US3794444A - Anti-icing spinner construction - Google Patents

Anti-icing spinner construction Download PDF

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US3794444A
US3794444A US00186074A US3794444DA US3794444A US 3794444 A US3794444 A US 3794444A US 00186074 A US00186074 A US 00186074A US 3794444D A US3794444D A US 3794444DA US 3794444 A US3794444 A US 3794444A
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fins
spinner
ice
external surface
shape
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US00186074A
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W Campbell
A Adamson
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General Electric Co
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General Electric Co
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    • 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
    • F01D25/02—De-icing means for engines having icing phenomena
    • 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

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  • ABSTRACT A spinner construction for maintaining ice accumulation thereon to an acceptably low level during operation of a gas turbine engine under icing conditions wherein a plurality of spaced fins extend from the arcuate outer surface of the spinner.
  • the fins are sized and arranged relative to impinging water droplets so that ice formation occurs principally on the fins rather than the spinner arcuate outer surface.
  • ice may accumulate on the rotating spinner or bullet nose of the type used in aircraft gas turbine engines.
  • the spinner ice build-up is non-uniform it may cause excessive engine vibration.
  • the ice build-up is shed in large pieces, it may cause damage to rotating or stationary components of the turbomachine.
  • One method which has been heretofore frequently used to avoid excessive ice build-up on turbomachinery spinners involves heating the exposed spinner surfaces to a temperature such that ice accumulation is prevented or to a temperature sufficient to weaken the ice/spinner bond such that the ice is shed by centrifugal action before the ice build-up becomes excessive. While such methods have been found effective in preventing excessive accumulation, they generally require the propulsion system to provide electrical energy or hot air or gases which tend to reduce the propulsion systems efficiency and reliability while increasing its weight, complexity and initial and maintenance costs.
  • a primary object of the present invention is to provide a rotating spinner construction which is geometrically configured such that ice will be automatically shed therefrom.
  • Another object of this invention is to provide a rotating spinner construction for a gas turbine engine which is geometrically configured so as to shed ice in the form of relatively small pieces.
  • Yet another object of this invention is a spinner construction which reduces ice accumulation to an acceptably low level during operation of a gas tubine engine under icing conditions.
  • the spinner with a plurality of fins or ribs which project generally radially outwardly from the arcuate external surface of the spinner.
  • the fins are preferably sized and oriented on the spinner in relation to the impinging airflow such that the fins shield or shadow the adjacent arcuate outer spinner surface from the impinging airflow.
  • FIG. 1 is a partial perspective view of a gas turbing engine employing the rotating spinner construction of this invention
  • FIG. 2 is a partial plan view, drawn to an enlarged scale, taken along lines 2-2 of FIG. 1;
  • the upstream end of the rotor 16 terminates in a bullet nose or spinner 18 which is formed with an arcuate outer surface 20 which converges to a nose at its upstream end 22.
  • the spinner is formed with a plurality of spaced fins or ribs 24 which extend generally radially outwardly from the spinner outer surface 20.
  • Each fin 24 has been shown in FIG. 2 as being generally spiral-like in shape as it progresses from the upstream to the downstream end of the spinner such that the approaching air velocity, relative to the spinner, is at an incidence angle such that the portion of the spinner outer surface 20 between the fins 24 is shadowed from the impinging airflow and, hence, from the water droplets carried by the impinging air.
  • FIG. 3 Such preferred arrangement is diagrammatically shown in FIG. 3 wherein the relative direction of impinging air is indicated at 26, the resultant angle of attack relative to the spinner is indicated at 28, and the resultant ice build-up on the fins during icing conditions is indicated at 30.
  • each fin 24 may be maintained constant over the length of the fin or may be varied, depending upon number of fins employed and the spacing of adjacent fins. For aerodynamic reasons, however, it is preferred that each fin 24 be of small radial height relative to the diameter of the spinner and that the angle of the fin at its downstream end, relative to the rotational axis 32 approximates the angle of the axially adjacent blades 16 as best shown in FIG. 2.
  • One factor that contributes to the improved ice shedding characteristics'of the present spinner construction is that the fin surface area upon which ice formation will occur may be greatly reduced as compared to the spinner area upon which ice formation would occur in the case of a conventional spinner.
  • fins 24 have been depicted and described as being generally spiral in shape it will be understood that they may be circular or otherwise suitably shaped, it being important only that they be oriented relative to the impinging water droplets so as to shield or shadow the adjacent spinner external surface therefrom.
  • the present invention provides improved spinner ice shedding characteristics while avoiding the system disadvantages which attend spinnerheating arrangements.
  • a fluid apparatus of the gas turbine engine type including a rotating spinner disposed within a circumscribing duct and having an arcuate external surface upon which liquid droplets may be impinged under icing conditions, means for improving the ice shedding characteristics of said spinner comprising:
  • said fluid apparatus includes a circumferential row of blades adjacent the downstream end of said spinner, said fins being generally spiral in shape and extending axially over a portion of said spinner external surface to its downstream end, said fins forming an angle relative to the spinner rotational axis at said downstream end which is approximately equal to the angle of said blades.

