US3474970A - Air assist nozzle - Google Patents

Air assist nozzle Download PDF

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Publication number
US3474970A
US3474970A US623249A US3474970DA US3474970A US 3474970 A US3474970 A US 3474970A US 623249 A US623249 A US 623249A US 3474970D A US3474970D A US 3474970DA US 3474970 A US3474970 A US 3474970A
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United States
Prior art keywords
air
fuel
nozzle
spray
pressure
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Expired - Lifetime
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US623249A
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English (en)
Inventor
Harold C Simmons
Eugene R Hogg
Roy C Kuhn
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Parker Hannifin Corp
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Parker Hannifin Corp
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Publication of US3474970A publication Critical patent/US3474970A/en
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F23D11/107—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet at least one of both being subjected to a swirling motion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11101—Pulverising gas flow impinging on fuel from pre-filming surface, e.g. lip atomizers

Definitions

  • Nozzle for spraying liquids especially fuel for use in aircraft gas turbines and the like.
  • Nozzle is of air assist type characterized by merging of concentric conical air stream and conical fuel sheet at exit oriiice of nozzle.
  • the present invention relates as indicated to a nozzle and particularly to a fuel nozzle of the air assist type for gas turbine and like application.
  • 'Ihe nozzle herein is in the class of liquid spraying devices in which some or all of the energy required to atomize and to disperse the spray is supplied by a second fluid, such as air.
  • a second fluid such as air.
  • Such devices take many forms with a variety of arrangements of liquid and gas passages and the gas pressures which are employed may be as high 4as several hundred pounds per square inch.
  • the present nozzle may be termed a low pressure atomizer because the air pressure required for efiicient atomization ranges only from about 1/2 to 10 p.s.i. which pressure is especially suited for use in aircraft gas turbines in view of the diiiiculty and expense of providing a source of high pressure air especially under high altitude conditions.
  • One disadvantage of known air operated spraying devices is that the spray is concentrated in a stream of relatively small included cone angle, i.e., less than 60, whereas, in combustion applications generally, as well as in other fields of -application such as spray drying, it is necessary to produce sprays having included cone angles of the order of 90 or greater.
  • a known advantage of air atomizing or spraying devices is the capability of atomizing liquids of relatively higher viscosities than can conveniently be atomized by using conventional liquid pressure operated devices.
  • the liquid passage dimensions can be made larger than otherwise required for a given flow rate, and thus the problems of clogging of passages with contaminants is minimized.
  • the invention comprises the features hereinafter fully described and particularly pointed out in the claims, the following description and the annexed drawing setting forth in detail a certain illustrative embodiment of the invention, this being indicative, however, of but one of the various ways in which the principle of the invention may be employed.
  • FIG. l is an elevation view of a fuel nozzle embodying the present invention as mounted on an air-fuel manifold;
  • FIG. 2 is a fragmentary cross-section view on much enlarged scale taken substantially along the line 2-2, FIG. 1;
  • FIG. 3 are comparative graphs of performance characteristics of the present air assist nozzle and a fuel pressure operated nozzle (without air assist).
  • the nozzle 1 herein is mounted in a dual manifold 2 for supplying air and fuel into the respective passages 3 and 4 in the nozzle 1.
  • the nozzle 1 herein shown comprises tubular body and nozzle members 5 and 6 defining therebetween the air passage 3.
  • the nozzle member 6 has, in the fuel passage 4 thereof, a swirl member 7 provided with slots 8 which are disposed at an angle to the axis of the vortex chamber 9 so as to produce a swirling fuel ilow having the general characteristics of a free vortex.
  • the fuel is discharged through the orifice 10 which is coaxial with the vortex chamber 9, the discharge orifice 10 being extended as shown in the direction of fuel Vdischarge in a substantially conical lip 11 terminating in a sharp edge 12.
  • the annular air passage 3 Surrounding the vortex chamber 9 is the annular air passage 3 the inner and outer walls of which converge conically through swirl producing vanes or slots 14 in nozzle member 6 to a minimum diameter and then flares conically outward.
  • the air flow is further guided by the lip 15 which is concentric with the vortex chamber discharge orifice 10 and terminates in the sharp edge 16.
  • the cross-section area for air flow is designed to be continually 4decreasing until the point 17 is reached and this is made as close as is practical to the edge 12 of the fuel dischargetician 10. Accordingly, the highest air velocity is produced at the point 17, and the shape of the surface 15, in conjunction with the use of swirl slots 14 produces an air ow discharge characterized as tending to follow the surface of a cone. It should be noted that the included angles of the lips 11 and 15 are sub'- Stantially the same.
