US3826088A - Gas turbine engine augmenter cooling liner stabilizers and supports - Google Patents

Gas turbine engine augmenter cooling liner stabilizers and supports Download PDF

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Publication number
US3826088A
US3826088A US00328769A US32876973A US3826088A US 3826088 A US3826088 A US 3826088A US 00328769 A US00328769 A US 00328769A US 32876973 A US32876973 A US 32876973A US 3826088 A US3826088 A US 3826088A
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US
United States
Prior art keywords
liner
band
stabilizer
gas turbine
turbine engine
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
US00328769A
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English (en)
Inventor
D Nash
C Lyons
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Priority to US00328769A priority Critical patent/US3826088A/en
Priority to GB333274A priority patent/GB1454614A/en
Priority to IT19763/74A priority patent/IT1007066B/it
Priority to DE2404040A priority patent/DE2404040C2/de
Priority to CA191,320A priority patent/CA995015A/en
Priority to FR7403305A priority patent/FR2216450B1/fr
Priority to BE140448A priority patent/BE810491A/fr
Priority to JP49012881A priority patent/JPS5920861B2/ja
Application granted granted Critical
Publication of US3826088A publication Critical patent/US3826088A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • C—CHEMISTRY; METALLURGY
    • C07—ORGANIC CHEMISTRY
    • C07D—HETEROCYCLIC COMPOUNDS
    • C07D277/00—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings
    • C07D277/02—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings
    • C07D277/20—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings having two or three double bonds between ring members or between ring members and non-ring members
    • C07D277/587—Heterocyclic compounds containing 1,3-thiazole or hydrogenated 1,3-thiazole rings not condensed with other rings having two or three double bonds between ring members or between ring members and non-ring members with aliphatic hydrocarbon radicals substituted by carbon atoms having three bonds to hetero atoms with at the most one bond to halogen, e.g. ester or nitrile radicals, directly attached to ring carbon atoms, said aliphatic radicals being substituted in the alpha-position to the ring by a hetero atom, e.g. with m >= 0, Z being a singly or a doubly bound hetero atom
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78—Other construction of jet pipes
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/822—Heat insulating structures or liners, cooling arrangements, e.g. post combustion liners; Infrared radiation suppressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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

