US2863634A - Shroud ring construction for turbines and compressors - Google Patents
Shroud ring construction for turbines and compressors Download PDFInfo
- Publication number
- US2863634A US2863634A US551583A US55158355A US2863634A US 2863634 A US2863634 A US 2863634A US 551583 A US551583 A US 551583A US 55158355 A US55158355 A US 55158355A US 2863634 A US2863634 A US 2863634A
- Authority
- US
- United States
- Prior art keywords
- section
- shroud ring
- casing
- ring
- arcuate
- 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
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
-
- 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
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
-
- 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
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/246—Fastening of diaphragms or stator-rings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
Definitions
- This invention relates to a construction of shroud ring for turbines or compressors, that is to say the shroud ring which closely surrounds a ring of rotor blades in a turbine or compressor.
- a shroud ring assembly comprises a tubular outer casting, and an annular shroud ring disposed within the outer casing and comprising a series of separate arcuate circumferentiallyextending sections each of which is rigidly connected at one end only (hereinafter called the fixed end) to the tubular outer casing and is supported at its other end (hereinafter called the free end) from the fixed end of the adjacent arcuate section through a connection which allows limited free relative circumferential movement between the adjacent ends of the two arcuate sections but substantially prevents relative radial movement between such adjacent ends.
- connection between the fixed end of each arcuate section and the free end of an adjacent arcuate section is in the form of a step on the end face of one of the sections engaging a coopcrating step on the adjacent end face of the other section, it being understood that the step is arranged so that the free end of the appropriate section is held from inward radial movement relatively to the fixed end of the other section by the inter-engaging steps.
- a key may be provided extending between and engaging axially extending slots in the adjacent ends of the two sections.
- each arcuate section of the shroud ring is preferably of such cross section as to provide Within it a chamber having means by which cooling air can be supplied to and permitted to escape from it.
- one or more sheet metal baflle members are then preferably provided within each arcuate section and arranged to define with the inner circumferential wall at least of the arcuate section a narrow passage through which the cooling air is caused by the baflle member to fioW.
- each arcuate section is secured to the tubular outer casing by means of a radially arranged bolt, stud, or the like engaging a bore in the appropriate end of the arcuate section.
- each of the bores in question may be screwthreaded and be engaged by the inner screwthreaded end of a bolt passing freely through a radial hole in the tubular outer casing.
- each arcuate section of the shroud ring is of channelshaped cross-section in planes containing the axis of the tubular casing, and one construction embodying arcuate sections of this form and a modification thereof, are shown in the accompanying drawings, in which:
- Figure 1 is a sectional view in a plane containing the axis of a combustion turbine of the part of such turbine including a shroud ring according to the invention and two adjacent rings of stator blades, the parts shown in the drawing being for convenience limited substantially to those necessary for an understanding of the invention itself and not representing a complete cross-section through the turbine,
- Figure 2 is a cross-section on the line 22 of Figure 1 through the shroud ring assembly
- Figure 3 is a fragmentary cross-section, corresponding to Figure 2, of a modified form of connection.
- A is the tubular outer casing of the turbine within which is mounted a ring of stator blades B of the kind sometimes called a nozzle ring through which the hot gases from combustion chambers, one of which is indicated at C, are delivered to a ring of rotor blades indicated at D supported upon a rotor disc D in well-known manner.
- the gases leaving the rotor blades D then pass through a ring of stator blades E rigid with the casing A before impinging on the rotor blades F of the next stage carried by a rotor disc F
- the blades B constituting the nozzle ring are of known hollow form and are arranged in a manner known per se and in itself forming no part of the invention, to have cooling air delivered to their inner ends through a chamber G so that this cooling air flows through the blades into an outer annular cooling air chamber H.
- a shroud ring assembly Surrounding the ring of rotor blades D is a shroud ring assembly according to the invention comprising a supporting structure formed by the surrounding part of the casing A on which, to this end, are formed a series of circumferentially spaced bosses A and a shroud ring comprising a series of separate relatively circumferentiaily aligned arcuate sections I each of channel-shaped cross-section, as shown and of closed-ended trough-like form, the inner circumferential wall of each section being in the form a section of a frustrum of a cone, While the flanges J J on the sides of each arcuate section are located between a flange A formed on a ring A rigid with the casing A and a ring A also rigid with the casing A and serving to support the outer ends of the blades B of the nozzle ring.