  • a vortex is formed having an air core as shown and the fuel discharges from the orifice 10 as a hollow conical sheet which is constrained to flow along the lip 11 and leave ythe edge 12 as a very thin conical sheet.
  • the thin conical sheet of fuel is immediately acted upon by the high velocity air stream and broken into a supplyfof small dropsl which continue under the combined momentum of the fuel and air streams to follow a substantially conical path until acted upon by other forces such as air turbulence.
  • a further important feature of the present invention is that when a high viscosity fuel is used at relatively low fuel pressure, the fuel issuing from the discharge orifice 10 has insufficient momentum to follow a conical path, but herein the high velocity air as it passes the point 17, acts in effect as a venturi in which, by reason of the lowering of static pressure due to high air velocity, the fuel is sucked outward following lips 11 and 15, and is atomized by the air stream.
  • FIG. 3 shows that the supply cone angle can be maintained by the air assist nozzle 1 down to very low fuel flow rates. In fact, this flow rate is far below the point at which a conventional fuel pressure operated nozzle ceases to produce a recognizably conical discharge.
  • the inlet passage 4 and discharge orifice 10 dimensions can be chosen without regard to the atomizing process. In other words, the dimensions can be maximized and low fuel spray pressures employed.
  • the geometry and sizes of the air flow passage 3 do not appear to be critical until the point 17 is reached and it has been found that the width ofthe air annulus at point 17 should rbe of the same order of magnitude as the dimensions of the fuel inlet slots 8 thus indicating no greater precision to be required in the manufacture of the air passages 3, and 14 than in the parts of the fuel vortex chamber 9.
  • the effectiveness of this nozzle 1 in producing finely atomized sprays is due to the high kinetic energy of the air stream.
  • the kinetic energy of the air can be shown to be about 600 times greater than the fuel.
  • the fuel pressure being no greater than l p.s.i.
  • the atomizing power of the nozzle 1 is similar to that which would be produced by a pressure operated fuel nozzle operating at about 300 p.s.i. fuel pressure.
  • the pressure operated nozzle would have eX- tremely small dimensions and would be very limited in the flow range available without using very high fuel pressures.
  • the cone angle of the spray can readily be changed .by simply changing the angles of the lips 11 and 15 without changing the proportions of the fuel vortex chamber 9 or the internal air passages 3 and 14.
  • the spray cone angle (curve 18) remains substantially constant, i.e., 90 at all fuel liow rates Ibetween 0 and 100 p.p.h.
  • a fuel pressure operated nozzle for a 90 spray cone angle (curve 19) does not attain that spray cone angle until the flow is about 60 p.p.h., the vangle gradually increasing to 90 from about 60 at 25 p.p.h.
  • the curve 20 represents the fuel supply pressure vs. fuel flow rate characteristics of both the nozzle 1 of the present invention and a conventional fuel pressure operated nozzle.
  • the conventional fuel pressure operated nozzle (curve 21) has a useful flow range of about 4:1 with an average droplet size of about 120 microns at 100 p.p.h. with the droplet size increasing to about 220 microns at 25 p.p.h., that being the limit of a usable fuel spray.
  • the present nozzle 1 (curve 23) has a usable flow range of about 100:1, since from a rate of fuel -ffow of just greater than 0 p.p.h. the droplet size ranges from less than 50 microns at such low flow to a maximum of about 140 microns at about 40 p.p.h. flow and then gradually down to about 120 microns tat 100 p.p.h.
  • a spray nozzle comprising a nozzle !body assembly defining therewithin a liquid passage having a vortex chamber to impart a whirling motion to the liquid flowing through -said passage and having an outwardly flared conical discharge orifice through which the liquid is discharged in the form of a hollow cone, and an annular air passage disposed concentrically around said orifice for flow of air to merge with the liquid cone as the latter flows past the end of said discharge orifice thus to break up the liquid into Ia fine conical spray, the wall of said discharge orifice and the inner wall of said air passage converging toward each other, said air passage being of minimum radial cross-section width substantially at the end of said orifice, and the outer wall of said air passage extending radially and axially beyond the end of said discharge orifice thus to form a conical surface havin-g an included angle substantially the same as the included angle of the orifice along which the air stre-am flows to assist in break up of the liquid as it leaves the confines

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Nozzles (AREA)
US623249A 1967-03-15 1967-03-15 Air assist nozzle Expired - Lifetime US3474970A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US62324967A 1967-03-15 1967-03-15

Publications (1)

Publication Number Publication Date
US3474970A true US3474970A (en) 1969-10-28

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Family Applications (1)