  • a stabilizing and support system for an augmenter cooling liner of a gas turbine engine isshown to in-' clude a plurality of stabilizers circumferentially spaced around, and mounted to, the liner.
  • Each of the stabilizers is captured on its outer end by a stabilizer guide which permits relative thermal expansion to take place between the cooling liner and the exhaust duct to which the liner is mounted.
  • the stabilizer guides are mounted to a positioning band which, in turn, mounts V to the inside of the exhaust duct.
  • the positioning band is provided with a gap'which permits the band'and stabilizer guides to flex to a diameter smaller than the internal diameter of the exhaust duct to permit easy assembly of the liner into the exhaust duct;
  • This invention relates generally to augmented gas turbine engines and, more particularly, to means for supporting and stabilizing cooling liners associated with an augmented turbofan engine.
  • Gas turbine engines generally comprise a compressor for compressing air flowing through the engine, a combustion system in which high energy fuel is mixed with the compressed air and ignited to form a high energy gas stream, and a turbine which includes a rotor portion operatively connected to the compressor to drive the same.
  • Many modem-day gas turbine engines are of the turbofan type in which a second or low pressure compressor is mounted forwardly of the high pressure compressor and is driven by a second turbine mounted downstream of the first turbine.
  • the low pressure compressor or fan presents an additional stage of compres-' sion and, in addition, is normally of a greater diameter than the high pressure compressor.
  • the turbofan engine is therefore capable of flowing a much larger mass of air, thereby greatly increasing the thrust output of the engine.
  • An additional known method of increasing the thrust output of the engine is to provide the engine with an augmentation system.
  • additional fuel is injected into an exhaust duct formed downstream of the second turbine and is ignited to provide an additional high energy gas stream which, in certain circumstances, is mixed with fan airflow and then ejected through an exhaust nozzle system to provide high energy thrust output from the engine.
  • the augmentation system is normally located within the exhaust duct of the engine, and, in most cases, some means must be provided for protecting the exhaust duct from the extremely high temperatures associated with the augmenter.
  • One common means of providing this protection is to position a'cooling liner within the exhaust duct and to pass cooling air between the liner and the exhaust duct.
  • the first such problem is concerned with the structural stabilizing of the lightweight, cylindrical member which forms the cooling liner.
  • the cooling liner is spaced radially inwardly from the exhaust duct and is subjected to external pressure loading.
  • the coolant pressure outside of the liner be greater than the pressure of the combustion gases inside the liner.
  • the coolant will flow through slots or openings provided in the liner and will form a film of 'coolant on the inside of the liner, thereby protecting the same from the high gas temperatures'within the liner. Because the pressure is greater on the outside of the liner than on the inside, the necessarily thin liner shells must be stabilized against buckling or collapsing inwardly.
  • the convolutions provide too great a coolant flow area for efficient use of the low temperature, fan air as a coolant.
  • the cooling liner must be maintained as close as possible to a pure cylindrical member in order to minimize the flow area between the liner and the exhaust duct.
  • the primary reason convoluted liners are not used on turbofan augmenters, however, is due to the alternate hot and cold streaks imposed on the liner by the mixedflow augmenter. Convoluted liners are susceptible to thermal fatigue failure or severe heat distortion as a result of these hot and cold streaks.
  • An additional method of stabilizing the cooling liners which has proven relatively successful, is to provide a series of reinforcing rings around the liner which provide the stabilizing feature and, in certain designs, also act as mounting brackets.
  • Such reinforcing rings tend to be extremely. heavy and in many cases are incapable of accommodating the relative thermal expansion between the cooling liner and the surrounding exhaust duct.
  • the above and similarly related objects are attained in the present instance by providing a cooling liner mounting system which constrains the liner round at a number of stations along its axial length by the use of stabilizers attached to the liner and stabilizer guides attached to the duct.
  • The'stabilizers are equally spaced circumferentially around the liner with a sufficient number being used such that buckling cannot take place between them.
  • FIG. 1 is a schematic, axial cross-sectional view of a gas turbine engine incorporating the present inventive liner
  • FIG. 2 is an enlarged, partial view of the cooling liner of FIG. 1;-
  • FIG. 3 is a sectional view, taken generally along line 3-3 of FIG. 2;
  • FIG. 4 is a partial. sectional view, taken generally along line 4-4 of FIG. 2;
  • FIG. 5 is a partial perspective view of the liner support assembly with portions deleted for clarity.
  • FIG. 6 is a view, similar to FIG. 3, showing the liner during the assembly step.
  • FIG. I a gas turbine engine 10 of the mixed flow' turbofan type is shown to include a core engine 12 which includes a fanturbine 14 which drives a plurality of fan blades, 15 mounted on a shaft 16.
  • the fan blades 15 are located within an inlet 17 formed byan outer or fan casing 18 which surrounds the entire gas turbine engine 10.