- the arcuate sections I, of the shroud ring are not gripped between the flange A and the ring A
- each arcuate shroud ring section I Formed in one fixed end of each arcuate shroud ring section I is a boss J provided with a circumferentially extending surface 10 having formed therein a radial hole which is internally screwthreaded as shown at J to receive the inner end of a bolt K passing through one of the bosses A and serving to immovably secure that end of the shroud ring section firmly to the casing A with its surface 10 flush against the inner circumferential wall 11 of the casing as shown most clearly in Figure 2.
- the free end of each said section is provided with a portion 12 normally abutting radially against theinner wall 11 of the casing in circumferentially sliding relation thereto.
- each shroud ring section J adjacent to the boss I is also provided with a Step as shown at J while the opposite or free end of the shroud ring section is provided with a step J having a face or portion 13 spaced radially inwardly of its portion 12 and which, as clearly shown in Figure 2, circumferentially slidably engages and co-operates with the step I on the adjacent end of the adjacent shroud ring section to form a circumferential-sliding connection between the adjoining ring section ends prevent the endprovided with a step I from moving radially inwards beyond a predetermined small amount represented by a limited working-clearance 14 between the abutting steps I and I is such that each shroudring section I is-free, to expand circumferentially'relatively to the casing A and to the adjacent shroud ring sections while, as will be-seen, being maintained substantially in position both axially and radially and supported from the casing A at a single point by the bolt K.
- each shroud ringsection In the arrangement shown there ismounted and located within each shroud ringsection a thin sheet metalbafile L the edge L of which is secured as by welding to-the flange J of the shroud ring section, while the edge L is spaced from the inner circumferentialwall 11 of the shroud ring section by spaced tabs L
- Air outlet apertures M are formed in each-shroud ring section and the arrangement is such, as will be seen, that cooling air delivered to the annular chamber H is causedto flow round the baffle L and out through the exit apertures M where it enters the gas stream flowing through the turbine and, by flowing over the tips of the rotor blades, tends to assist further in the cooling of the shroud ring and to assist in the cooling of these blades.
- bafile means represented by the battle L defines with the adjacent walls of the casing A and the shroud ring section I a narrow passage between the bafile means and the walls of the casing and shroud section, through which narrow passage the cooling air is caused to flow.
- a shroud ring assembly for an axial flow turbine comprising a tubular cylindrical outer casing having an inner circumferential wall, and an annular shroud ring disposed coaxially within the outer casing, said shroud ring comprising a plurality of separate circumferentially aligned arcuate sections, each section having a fixed end formed with a circumferentially extending surface and a free end at its opposite circumferential extremity, means The arrangement fixedly and immovably securing the fixed end of each said section in said casing with said circumferentially extending surface flush against said inner circumferential wall of the casing, the remainder of each said section, including its free end, being disconnected from said casing, the free end of each said section being in circumferentially spaced relation tosaid fixed end of an adjoining section, and having a portion normally abutting radially against the said inner circumferential wall of the casing and having a further circumferentially extending portion radially inwardly spaced from said first mentioned portion, and
- a shroud ring assembly as claimed in claim 1, in which the said means by which the fixed end of each arcuate section is secured to the inner circumferential wall of. the casing comprises a radially arranged bolt, engaging a bore in the appropriate end of the arcuate section.
- a shroud ring assembly as claimed in claim 3, in which the said bore is screwthreaded and is engaged by the inner screwthreaded endv of the bolt, which passes freely through a hole in the tubular outer casing.