Abstract

A spinner construction for maintaining ice accumulation thereon to an acceptably low level during operation of a gas turbine engine under icing conditions wherein a plurality of spaced fins extend from the arcuate outer surface of the spinner. The fins are sized and arranged relative to impinging water droplets so that ice formation occurs principally on the fins rather than the spinner arcuate outer surface.

Description

United States Patent 1191 Campbell et a1.
ANTI-ICING SPINNER CONSTRUCTION Inventors: William B. Campbell; Arthur P,
Adamson, both of Cincinnati, Ohio Assignee: General Electric Company, Cincinnati, Ohio Filed: Oct. 4, 1971 Appl. No.: 186,074
US. Cl 416/201, 416/245, 415/143 Int. Cl. B64c 11/1 Field of Search... 416/201, 245, 175, 203, 124, 416/94,177,176,198, 200;415/DIG. 1,121 A, 143, 168
References Cited 7 UNlTED STATES PATENTS 9/1931 Grumpelt 4-16/175 [451 Feb. 26, 1974 1,920,880 8/1933 Parker 416/175 2,260,786 10/1941 Muhlenbruck 416/201 I 2,755,868 7/1956 Smith 416/245 X Quan 416/245 UX Primary ExaminerEverette A. Powell, Jr.
Attorney, Agent, or Firm-James M. Kipling; Derek P.
Lawrence 5 7] ABSTRACT A spinner construction for maintaining ice accumulation thereon to an acceptably low level during operation of a gas turbine engine under icing conditions wherein a plurality of spaced fins extend from the arcuate outer surface of the spinner. The fins are sized and arranged relative to impinging water droplets so that ice formation occurs principally on the fins rather than the spinner arcuate outer surface.
7 Claims, 3 Drawing Figures ANTI-ICING SPINNER CONSTRUCTION This invention relates to turbomachinery and, more.
particularly, to a spinner construction which mitigates ice build-up by enhancing the ice shedding characteristics of the spinner.
During aircraft flight through icing conditions, ice may accumulate on the rotating spinner or bullet nose of the type used in aircraft gas turbine engines. In such applications, due to the high rotational speed of the spinner, if the spinner ice build-up is non-uniform it may cause excessive engine vibration. On the other hand, if the ice build-up is shed in large pieces, it may cause damage to rotating or stationary components of the turbomachine.
One method which has been heretofore frequently used to avoid excessive ice build-up on turbomachinery spinners involves heating the exposed spinner surfaces to a temperature such that ice accumulation is prevented or to a temperature sufficient to weaken the ice/spinner bond such that the ice is shed by centrifugal action before the ice build-up becomes excessive. While such methods have been found effective in preventing excessive accumulation, they generally require the propulsion system to provide electrical energy or hot air or gases which tend to reduce the propulsion systems efficiency and reliability while increasing its weight, complexity and initial and maintenance costs.
A primary object of the present invention is to provide a rotating spinner construction which is geometrically configured such that ice will be automatically shed therefrom.
Another object of this invention is to provide a rotating spinner construction for a gas turbine engine which is geometrically configured so as to shed ice in the form of relatively small pieces.
Yet another object of this invention is a spinner construction which reduces ice accumulation to an acceptably low level during operation of a gas tubine engine under icing conditions.
Briefly, these and other objects, which will become apparent upon reading hereinafter, are achieved in the present invention by forming the spinner with a plurality of fins or ribs which project generally radially outwardly from the arcuate external surface of the spinner. The fins are preferably sized and oriented on the spinner in relation to the impinging airflow such that the fins shield or shadow the adjacent arcuate outer spinner surface from the impinging airflow. In this manner, most or all of the water droplets carried by the air which would otherwise impinge on the spinner outer arcuate surface, impinge instaad on the fins. Where such impingement occurs during icing conditions, ice forms primarily on the fins where it is centrifuged off in small pieces before build-up becomes excessive.
While the specification concludes with claims particularly pointing out and distinctly claiming the subject matter of this invention, it is believed that the invention will be better understood upon reading the following specification in conjunction with the accompanying drawings, wherein:
FIG. 1 is a partial perspective view of a gas turbing engine employing the rotating spinner construction of this invention;
FIG. 2 is a partial plan view, drawn to an enlarged scale, taken along lines 2-2 of FIG. 1; and
rality of radially extending blades 16 for pressurizing airflow through the duct 10.
The upstream end of the rotor 16 terminates in a bullet nose or spinner 18 which is formed with an arcuate outer surface 20 which converges to a nose at its upstream end 22.
,In order to mitigate ice build-up on the spinner 18 to an acceptably low level during operation of the engine under icing conditions, and in accordance with the present invention, the spinner is formed with a plurality of spaced fins or ribs 24 which extend generally radially outwardly from the spinner outer surface 20.
