US3876742A - Method for manufacturing bladed members from powder material - Google Patents

Method for manufacturing bladed members from powder material Download PDF

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US3876742A
US3876742A US324185A US32418573A US3876742A US 3876742 A US3876742 A US 3876742A US 324185 A US324185 A US 324185A US 32418573 A US32418573 A US 32418573A US 3876742 A US3876742 A US 3876742A
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shroud
mould
aerofoil
mixture
silicon nitride
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US324185A
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Jack Raymond Bird
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Rolls Royce PLC
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Rolls Royce 1971 Ltd
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    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
    • C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/515—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics
    • C04B35/58—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides
    • C04B35/584—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides based on silicon nitride
    • C04B35/593—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on non-oxide ceramics based on borides, nitrides, i.e. nitrides, oxynitrides, carbonitrides or oxycarbonitrides or silicides based on silicon nitride obtained by pressure sintering
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F5/00—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product
    • B22F5/04—Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of turbine blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/284—Selection of ceramic materials
    • 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

  • Guide vanes are usually in the form of an aerofoil portion and two shroud portions and according to the invention, the aerofoil portion is made in a first mould by hot pressing a mixture of silicon nitride powder and a fluxing agent. such as magnesia.
  • the formed aerofoil is placed in a second mould so that each end extends partly into a space which is to be filled with a further mixture of silicon nitride powder and a fluxing agent.
  • the further mixtures are hot pressed both to form the shroud portions and to amalgamate the shroud portions with the aerofoil portion.
  • flanges and webs can be formed in the shrouds during the moulding process or they can be machined into the shrouds after the vane is removed from the second mould.
  • hot pressed dense silicon nitride refers to the method of forming silicon nitride powder as described and claimed in UK. Pat. specification No. 970.639.
  • Nozzle guide vanes usually comprise an aerofoil portion.
  • an inner shroud portion and an outer portion and the shroud portions usually differ in thickness from the aerofoil portion.
  • the different thicknesses of the various portions of the vane prevents homogenous densification of the vane during manufacture as a one piece moulding.
  • the thicker portions will not completely densify and cracking may occur due to internal stresses between sections of different density. For instance elastic moduli. thermal conductivity and strength vary di rectly with changing density.
  • the present invention seeks to provide a method of making a bladed member. such as a nozzle guide vane which overcomes the above difficulties.
  • the present invention provides a method of making a bladed member.
  • the member including an aerofoil portion and at least one shroud portion.
  • the method including the steps of hot pressing a first mixture of silicon nitride powder and a fluxing agent in a suitably shaped first mould to form the aerofoil portion. placing the formed aerofoil portion in locating means. the aerofoil portion extending partly from one end at least of the locating means. placing the locating means in a second mould. placing a second mixture of silicon nitride powder and a fluxing agent in a suitably shaped portion of the second mould. the aerofoil portion extending into the second powder mixture. hot pressing the second powder mixture to form the shroud portion and simultaneously to amalgamate the shroud portion with the aerofoil portion.
  • the bladed member will have two shroud portions and the second mould will therefore have two suitably shaped portions in which the two shroud portions can be formed.
  • the shroud portion or portions can be partly preformed by hot pressing parts of the or each shroud beforehand and attaching these pre-formed parts to a plunger which is adapted to compress the second powder mixture.
  • the pre-formed parts may be formed with fixing means which may include features such as. flanges, webs, dowels and apertures so that completed bladed members can be readily secured within a structure such as a gas turbine engine.
  • the pre-formed parts can be omitted and the plunger may either have a plain face or may be shaped to produce fixing means as above defined in the completed shroud or shrouds.
  • FIG. I shows a plan of one form of mould which can be used for performing the method according to the present invention.
  • FIGS. 2. 3 and 4 show elevations of the mould shown in FIG. 1 at various stages of performing the method according to the present invention.
  • the nozzle guide vane 2 as shown in FIG. 4 consists of an aerofoil portion 4. a root shroud portion 6 and an outer shroud portion 8.