  • the fan casing 18 cooperates with a core engine casing 20 to define parallel flow paths 22 and 23.
  • Air entering the flow path 23 is compressed by means of a compressor 24 and is mixed with fuel in combustor 26.
  • Fuel is delivered to the combustor 26 by means of a plurality of fuel injection points 27 from fuel tubes 28 which extend through the flow path 22.
  • the resultant high energy gas stream exits the combustor 26 and drives a turbine 30 which, in turn; drives the compressor 24 by means of a shaft 31.
  • air flowing through the outer or fan flow path 22 and air exiting the core engine 12 flow through a mixer 32, which operates to mix the two separate flow paths.
  • the mixed flowpath is then plurality of fuel injectors 38.
  • the resultant fuel/air mixture in the augmenter 34 is ignited by means of a suitable igniter (not shown), flows through an exhaust duct 40, and thereafter provides an additional propulsive force by exiting through an. exhaust nozzle 42.
  • the exhaust duct 40 is located at the downstream end of the fan casing 18 and is shown in FIG. 1 to inacted upon by an augmenter 34, which consists of a elude an outer cylindrical casing 44anda cooling air liner which is generally designated by'the numeral 46.
  • the cooling liner 46 is spaced radially inwardly from the exhaust duct casing 44 and defines an annular coolant flow path 48 having an inlet 50 formed by a forward lip 52 at the upstream end of the cooling liner 46.
  • the cooling liner 46 includes a plurality of openings or slots 54 adapted to deliver cooling air from the passageway 48 to the inside of the liner 46.
  • the coolant flowing through the openings 54 provides a film of coolair on the inside of the liner 46thereby protecting both the liner 46 and the surrounding cylindrical casing member 44 from the high temperatures associated-with the operation of the augmenter 34.
  • a high energy gas stream is generated by the combustor 26 and drives the high pressure turbine 30 and low pressure turbine 14, which, in turn, drive the core engine compressor 24 and the fan 15.
  • Air exiting the low pressure turbine 14 and air flowing through the fan flow path 22 are mixed within the mixer 32 and the mixed flow is delivered to the region of the augmenter 34, and a resultant fuel/air mixture generated by the augmenter 34 is ignited to provide an additional propulsive force by exiting through the exhaust nozzle 42.
  • a portion of the air flowing through the fan flow path flows through the openings 54 and forms a film on the inside of the cooling liner 46 thereby protecting the liner 46 and the surrounding casing member 44 from the high gas temperatures associated with operation of the augmenter 34.
  • gas turbine engine 10 described above is typical of manypresent-day augmented turbofan engines and has been described solely to place thepresent invention in proper perspective. As will become clear to those skilled in the art, the present invention will be applicable to other types of gas turbine engines and, therefore, the engine 10 is merely meant to be illustrative.
  • the gas turbine engine augmenter cooling liner 46 and its associated mounting and stabilizing system is shown in greater detail.
  • the exhaust duct casing 44 is mounted to the downstream end of the fan casing 18 by means of flange sections 56 and 58, which form the downstream and upstream ends of the fan casing 18 and the exhaust duct casing 44, respectively.
  • the flange sections 56 and 58 are interconnected in any suitable manner, such as by means of bolts 60.
  • the cooling liner 46 is mounted to the fan casing 18 and the exhaust duct casing 44 by means of a plurality of stabilizer assemblies 62, the details of which are shown in FIGS. 2 through 6. They stabilizer assemblies 62 are located at one or more positions along the axial length of the cooling liner 46,-depending on the length of the.liner..
  • the stabilizer assemblies 62 include'a plurality of stabilizers 64-which are equally spaced around the circumference of the liner 46.
  • Each of the stabilizers 64 includes a mounting plate 66 which attaches directly to the cooling liner 46, a top plate 68 and an interconnecting link 70, which preferably is formed integrally with the mounting plate 66 and top plate 68.
  • the mounting plates 66 are connected to the liner 46 in any suitable manner, such as by means of rivets 72, and the stabilizers 64 are equally spaced around the perimeter of the cooling liner 46 in a circumferential row.
  • the stabilizers act to hold the liner round within the exhaust duct 44.
  • a sufficient number of thestabilizers 64 are provided circumferentially to preclude buckling of the liner 46 between the stabilizers.
  • the stabilizers also act to maintain the proper passage height between the exhaust duct 44 and the liner 46.
  • each of the stabilizers 64 is captured within a stabilizer guide 74, which comprises a generally U-shaped channel member as shown in FIG. 2 havinga bight portion 75 and a pair of overhanging lip members 76 extending inwardly from opposite sides thereof.
  • the lip members 76 may extend over only a portion of the length of the stabilizer guide 74 as best shown in FIG. 5 in order to reduce the weight thereof.
  • the 'overhanginglips 76 and the bight portion 75 of the stabilizer guide 74 act to capture the stabilizer in a radial direction (R-R) and an axial direction (AA) with respect to the centerline of the engine 10.
  • the stabilizers 64 are captured in the circumferential direction (C-C) by means of a pair of capture nuts 78 located on opposite ends of the U-shaped channel portion of the stabilizer sired manner, in the present case, a pair of studs 82 associated with each of the capture nuts 78 are used to connect the stabilizer guides 74 to the positioning band 80.