Application Number Title Priority Date Filing Date
US623249A Expired - Lifetime US3474970A (en) 1967-03-15 1967-03-15 Air assist nozzle

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Country Link
US (1) US3474970A (enrdf_load_stackoverflow)
BE (1) BE712147A (enrdf_load_stackoverflow)
DE (1) DE1601958A1 (enrdf_load_stackoverflow)
GB (1) GB1188761A (enrdf_load_stackoverflow)

Cited By (36)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2442895A1 (de) * 1973-09-10 1975-03-13 Gen Electric Brennstoffinjektionsvorrichtung
US3972182A (en) * 1973-09-10 1976-08-03 General Electric Company Fuel injection apparatus
US4139157A (en) * 1976-09-02 1979-02-13 Parker-Hannifin Corporation Dual air-blast fuel nozzle
DE2834313A1 (de) * 1977-08-31 1979-03-15 Parker Hannifin Corp Kraftstoffduese
US4185778A (en) * 1978-03-30 1980-01-29 Envirotech Corporation Spray nozzle
US4261517A (en) * 1979-11-23 1981-04-14 General Electric Company Atomizing air metering nozzle
US4280851A (en) * 1979-12-14 1981-07-28 General Foods Corporation Process for cooking or gelatinizing materials
US4558822A (en) * 1982-08-20 1985-12-17 Lechler Gmbh & Co. Kg Binary atomizing nozzle
US4559009A (en) * 1982-08-06 1985-12-17 Hauck Manufacturing Company Aggregate dryer burner
US4941617A (en) * 1988-12-14 1990-07-17 United Technologies Corporation Airblast fuel nozzle
US4974571A (en) * 1989-02-24 1990-12-04 Regents Of The University Of California Pulsed jet combustion generator for non-premixed charge engines
US5423132A (en) * 1992-09-30 1995-06-13 Graber; David A. Dryer apparatus using hot gases in free standing vortex
US5499768A (en) * 1989-05-31 1996-03-19 Ohkawara Kakohki Co., Ltd. Spray nozzle unit
US5513798A (en) * 1993-08-08 1996-05-07 Tavor; Elhanan Atomizer
US5697553A (en) * 1995-03-03 1997-12-16 Parker-Hannifin Corporation Streaked spray nozzle for enhanced air/fuel mixing
US6076745A (en) * 1997-05-01 2000-06-20 Haldor Topsoe A/S Swirling-flow burner
US6363726B1 (en) 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
US6367262B1 (en) 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6381964B1 (en) 2000-09-29 2002-05-07 General Electric Company Multiple annular combustion chamber swirler having atomizing pilot
US6418726B1 (en) 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
WO2002073089A1 (en) * 2001-03-07 2002-09-19 Delavan Inc Air assist fuel nozzle
US6460344B1 (en) 1999-05-07 2002-10-08 Parker-Hannifin Corporation Fuel atomization method for turbine combustion engines having aerodynamic turning vanes
US6474071B1 (en) 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US6484489B1 (en) 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US20030196440A1 (en) * 1999-05-07 2003-10-23 Erlendur Steinthorsson Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6698208B2 (en) 2001-12-14 2004-03-02 Elliott Energy Systems, Inc. Atomizer for a combustor
US20060272332A1 (en) * 2005-06-03 2006-12-07 Siemens Westinghouse Power Corporation System for introducing fuel to a fluid flow upstream of a combustion area
JP2007517181A (ja) * 2003-12-24 2007-06-28 プラット　アンド　ホイットニー　カナダ　コーポレイション 螺旋形通路燃料分配器および方法
US20090100837A1 (en) * 2007-10-18 2009-04-23 Ralf Sebastian Von Der Bank Lean premix burner for a gas-turbine engine
JP2010522864A (ja) * 2007-03-26 2010-07-08 サン−ゴバン アンバラージュ 液体燃料用中空噴流噴射器噴流噴射器
US20110175244A1 (en) * 2008-10-01 2011-07-21 Fluor Technologies Corporation Configurations and Methods of Gas-Assisted Spray Nozzles
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160281991A1 (en) * 2013-03-19 2016-09-29 Snecma Injection system for a combustion chamber of a turbine engine, comprising an annular wall having a convergent inner cross-section
US10830445B2 (en) * 2015-12-30 2020-11-10 General Electric Company Liquid fuel nozzles for dual fuel combustors