  • a mould 10 consists of a susceptor 12.21 packing ring 14 (FIG. 2) on which the susceptor stands. a split die 16, a locating plunger 18 (FIG. 2) an outer shroud plunger 20. a root shroud plunger 22 and a split aerofoil die 24.
  • the aerofoil portion 4 is preformed by hot pressing a mixture of silicon nitride powder and magnesium oxide in a suitably shaped die.
  • the pressing is preferably carried out at about L200 psi. and at a temperature of about l.75l) C.
  • This method of forming silicon nitride articles is described in detail in UK. Pat. specification No. 970.369 and use of the mctod produces dense. compact silicon nitride articles ofalmost maximum theoretical density.
  • the pre-formed portion 4 is placed in the split aerofoil die 24 so that a small portion of the aerofoil extends beyond each end of the die.
  • the die is then placed in a rectangular aperture 26 in the die 16 and is located on a shoulder 28. the lower end of the aerofoil resting on the locating plunger 18.
  • the space above the aerofoil portion 4 is filled with a mixture of silicon nitride powder and magnesium oxide in the ratio 20 to l by weight. This powder mixture being eventually to form the root shroud portion 6.
  • the amount of powder mixture used depends on the depth ofthe formed root shroud which is required.
  • the root shroud plunger 22 has a preformed root shroud portion 30 lightly attached to it. the portion 30 being of dense silicon nitride and formed by the method de scribed above. The plunger 22 is placed in the aperture and the powder mixture is lightly comptacted at normal temperature.
  • the mould 10, in the configuration shown in FIG. 3 is placed in a press (not shown) and a pressure of about 1,200 psi. is applied at a temperature of about l.750 C.
  • the powder mixtures above and below the aerofoil densify to form the inner and outer shroud portions 6 and 8 respectively.
  • All the preformed portions 30 and 32 amalgamate with the shroud portions 6 and 8 re spectively and the aerofoil portion 4 amalgamates with the shroud portions.
  • a section taken through the completed nozzle guide vane shows that there is virtually no change in the structure across the boundaries between the pre-formed portions of the vane and the shroud portions which are formed in the final pressing action.
  • the preformed portions of the inner and outer shrouds may be omitted or these pre-formed portions may be formed with fixing means. so that the formed bladed member may be readily attached to the engine structure.
  • fixing means typically comprise features such as flanges. webs. apertures and dowels or any combination of these features.
  • the plungers may be formed so that any of these features can be produced on either or both shrouds.
  • the bladed member may be formed with only one of the shroud portions. e.g. the root shourd. in which case. the final configuration of the mould is as shown in FIG. 2.
  • a method of making a bladed member including an aerofoil section and at least one shroud portion. the method including the steps of hot pressing a first mixture of nitride powder and a fluxing agent in a suitably shaped first mould to form said aerofoil portion placing the formed aerofoil portion in locating means. the aerofoil portion extending partly from one end at least of the locating means. placing the locating means in a second mould. placing a second mixture of silicon nitride powder and fluxing agent in a suitably shaped portion of the second mould, the aerofoil portion extending into said second mixture. hot pressing the second mixture to form the shroud portion and to amalgamate the shroud portion with the aerofoil portion.
  • the second mould having two suitably shaped portions. the method including the steps of placing pre-determined quantities of said second powder mixture in the two suitably shaped portions of the second mould, hot pressing the second powder mixture to form the inner and outer shroud portions and to amalgamate said shroud portions with the aerofoil portion.
  • a method as claimed in claim 1 in which a portion of at least one of said two shroud portions is pre-formed by hot pressing a mixture of silicon nitride powder and a t'luxing agent in a suitably shaped mould.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Mechanical Engineering (AREA)
  • Ceramic Engineering (AREA)
  • Materials Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Structural Engineering (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Ceramic Products (AREA)
  • Powder Metallurgy (AREA)
  • Press-Shaping Or Shaping Using Conveyers (AREA)

Abstract

The invention is concerned with manufacturing gas turbine engine components e.g. guide vanes and blades, in dense silicon nitride starting with silicon nitride in a powder form. Guide vanes are usually in the form of an aerofoil portion and two shroud portions and according to the invention, the aerofoil portion is made in a first mould by hot pressing a mixture of silicon nitride powder and a fluxing agent, such as magnesia. The formed aerofoil is placed in a second mould so that each end extends partly into a space which is to be filled with a further mixture of silicon nitride powder and a fluxing agent. The further mixtures are hot pressed both to form the shroud portions and to amalgamate the shroud portions with the aerofoil portion. Features, such as, flanges and webs can be formed in the shrouds during the moulding process or they can be machined into the shrouds after the vane is removed from the second mould.

