227545B1 (en) * 1997-10-28 2001-05-08 Voith Sulzer Papiertechnik Patent Gmbh Heatable and/or coolable cylinder
US6453556B1 (en) * 2000-10-11 2002-09-24 Hmy Ltd. Method of producing exhaust gas vane blade for superchargers of motor vehicles and vane blade
US20080075583A1 (en) * 2006-08-28 2008-03-27 Abb Turbo Systems Ag Sealing of variable guide vanes
CN112388260A (zh) * 2020-11-20 2021-02-23 无锡航亚科技股份有限公司 一种航空发动机双轴颈整流叶片轴颈的加工方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
US2950084A (en) * 1953-10-15 1960-08-23 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in elastic fluid machines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2651496A (en) * 1951-10-10 1953-09-08 Gen Electric Variable area nozzle for hightemperature turbines
US2950084A (en) * 1953-10-15 1960-08-23 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in elastic fluid machines
US3013771A (en) * 1960-10-18 1961-12-19 Chrysler Corp Adjustable nozzles for gas turbine engine
US3367628A (en) * 1966-10-31 1968-02-06 United Aircraft Corp Movable vane unit

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3850544A (en) * 1973-11-02 1974-11-26 Gen Electric Mounting arrangement for a bearing of axial flow turbomachinery having variable pitch stationary blades
US3966352A (en) * 1975-06-30 1976-06-29 United Technologies Corporation Variable area turbine
US4025227A (en) * 1975-06-30 1977-05-24 United Technologies Corporation Variable area turbine
US4277221A (en) * 1976-04-22 1981-07-07 Dominion Engineering Works Limited Wicket gate bearing seal
US6227545B1 (en) * 1997-10-28 2001-05-08 Voith Sulzer Papiertechnik Patent Gmbh Heatable and/or coolable cylinder
US6453556B1 (en) * 2000-10-11 2002-09-24 Hmy Ltd. Method of producing exhaust gas vane blade for superchargers of motor vehicles and vane blade
EP1197277B1 (de) * 2000-10-11 2004-03-24 HMY, Ltd. Herstellungsverfahren von Schaufeln für Abgasturboladerturbinen von Fahrzeugen und Schaufel
US20080075583A1 (en) * 2006-08-28 2008-03-27 Abb Turbo Systems Ag Sealing of variable guide vanes
CN112388260A (zh) * 2020-11-20 2021-02-23 无锡航亚科技股份有限公司 一种航空发动机双轴颈整流叶片轴颈的加工方法

Also Published As

Publication number Publication date
DE1751812A1 (de) 1970-10-01
NL6811394A (de) 1970-01-29
DE1751812B2 (de) 1971-05-13
GB1271822A (en) 1972-04-26
NL145635B (nl) 1975-04-15
BE731928A (de) 1969-10-23
FR2013758A1 (de) 1970-04-10
CH494895A (de) 1970-08-15

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