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3684186A (en) * 1970-06-26 1972-08-15 Ex Cell O Corp Aerating fuel nozzle
SE421952B (sv) * 1978-07-31 1982-02-08 Scaniainventor Ab Brennare for en suspension av finkorningt kol i vetska
US4404931A (en) 1978-11-13 1983-09-20 Cummins Engine Company, Inc. Stable fuel burner for preheating intake air of internal combustion engine
US4505665A (en) * 1980-02-19 1985-03-19 Southern California Edison Method and burner tip for suspressing emissions of nitrogen oxides
US4618323A (en) * 1980-02-19 1986-10-21 Southers California Edison Method and burner tip for suppressing emissions of nitrogen oxides
GB9420375D0 (en) * 1994-10-10 1994-11-23 Itw Ltd An improved nozzle and aircap for spray guns
FR2772118B1 (fr) * 1997-12-05 2001-08-17 Saint Gobain Vitrage Procede de combustion et bruleur a pulverisation de combustible mettant en oeuvre un tel procede
DE102011120717A1 (de) * 2011-12-12 2013-06-13 Sm-Klebetechnik Vertriebs Gmbh Düse

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2566788A (en) * 1949-05-21 1951-09-04 Wright Aeronautical Corp Air assisted fuel nozzle
US2595759A (en) * 1948-11-30 1952-05-06 Gen Electric Atomizing nozzle for spraying viscous liquids
US2643916A (en) * 1949-04-25 1953-06-30 Braun & Co C F Fuel burner
US2703260A (en) * 1951-07-07 1955-03-01 Delavan Mfg Company Dual orifice atomizing nozzle
US3013732A (en) * 1959-09-01 1961-12-19 Parker Hannifin Corp Fuel injection nozzle
US3346412A (en) * 1963-09-04 1967-10-10 Fur Firestone Produckte Ag Fab Tire coating apparatus

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2595759A (en) * 1948-11-30 1952-05-06 Gen Electric Atomizing nozzle for spraying viscous liquids
US2643916A (en) * 1949-04-25 1953-06-30 Braun & Co C F Fuel burner
US2566788A (en) * 1949-05-21 1951-09-04 Wright Aeronautical Corp Air assisted fuel nozzle
US2703260A (en) * 1951-07-07 1955-03-01 Delavan Mfg Company Dual orifice atomizing nozzle
US3013732A (en) * 1959-09-01 1961-12-19 Parker Hannifin Corp Fuel injection nozzle
US3346412A (en) * 1963-09-04 1967-10-10 Fur Firestone Produckte Ag Fab Tire coating apparatus