Description

United States Patent Bird Apr. 8, 1975 1 METHOD FOR MANUFACTURING BLADED MEMBERS FROM POWDER MATERIAL Primary Eraminen-Richard R. Kucia [75] Inventor: Jack Raymond Bird. cheuaston Attorney, Agent, or FtrmCushman. Darby &
Cushman England [73] Assignec: Rolls Royce (1971) Limited. [57] ABSTRACT London England The invention is concerned with manufacturing gas [22] Filed: Jan. 16, 1973 turbine engine components e.g. guide vanes and Appl. No.: 324,185
blades. in dense silicon nitride starting with silicon nitride in a powder form.
Guide vanes are usually in the form of an aerofoil portion and two shroud portions and according to the invention, the aerofoil portion is made in a first mould by hot pressing a mixture of silicon nitride powder and a fluxing agent. such as magnesia. The formed aerofoil is placed in a second mould so that each end extends partly into a space which is to be filled with a further mixture of silicon nitride powder and a fluxing agent. The further mixtures are hot pressed both to form the shroud portions and to amalgamate the shroud portions with the aerofoil portion.
Features, such as. flanges and webs can be formed in the shrouds during the moulding process or they can be machined into the shrouds after the vane is removed from the second mould.
5 Claims. 4 Drawing Figures PATENTEDAPR 8I975 METHOD FOR MANUFACTURING BLADED MEMBERS FROM POWDER MATERIAL This invention relates to a method for making bladed members from powder material. The invention is par ticularly though not exclusively concerned with the manufacture of nozzle guide vanes for gas turbine engines in hot pressed dense silicon nitride.
Throughout this specification the term hot pressed dense silicon nitride refers to the method of forming silicon nitride powder as described and claimed in UK. Pat. specification No. 970.639.
Nozzle guide vanes usually comprise an aerofoil portion. an inner shroud portion and an outer portion and the shroud portions usually differ in thickness from the aerofoil portion. The different thicknesses of the various portions of the vane prevents homogenous densification of the vane during manufacture as a one piece moulding. The thicker portions will not completely densify and cracking may occur due to internal stresses between sections of different density. For instance elastic moduli. thermal conductivity and strength vary di rectly with changing density.
The present invention seeks to provide a method of making a bladed member. such as a nozzle guide vane which overcomes the above difficulties.
Accordingly. the present invention provides a method of making a bladed member. the member including an aerofoil portion and at least one shroud portion. the method including the steps of hot pressing a first mixture of silicon nitride powder and a fluxing agent in a suitably shaped first mould to form the aerofoil portion. placing the formed aerofoil portion in locating means. the aerofoil portion extending partly from one end at least of the locating means. placing the locating means in a second mould. placing a second mixture of silicon nitride powder and a fluxing agent in a suitably shaped portion of the second mould. the aerofoil portion extending into the second powder mixture. hot pressing the second powder mixture to form the shroud portion and simultaneously to amalgamate the shroud portion with the aerofoil portion.
Generally the bladed member will have two shroud portions and the second mould will therefore have two suitably shaped portions in which the two shroud portions can be formed.
The shroud portion or portions can be partly preformed by hot pressing parts of the or each shroud beforehand and attaching these pre-formed parts to a plunger which is adapted to compress the second powder mixture.
The pre-formed parts may be formed with fixing means which may include features such as. flanges, webs, dowels and apertures so that completed bladed members can be readily secured within a structure such as a gas turbine engine.
Alternatively. the pre-formed parts can be omitted and the plunger may either have a plain face or may be shaped to produce fixing means as above defined in the completed shroud or shrouds.
The invention will now be particularly described with reference to the accompanying drawings in which:
FIG. I shows a plan of one form of mould which can be used for performing the method according to the present invention.
FIGS. 2. 3 and 4 show elevations of the mould shown in FIG. 1 at various stages of performing the method according to the present invention.
The invention will now be initially described with reference to the manufacture of hot pressed dense silicon nitride nozzle guide vanes for use in gas turbine engines.
The nozzle guide vane 2 as shown in FIG. 4 consists of an aerofoil portion 4. a root shroud portion 6 and an outer shroud portion 8.