Each fin 24 has been shown in FIG. 2 as being generally spiral-like in shape as it progresses from the upstream to the downstream end of the spinner such that the approaching air velocity, relative to the spinner, is at an incidence angle such that the portion of the spinner outer surface 20 between the fins 24 is shadowed from the impinging airflow and, hence, from the water droplets carried by the impinging air. Such preferred arrangement is diagrammatically shown in FIG. 3 wherein the relative direction of impinging air is indicated at 26, the resultant angle of attack relative to the spinner is indicated at 28, and the resultant ice build-up on the fins during icing conditions is indicated at 30. The radial height of each fin 24 may be maintained constant over the length of the fin or may be varied, depending upon number of fins employed and the spacing of adjacent fins. For aerodynamic reasons, however, it is preferred that each fin 24 be of small radial height relative to the diameter of the spinner and that the angle of the fin at its downstream end, relative to the rotational axis 32 approximates the angle of the axially adjacent blades 16 as best shown in FIG. 2.
With the spinner geometry of this invention, it has been found that ice will shed from the fins 24 at a rate which maintains the total ice accumulation on the spinner 18 to an acceptably low level and, additionally, that the ice is shed in small pieces which may be digested by the fan 12 without damage. These improved ice shedding characteristics, which have been observed in testing, are believed to result from an increase in the stress levels of the ice/fin bond as compared to the stresses that would be expected in the bond between a conventional spinner external surface and the ice formed thereon.
One factor that contributes to the improved ice shedding characteristics'of the present spinner construction is that the fin surface area upon which ice formation will occur may be greatly reduced as compared to the spinner area upon which ice formation would occur in the case of a conventional spinner.
Accordingly, assuming that ice will shed at the same build-up thickness for either the finned spinner of this invention or from a conventional unfinned spinner of similar size and shape which is operating at the same rotating speed, it will be apparent that the total mass of ice accumulated on the reduced fin area will be less than that accumulated on the larger ice forming area of the conventional spinner.
the ice, while in the conventional or unfinned spinner the bond is subjected primarily to tensile forces only.
While the fins 24 have been depicted and described as being generally spiral in shape it will be understood that they may be circular or otherwise suitably shaped, it being important only that they be oriented relative to the impinging water droplets so as to shield or shadow the adjacent spinner external surface therefrom.
From the foregoing, it will be apparent that the present invention provides improved spinner ice shedding characteristics while avoiding the system disadvantages which attend spinnerheating arrangements.
While a particular embodiment of the present invention has been depicted and described, such is intended to be exemplary only and not definitive and it will be understood by those skilled in the art that many modifications, substitutions and changes may be made thereto without departing from the fundamental theme of the invention.
What is claimed is:
1. Means for improving the ice shedding characteristics of a rotating spinner of the type used in gas turbine engines and having an arcuate external surface disposed within a circumscribing duct and, said means comprising a plurality of fins projecting generally radially from said arcuate external surface, said fins being spaced, sized in radial height and oriented relative to the spinner rotational axis such that liquid droplets carried by air which would otherwise impinge on said arcuate external spinner surface in the area of said fins impinge instead of said fins.
2. The structure of claim 1 further characterized in that said fins are generally spiral in shape.
3. The structure of claim 1 further characterized in that said fins are generally circular in shape.
4. In a fluid apparatus of the gas turbine engine type including a rotating spinner disposed within a circumscribing duct and having an arcuate external surface upon which liquid droplets may be impinged under icing conditions, means for improving the ice shedding characteristics of said spinner comprising:
a plurality of spaced fins projecting generally radially from said spinner external surface, with the radial height and spacing of said fins being sized relative to the incidence angle of said impinging liquid droplets such that, in the area of said fins, liquid impingement and, hence, ice formation occurs primarily on said fins.
5. The structure of claim 4 further characterized in that said fins are generally spiral in shape.
6. The structure of claim 4 further characterized in that said fins are generally circular in shape.
7. The structure of claim 4 further characterized in that said fluid apparatus includes a circumferential row of blades adjacent the downstream end of said spinner, said fins being generally spiral in shape and extending axially over a portion of said spinner external surface to its downstream end, said fins forming an angle relative to the spinner rotational axis at said downstream end which is approximately equal to the angle of said blades.