Cited By (48)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE2442895A1 (de) * 1973-09-10 1975-03-13 Gen Electric Brennstoffinjektionsvorrichtung
US3946552A (en) * 1973-09-10 1976-03-30 General Electric Company Fuel injection apparatus
US3972182A (en) * 1973-09-10 1976-08-03 General Electric Company Fuel injection apparatus
US4139157A (en) * 1976-09-02 1979-02-13 Parker-Hannifin Corporation Dual air-blast fuel nozzle
DE2834313A1 (de) * 1977-08-31 1979-03-15 Parker Hannifin Corp Kraftstoffduese
US4168803A (en) * 1977-08-31 1979-09-25 Parker-Hannifin Corporation Air-ejector assisted fuel nozzle
US4185778A (en) * 1978-03-30 1980-01-29 Envirotech Corporation Spray nozzle
US4261517A (en) * 1979-11-23 1981-04-14 General Electric Company Atomizing air metering nozzle
US4280851A (en) * 1979-12-14 1981-07-28 General Foods Corporation Process for cooking or gelatinizing materials
US4559009A (en) * 1982-08-06 1985-12-17 Hauck Manufacturing Company Aggregate dryer burner
US4558822A (en) * 1982-08-20 1985-12-17 Lechler Gmbh & Co. Kg Binary atomizing nozzle
US4941617A (en) * 1988-12-14 1990-07-17 United Technologies Corporation Airblast fuel nozzle
US4974571A (en) * 1989-02-24 1990-12-04 Regents Of The University Of California Pulsed jet combustion generator for non-premixed charge engines
US5499768A (en) * 1989-05-31 1996-03-19 Ohkawara Kakohki Co., Ltd. Spray nozzle unit
US5423132A (en) * 1992-09-30 1995-06-13 Graber; David A. Dryer apparatus using hot gases in free standing vortex
US5513798A (en) * 1993-08-08 1996-05-07 Tavor; Elhanan Atomizer
US5697553A (en) * 1995-03-03 1997-12-16 Parker-Hannifin Corporation Streaked spray nozzle for enhanced air/fuel mixing
US6076745A (en) * 1997-05-01 2000-06-20 Haldor Topsoe A/S Swirling-flow burner
US6460344B1 (en) 1999-05-07 2002-10-08 Parker-Hannifin Corporation Fuel atomization method for turbine combustion engines having aerodynamic turning vanes
US6883332B2 (en) 1999-05-07 2005-04-26 Parker-Hannifin Corporation Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US20030196440A1 (en) * 1999-05-07 2003-10-23 Erlendur Steinthorsson Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6560964B2 (en) 1999-05-07 2003-05-13 Parker-Hannifin Corporation Fuel nozzle for turbine combustion engines having aerodynamic turning vanes
US6474071B1 (en) 2000-09-29 2002-11-05 General Electric Company Multiple injector combustor
US6363726B1 (en) 2000-09-29 2002-04-02 General Electric Company Mixer having multiple swirlers
US6367262B1 (en) 2000-09-29 2002-04-09 General Electric Company Multiple annular swirler
US6609377B2 (en) 2000-09-29 2003-08-26 General Electric Company Multiple injector combustor
US6381964B1 (en) 2000-09-29 2002-05-07 General Electric Company Multiple annular combustion chamber swirler having atomizing pilot
US6688534B2 (en) 2001-03-07 2004-02-10 Delavan Inc Air assist fuel nozzle
US20040139750A1 (en) * 2001-03-07 2004-07-22 Bretz David H. Air assist fuel nozzle
WO2002073089A1 (en) * 2001-03-07 2002-09-19 Delavan Inc Air assist fuel nozzle
US6484489B1 (en) 2001-05-31 2002-11-26 General Electric Company Method and apparatus for mixing fuel to decrease combustor emissions
US6418726B1 (en) 2001-05-31 2002-07-16 General Electric Company Method and apparatus for controlling combustor emissions
US6698208B2 (en) 2001-12-14 2004-03-02 Elliott Energy Systems, Inc. Atomizer for a combustor
JP2007517181A (ja) * 2003-12-24 2007-06-28 プラット　アンド　ホイットニー　カナダ　コーポレイション 螺旋形通路燃料分配器および方法
EP1706671A4 (en) * 2003-12-24 2009-07-29 Pratt & Whitney Canada Corp Pr FUEL DISTRIBUTORS WITH SCREW-TYPE CHANNELS AND METHOD
US7810336B2 (en) 2005-06-03 2010-10-12 Siemens Energy, Inc. System for introducing fuel to a fluid flow upstream of a combustion area
US20060272332A1 (en) * 2005-06-03 2006-12-07 Siemens Westinghouse Power Corporation System for introducing fuel to a fluid flow upstream of a combustion area
JP2010522864A (ja) * 2007-03-26 2010-07-08 サン−ゴバン アンバラージュ 液体燃料用中空噴流噴射器噴流噴射器
US20090100837A1 (en) * 2007-10-18 2009-04-23 Ralf Sebastian Von Der Bank Lean premix burner for a gas-turbine engine
US8910483B2 (en) * 2007-10-18 2014-12-16 Rolls-Royce Deutschland Ltd & C Lean premix burner for a gas-turbine engine
US20110175244A1 (en) * 2008-10-01 2011-07-21 Fluor Technologies Corporation Configurations and Methods of Gas-Assisted Spray Nozzles
US8616533B2 (en) 2008-10-01 2013-12-31 Fluor Technologies Corporation Configurations and methods of gas-assisted spray nozzles
US8893500B2 (en) 2011-05-18 2014-11-25 Solar Turbines Inc. Lean direct fuel injector
US8919132B2 (en) 2011-05-18 2014-12-30 Solar Turbines Inc. Method of operating a gas turbine engine
US9182124B2 (en) 2011-12-15 2015-11-10 Solar Turbines Incorporated Gas turbine and fuel injector for the same
US20160281991A1 (en) * 2013-03-19 2016-09-29 Snecma Injection system for a combustion chamber of a turbine engine, comprising an annular wall having a convergent inner cross-section
US10036552B2 (en) * 2013-03-19 2018-07-31 Snecma Injection system for a combustion chamber of a turbine engine, comprising an annular wall having a convergent inner cross-section
US10830445B2 (en) * 2015-12-30 2020-11-10 General Electric Company Liquid fuel nozzles for dual fuel combustors

Also Published As

Publication number Publication date
GB1188761A (en) 1970-04-22
BE712147A (enrdf_load_stackoverflow) 1968-09-16
DE1601958B2 (enrdf_load_stackoverflow) 1979-06-13
DE1601958A1 (de) 1971-03-04

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