Referring to the Figs. generally. a mould 10 consists ofa susceptor 12.21 packing ring 14 (FIG. 2) on which the susceptor stands. a split die 16, a locating plunger 18 (FIG. 2) an outer shroud plunger 20. a root shroud plunger 22 and a split aerofoil die 24.
Referring to FIG. 2 particularly. the aerofoil portion 4 is preformed by hot pressing a mixture of silicon nitride powder and magnesium oxide in a suitably shaped die. The pressing is preferably carried out at about L200 psi. and at a temperature of about l.75l) C. This method of forming silicon nitride articles is described in detail in UK. Pat. specification No. 970.369 and use of the mctod produces dense. compact silicon nitride articles ofalmost maximum theoretical density.
The pre-formed portion 4 is placed in the split aerofoil die 24 so that a small portion of the aerofoil extends beyond each end of the die. The die is then placed in a rectangular aperture 26 in the die 16 and is located on a shoulder 28. the lower end of the aerofoil resting on the locating plunger 18.
The space above the aerofoil portion 4 is filled with a mixture of silicon nitride powder and magnesium oxide in the ratio 20 to l by weight. this powder mixture being eventually to form the root shroud portion 6. The amount of powder mixture used depends on the depth ofthe formed root shroud which is required. The root shroud plunger 22 has a preformed root shroud portion 30 lightly attached to it. the portion 30 being of dense silicon nitride and formed by the method de scribed above. The plunger 22 is placed in the aperture and the powder mixture is lightly comptacted at normal temperature.
The mould 10, in the configuration shown in FIG. 3 is placed in a press (not shown) and a pressure of about 1,200 psi. is applied at a temperature of about l.750 C. The powder mixtures above and below the aerofoil densify to form the inner and outer shroud portions 6 and 8 respectively. All the preformed portions 30 and 32 amalgamate with the shroud portions 6 and 8 re spectively and the aerofoil portion 4 amalgamates with the shroud portions. A section taken through the completed nozzle guide vane shows that there is virtually no change in the structure across the boundaries between the pre-formed portions of the vane and the shroud portions which are formed in the final pressing action.
Various modifications of the method described above are possible within the scope of the present invention. The preformed portions of the inner and outer shrouds may be omitted or these pre-formed portions may be formed with fixing means. so that the formed bladed member may be readily attached to the engine structure. Such fixing means typically comprise features such as flanges. webs. apertures and dowels or any combination of these features. Alternatively. the plungers may be formed so that any of these features can be produced on either or both shrouds.
Also the bladed member may be formed with only one of the shroud portions. e.g. the root shourd. in which case. the final configuration of the mould is as shown in FIG. 2.
What I claim is:
l. A method of making a bladed member. the member including an aerofoil section and at least one shroud portion. the method including the steps of hot pressing a first mixture of nitride powder and a fluxing agent in a suitably shaped first mould to form said aerofoil portion placing the formed aerofoil portion in locating means. the aerofoil portion extending partly from one end at least of the locating means. placing the locating means in a second mould. placing a second mixture of silicon nitride powder and fluxing agent in a suitably shaped portion of the second mould, the aerofoil portion extending into said second mixture. hot pressing the second mixture to form the shroud portion and to amalgamate the shroud portion with the aerofoil portion.
2. A method as claimed in claim 1 in which the bladed member has two shroud portions, an inner shroud and an outer shroud portion. the second mould having two suitably shaped portions. the method including the steps of placing pre-determined quantities of said second powder mixture in the two suitably shaped portions of the second mould, hot pressing the second powder mixture to form the inner and outer shroud portions and to amalgamate said shroud portions with the aerofoil portion.
3. A method as claimed in claim 1 in which a portion of at least one of said two shroud portions is pre-formed by hot pressing a mixture of silicon nitride powder and a t'luxing agent in a suitably shaped mould.
4. A method as claimed in claim 3 in which the mould for the pre-formed shroud portion is formed so that the pre-formed shroud portion is formed with fixing means.
5. A method as claimed in claim 1 in which the second powder mixture is lightly compacted at normal temperature prior to hot pressing.