Claims (7)

1. Means for improving the ice shedding characteristics of a rotating spinner of the type used in gas turbine engines and having an arcuate external surface disposed within a circumscribing duct and, said means comprising a plurality of fins projecting generally radially from said arcuate external surface, said fins being spaced, sized in radial height and oriented relative to the spinner rotational axis such that liquid droplets carried by air which would otherwise impinge on said arcuate external spinner surface in the area of said fins impinge instead of said fins.
2. The structure of claim 1 further characterized in that said fins are generally spiral in shape.
3. The structure of claim 1 further characterized in that said fins are generally circular in shape.
4. In a fluid apparatus of the gas turbine engine type including a rotating spinner disposed within a circumscribing duct and having an arcuate external surface upon which liquid droplets may be impinged under icing conditions, means for improving the ice shedding characteristics of said spinner comprising: a plurality of spaced fins projecting generally radially from said spinner external surface, with the radial height and spacing of said fins being sized relative to the incidence angle of said impinging liquid droplets such that, in the area of said fins, liquid impingement and, hence, ice formation occurs primarily on said fins.
5. The structure of claim 4 further characterized in that said fins are generally spiral in shape.
6. The structure of claim 4 further characterized in that said fins are generally circular in shape.
7. The structure of claim 4 further characterized in that said fluid apparatus includes a circumferential row of blades adjacent the downstream end of said spinner, said fins being generally spiral in shape and extending axially over a portion of said spinner external surface to its downstream end, said fins forming an angle relative to the spinner rotational axis at said downstream end which is approximately equal to the angle of said blades.
US00186074A 1971-10-04 1971-10-04 Anti-icing spinner construction Expired - Lifetime US3794444A (en)

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IT (1) IT968432B (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2194295A (en) * 1986-07-31 1988-03-02 Mitsui O S K Lines Ltd Screw propeller boss cap
GB2369161A (en) * 2000-11-20 2002-05-22 Ajoy Kumar Kundu Spinner for a propeller
US20080000216A1 (en) * 2006-06-28 2008-01-03 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US20090016870A1 (en) * 2005-01-26 2009-01-15 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US20090272095A1 (en) * 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
US20090272850A1 (en) * 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
US20090304518A1 (en) * 2006-07-04 2009-12-10 Ihi Corporation Turbofan engine
US20120036826A1 (en) * 2009-03-13 2012-02-16 Sagem Defense Securite Engine and pod assembly for an aircraft, equipped with an anti-icing device
EP2476617A1 (en) * 2011-01-14 2012-07-18 Sikorsky Aircraft Corporation Passive control of ice shedding
US10371051B2 (en) 2013-03-01 2019-08-06 United Technologies Corporation Gas turbine engine noise reducing nose cone
EP3597928A1 (en) * 2018-07-16 2020-01-22 Rolls-Royce plc Fan unit for a turbofan engine comprising vortex-generating elements
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US11492923B2 (en) * 2018-04-09 2022-11-08 Gulfstream Aerospace Corporation Ice shedding aircraft engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1524908A (en) * 1976-06-01 1978-09-13 Rolls Royce Gas turbine engine with anti-icing facility
JPH07108486B2 (en) * 1987-02-09 1995-11-22 静岡製機株式会社 Finishing method and device by electrolytic processing
DE602007003971D1 (en) * 2007-07-09 2010-02-04 Agusta Spa Apparatus and method for protecting an aircraft component from collisions with flying objects
JP5510149B2 (en) * 2010-07-23 2014-06-04 株式会社Ｉｈｉ Gas turbine engine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1824667A (en) * 1926-07-20 1931-09-22 Syndicat Vaproc Rotary propeller
US1920880A (en) * 1932-01-13 1933-08-01 Parker Elgia Lawerence Propeller construction
US2260786A (en) * 1940-05-28 1941-10-28 Roy F Muhlenbruck Attachment for propellers
US2755868A (en) * 1953-09-17 1956-07-24 United Aircraft Corp Spinner construction for an aeronautical propeller
US2997229A (en) * 1959-10-06 1961-08-22 Means for removing moisture from a surface