  • the capture nuts 78 also provide a threaded opening 84 which is adapted to align with a hole 86 provided in the positioning band 80.
  • the threaded openings 84 and holes 86 in the stabilizer guide 74 and the positioning band 80 are, in turn, adapted to be aligned with a plurality of holes 88 located in the exhaust duct casing 44 when the liner 46 is positioned within the duct 44.
  • the positioning band 80 may be connected to the cylindrical casing 44 by means of a plurality of bolts 90, when the positioning band 80 is properly positioned within the cylindrical casing 44.
  • the positioning band 80 is formed to include a gap 92 to aid in the assembly of the combustion liner 46 to the exhaust duct casing 44.
  • the stabilizer guides 74 are designed so as to provide a gap 94. between the top plate 68 and the bight portion 75 of the stabilizer guide 74. .
  • the gap 94 is designed to accommodate the difierential thermal growth between the cooling liner 46 and the duct casing 44 during operapositioning band to be contracted to a smaller diameter with the amount of contraction depending on the size ofthe gap 94.
  • the ability to contract the positioning band 80 greatly enhances the assembly of the cooling liner 46 into the cylindrical casing 44.
  • assembly of the cooling liner 46 is accomplished as follows.
  • the positioning band 80 is contracted to its-smallest possible diameter thereby providing a gap G between the positioning band 80 and the exhaust duct casing44.
  • cooling liner is then slid into the cylindrical casing 44 .and one of the threaded openings 84 withinthe positioning band 80 is aligned with one of the corresponding holes 88 in the cylindrical casing 44 thereby aligning one of the threaded openings 84 with'the hole 88 in the casing.
  • a bolt is then positioned within the opening 84 thereby partially securing the positioning band 80 to the inside of the casing 44 and also aligning each of the remaining holes 86 and 88 around the circumference of the positioning band 80 and the casing 44, respectively.
  • the remaining bolts 90 are positioned within the threaded openings 84 and the positioning band 80 is thus secured to the casing'44. In this manner, the stabilizer guides 74, the stabilizer 64, and, thus, the cooling liner-46 are connected to the casing 44.
  • stabilizers 64 act to hold the liner 46 round'within the casing 44, to define the proper dimension for the coolant passageway 48, permit relative thermal expansion to occur between the liner 46-and the casing 44, are lightweight, and easily aligned during assembly.
  • the mounting assemblies 62 could be axially spaced, as required, along the liner 46 to mount the liner at various points.
  • the mounting assemblies 62 could be used in conjunction with other mounting schemes or could be used as the sole type of mount, depending upon the application.
  • changes could be made in the shape of the individual components, such as the stabilizers 64, without departing from the broad concept disclosed herein. The appended claims are intended to cover these and similar variations in the inventors concepts disclosed herein.
  • a mounting and stabilizing system for said cooling liner including a plurality of stabilizers, means for connecting said stabilizers to said liner, a positioning band adapted to surround a circumferential row of said stabilizers, a plurality of stabilizer guides connected to said positioning band, each of said guides being adapted to capture one of said stabilizers in at least a first direction but to permit relative movement of said stabilizer with respect to said stabilizer guide along said first direction, and means for connecting saidband to said exhaust duct.
  • said band includes at least one gap thereinso as to be capable of contraction to a diameter smaller said band may be contracted to a smaller diameter so as to permit easy insertion of said liner and band into said duct.
  • said stabilizer guide includes means for capturing said stabilizer in a direction perpendicular to said .first direction.
  • said stabilizer includes a mounting plate adapted to be connected to said liner, a top plate adapted to be captured by said stabilizer guide, and a link member adapted to interconnect said mounting plate and said top plate.
  • said, stabilizer guide includes a generally U- shaped channel member having a bight portion and a pair of overhanging lip members extending from said bight portion adapted to capture said top plate, said lip members being spaced from the bight portion of said channel member so as to accommodate relative movement between said channel member and said stabilizer.
  • said band includes a gap permitting contraction of said band to a diameter smaller than that of said exhaust duct.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US00328769A 1973-02-01 1973-02-01 Gas turbine engine augmenter cooling liner stabilizers and supports Expired - Lifetime US3826088A (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
US00328769A US3826088A (en) 1973-02-01 1973-02-01 Gas turbine engine augmenter cooling liner stabilizers and supports
GB333274A GB1454614A (en) 1973-02-01 1974-01-24 Gas turbine engines including exhaust reheat combustion equipment
IT19763/74A IT1007066B (it) 1973-02-01 1974-01-24 Stabilizzatori e sostegni di ca micia di raffreddamento per poten ziatore di spinta di turbomotore a gas
DE2404040A DE2404040C2 (de) 1973-02-01 1974-01-29 Halterung für eine innere Kühlverkleidung des Gehäuses eines Gasturbinentriebwerks-Nachbrenners
CA191,320A CA995015A (en) 1973-02-01 1974-01-30 Gas turbine engine augmenter cooling liner stabilizers and supports
FR7403305A FR2216450B1 (fr) 1973-02-01 1974-01-31
BE140448A BE810491A (fr) 1973-02-01 1974-02-01 Moteur a turbine a gaz a dispositif de post-combustion
JP49012881A JPS5920861B2 (ja) 1973-02-01 1974-02-01 冷却用ライナの取付け及び安定化装置