Claims (5)

1. A METHOD OF MAKING A BLADED MEMBER, THE MEMBER INCLUDING AN AEROFOIL SECTION AND AT LEAST ONE SHROUD PORTION, THE METHOD INCLUDING THE STEPS OF HOT PRESSING A FIRST MIXTURE OF NITRIDE POWDER AND A FLUXING AGENT IN A SUITABLY SHAPED FIRST MOULD TO FORM SAID AEROFOIL PORTION PLACING THE FORMED AEROFOIL PORTION IN LOCATING MEANS, THE AEROFOIL PORTION EXTENDING PARTLY FROM ONE END AT LEAST OF THE LOCATING MEANS, PLACING THE LOCATING MEANS IN A SECOND MOULD, PLACING A SECOND MIXTURE OF SILICON NITRIDE POWDER AND FLUXING AGENT IN A SUITABLY SHAPED PORTION OF THE SECOND MOULD, THE AEROFOIL PORTION EXTENDING INTO SAID SECOND MIXTURE, HOT PRESSING THE SECOND MIXTURE TO FORM THE SHROUD PORTION AND TO AMALGAMATE THE SHROUD PORTION WITH THE AEROFOIL PORTION.
2. A method as claimed in claim 1 in which the bladed member has two shroud portions, an inner shroud and an outer shroud portion, the second mould having two suitably shaped portions, the method including the steps of placing pre-determined quantities of said second powder mixture in the two suitably shaped portions of the second mould, hot pressing the second powder mixture to form the inner and outer shroud portions and to amalgamate said shroud portions with the aerofoil portion.
3. A method as claimed in claim 1 in which a portion of at least one of said two shroud portions is pre-formed by hot pressing a mixture of silicon nitride powder and a fluxing agent in a suitably shaped mould.
4. A method as claimed in claim 3 in which the mould for the pre-formed shroud portion is formed so that the pre-formed shroud portion is formed with fixing means.
5. A method as claimed in claim 1 in which the second powder mixture is lightly compacted at normal temperature prior to hot pressing.
US324185A 1972-01-19 1973-01-16 Method for manufacturing bladed members from powder material Expired - Lifetime US3876742A (en)

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US4096120A (en) * 1975-02-02 1978-06-20 Mtu Munchen Gmbh Method of making a ceramic turbine wheel and turbine wheel made thereby
WO2019186144A1 (en) * 2018-03-27 2019-10-03 Intelligent Power Generation Limited Axial out-runner turbine and method for manufacturing a rotor section for that turbine

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US7914454B2 (en) * 2004-06-25 2011-03-29 Wilk Ultrasound Of Canada, Inc. Real-time 3D ultrasonic imaging apparatus and method
US8062014B2 (en) * 2007-11-27 2011-11-22 Kennametal Inc. Method and apparatus using a split case die to press a part and the part produced therefrom
US8033805B2 (en) * 2007-11-27 2011-10-11 Kennametal Inc. Method and apparatus for cross-passageway pressing to produce cutting inserts
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US4004937A (en) * 1972-10-24 1977-01-25 Kabushiki Kaisha Toyota Chuo Kenkyusho Method for producing a sintered silicon nitride base ceramic and said ceramic
US4096120A (en) * 1975-02-02 1978-06-20 Mtu Munchen Gmbh Method of making a ceramic turbine wheel and turbine wheel made thereby
WO2019186144A1 (en) * 2018-03-27 2019-10-03 Intelligent Power Generation Limited Axial out-runner turbine and method for manufacturing a rotor section for that turbine
CN112313393A (en) * 2018-03-27 2021-02-02 智能发电有限公司 Axial flow external rotor turbine and method for manufacturing rotor part of the turbine

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DE2302202A1 (en) 1973-08-16
FR2168485A1 (en) 1973-08-31
DE2302202B2 (en) 1976-09-16
US3972662A (en) 1976-08-03
JPS4883106A (en) 1973-11-06
FR2168485B1 (en) 1976-11-05
GB1359896A (en) 1974-07-17

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