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1824667A (en) * 1926-07-20 1931-09-22 Syndicat Vaproc Rotary propeller
US1920880A (en) * 1932-01-13 1933-08-01 Parker Elgia Lawerence Propeller construction
US2260786A (en) * 1940-05-28 1941-10-28 Roy F Muhlenbruck Attachment for propellers
US2755868A (en) * 1953-09-17 1956-07-24 United Aircraft Corp Spinner construction for an aeronautical propeller
US2997229A (en) * 1959-10-06 1961-08-22 Means for removing moisture from a surface

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
AU593670B2 (en) * 1986-07-31 1990-02-15 Mikado Propeller Co., Ltd. A screw propeller boss cap with fins
GB2194295B (en) * 1986-07-31 1991-03-20 Mitsui O S K Lines Ltd A screw propeller
GB2194295A (en) * 1986-07-31 1988-03-02 Mitsui O S K Lines Ltd Screw propeller boss cap
GB2369161A (en) * 2000-11-20 2002-05-22 Ajoy Kumar Kundu Spinner for a propeller
GB2369161B (en) * 2000-11-20 2004-11-10 Ajoy Kumar Kundu Spinner for a propeller
US20090016870A1 (en) * 2005-01-26 2009-01-15 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US7748950B2 (en) * 2005-01-26 2010-07-06 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US7721526B2 (en) 2006-06-28 2010-05-25 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US20080000216A1 (en) * 2006-06-28 2008-01-03 Ishikawajima-Harima Heavy Industries Co., Ltd. Turbofan engine
US8579592B2 (en) 2006-07-04 2013-11-12 Ihi Corporation Turbofan engine
US20090304518A1 (en) * 2006-07-04 2009-12-10 Ihi Corporation Turbofan engine
WO2009142793A3 (en) * 2008-04-30 2010-06-17 General Electric Company Ice shed reduction for leading edge structures
US8245981B2 (en) 2008-04-30 2012-08-21 General Electric Company Ice shed reduction for leading edge structures
US20090272850A1 (en) * 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
GB2471614A (en) * 2008-04-30 2011-01-05 Gen Electric Ice shed reduction for leading edge structures
US7992823B2 (en) 2008-04-30 2011-08-09 General Electric Company Ice shed reduction for leading edge structures
US20090272095A1 (en) * 2008-04-30 2009-11-05 General Electric Company Ice shed reduction for leading edge structures
GB2471614B (en) * 2008-04-30 2012-09-26 Gen Electric Ice shed reduction for leading edge structures
WO2009142793A2 (en) * 2008-04-30 2009-11-26 General Electric Company Ice shed reduction for leading edge structures
US20120036826A1 (en) * 2009-03-13 2012-02-16 Sagem Defense Securite Engine and pod assembly for an aircraft, equipped with an anti-icing device
US8997451B2 (en) * 2009-03-13 2015-04-07 Sagem Defense Securite Engine and pod assembly for an aircraft, equipped with an anti-icing device including a source of radiation and pulse control unit connected to the source of radiation
EP2476617A1 (en) * 2011-01-14 2012-07-18 Sikorsky Aircraft Corporation Passive control of ice shedding
US8770512B2 (en) 2011-01-14 2014-07-08 Sikorsky Aircraft Corporation Passive control of ice shedding
US10371051B2 (en) 2013-03-01 2019-08-06 United Technologies Corporation Gas turbine engine noise reducing nose cone
US10670037B2 (en) * 2017-11-21 2020-06-02 General Electric Company Turbofan engine's fan blade and setting method thereof
US11492923B2 (en) * 2018-04-09 2022-11-08 Gulfstream Aerospace Corporation Ice shedding aircraft engine
EP3597928A1 (en) * 2018-07-16 2020-01-22 Rolls-Royce plc Fan unit for a turbofan engine comprising vortex-generating elements

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DE2248142A1 (en) 1973-04-12
BE789482A (en) 1973-01-15
IT968432B (en) 1974-03-20
FR2156630A1 (en) 1973-06-01
JPS4844613A (en) 1973-06-27
FR2156630B1 (en) 1976-08-13
GB1407444A (en) 1975-09-24

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