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US00328769A US3826088A (en) 1973-02-01 1973-02-01 Gas turbine engine augmenter cooling liner stabilizers and supports

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US3826088A true US3826088A (en) 1974-07-30

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Application Number Title Priority Date Filing Date
US00328769A Expired - Lifetime US3826088A (en) 1973-02-01 1973-02-01 Gas turbine engine augmenter cooling liner stabilizers and supports

Country Status (8)

Country Link
US (1) US3826088A (fr)
JP (1) JPS5920861B2 (fr)
BE (1) BE810491A (fr)
CA (1) CA995015A (fr)
DE (1) DE2404040C2 (fr)
FR (1) FR2216450B1 (fr)
GB (1) GB1454614A (fr)
IT (1) IT1007066B (fr)

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US4718230A (en) * 1986-11-10 1988-01-12 United Technologies Corporation Augmentor liner construction
US4854122A (en) * 1988-01-28 1989-08-08 The United States Of America As Represented By The Secretary Of The Air Force Augmentor curtain liner assembly for sharing tensile loading
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US4866942A (en) * 1987-10-13 1989-09-19 The United States Of America As Represented By The Secretary Of The Air Force Augmentor curtain liner for equalizing pressure therein
US4907946A (en) * 1988-08-10 1990-03-13 General Electric Company Resiliently mounted outlet guide vane
US4920742A (en) * 1988-05-31 1990-05-01 General Electric Company Heat shield for gas turbine engine frame
US4987736A (en) * 1988-12-14 1991-01-29 General Electric Company Lightweight gas turbine engine frame with free-floating heat shield
US4989406A (en) * 1988-12-29 1991-02-05 General Electric Company Turbine engine assembly with aft mounted outlet guide vanes
US5201887A (en) * 1991-11-26 1993-04-13 United Technologies Corporation Damper for augmentor liners
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US20110016879A1 (en) * 2006-07-28 2011-01-27 United Technologies Corporation Low profile attachment hanger system for a cooling liner within a gas turbine engine swivel exhaust duct
US20130167553A1 (en) * 2010-09-08 2013-07-04 Snecma Hyperstatic truss comprising connecting rods
US20140003931A1 (en) * 2012-06-28 2014-01-02 Alstom Technology Ltd Diffuser for the exhaust section of a gas turbine and gas turbine with such a diffuser
US20140026590A1 (en) * 2012-07-25 2014-01-30 Hannes A. Alholm Flexible combustor bracket
US20140053563A1 (en) * 2012-08-27 2014-02-27 Snecma Method for assembling a nozzle and an exhaust case of a turbomachine
US20140090398A1 (en) * 2012-09-28 2014-04-03 United Technologies Corporation Flexible connection between a wall and a case of a turbine engine
US20140219707A1 (en) * 2013-02-07 2014-08-07 Rolls-Royce Plc Panel mounting arrangement
EP2837811A1 (fr) * 2013-08-16 2015-02-18 Rolls-Royce plc Système de fixation de panneau
US20150068212A1 (en) * 2012-04-19 2015-03-12 General Electric Company Combustor liner stop
US9133768B2 (en) 2012-08-21 2015-09-15 United Technologies Corporation Liner bracket for gas turbine engine
US9188024B2 (en) 2013-02-22 2015-11-17 Pratt & Whitney Canada Corp. Exhaust section for bypass gas turbine engines
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US20160032863A1 (en) * 2013-04-15 2016-02-04 Aircelle Nozzle for an aircraft turboprop engine with an unducted fan
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US9316174B2 (en) 2012-06-04 2016-04-19 United Technologies Corporation Liner hanger with spherical washers
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US10253651B2 (en) 2012-06-14 2019-04-09 United Technologies Corporation Turbomachine flow control device
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Also Published As

Publication number Publication date
GB1454614A (en) 1976-11-03
BE810491A (fr) 1974-05-29
IT1007066B (it) 1976-10-30
FR2216450B1 (fr) 1980-06-27
FR2216450A1 (fr) 1974-08-30
DE2404040A1 (de) 1974-08-08
JPS5920861B2 (ja) 1984-05-16
JPS49105018A (fr) 1974-10-04
DE2404040C2 (de) 1983-09-01
CA995015A (en) 1976-08-17

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