- each arcuate section is of channel-shaped cross-section with the sides of the channel facing radially outwards and, the tubular outer casing includes parts rigid with it and locating the arcuate sections by engagement with the sides thereof.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB345766X | 1954-12-16 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2863634A true US2863634A (en) | 1958-12-09 |
Family
ID=10367346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US551583A Expired - Lifetime US2863634A (en) | 1954-12-16 | 1955-12-07 | Shroud ring construction for turbines and compressors |
Country Status (7)
Country | Link |
---|---|
US (1) | US2863634A (xx) |
BE (1) | BE543709A (xx) |
CH (1) | CH345766A (xx) |
DE (1) | DE1080119B (xx) |
FR (1) | FR1138118A (xx) |
GB (1) | GB785466A (xx) |
NL (2) | NL202529A (xx) |
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3391904A (en) * | 1966-11-02 | 1968-07-09 | United Aircraft Corp | Optimum response tip seal |
US3408044A (en) * | 1965-07-23 | 1968-10-29 | Bbc Brown Boveri & Cie | Combustion gas turbine with cooled guide vane support structure |
US3520635A (en) * | 1968-11-04 | 1970-07-14 | Avco Corp | Turbomachine shroud assembly |
US3689174A (en) * | 1971-01-11 | 1972-09-05 | Westinghouse Electric Corp | Axial flow turbine structure |
US3807891A (en) * | 1972-09-15 | 1974-04-30 | United Aircraft Corp | Thermal response turbine shroud |
US3824031A (en) * | 1972-01-12 | 1974-07-16 | Rolls Royce 1971 Ltd | Turbine casing for a gas turbine engine |
US3854843A (en) * | 1971-12-01 | 1974-12-17 | R Penny | Composite elongate member having a predetermined effective coefficient of linear expansion |
US3981609A (en) * | 1975-06-02 | 1976-09-21 | United Technologies Corporation | Coolable blade tip shroud |
US3986720A (en) * | 1975-04-14 | 1976-10-19 | General Electric Company | Turbine shroud structure |
US4013376A (en) * | 1975-06-02 | 1977-03-22 | United Technologies Corporation | Coolable blade tip shroud |
US4317646A (en) * | 1979-04-26 | 1982-03-02 | Rolls-Royce Limited | Gas turbine engines |
US4355952A (en) * | 1979-06-29 | 1982-10-26 | Westinghouse Electric Corp. | Combustion turbine vane assembly |
US4398864A (en) * | 1979-05-02 | 1983-08-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Sealing device between two elements of a turbomachine |
US4595345A (en) * | 1979-01-15 | 1986-06-17 | Varga John M J | Gas compressor or blower |
US4741669A (en) * | 1983-04-27 | 1988-05-03 | Tatsuji Shimokawabe | Shroud |
US5088888A (en) * | 1990-12-03 | 1992-02-18 | General Electric Company | Shroud seal |
US5131811A (en) * | 1990-09-12 | 1992-07-21 | United Technologies Corporation | Fastener mounting for multi-stage compressor |
US5145316A (en) * | 1989-12-08 | 1992-09-08 | Rolls-Royce Plc | Gas turbine engine blade shroud assembly |
US5158430A (en) * | 1990-09-12 | 1992-10-27 | United Technologies Corporation | Segmented stator vane seal |
US5180281A (en) * | 1990-09-12 | 1993-01-19 | United Technologies Corporation | Case tying means for gas turbine engine |
US5297932A (en) * | 1990-09-12 | 1994-03-29 | United Technologies Corporation | Fastener for multi-stage compressor |
US5823741A (en) * | 1996-09-25 | 1998-10-20 | General Electric Co. | Cooling joint connection for abutting segments in a gas turbine engine |
US6464453B2 (en) * | 2000-12-04 | 2002-10-15 | General Electric Company | Turbine interstage sealing ring |
US20040219009A1 (en) * | 2003-03-06 | 2004-11-04 | Snecma Moteurs | Turbomachine with cooled ring segments |
US20050232752A1 (en) * | 2004-04-15 | 2005-10-20 | David Meisels | Turbine shroud cooling system |
US9334754B2 (en) | 2010-11-29 | 2016-05-10 | Alstom Technology Ltd. | Axial flow gas turbine |
EP3187690A1 (en) * | 2016-01-04 | 2017-07-05 | General Electric Company | System for an inlet guide vane shroud and baffle assembly |
US20170218788A1 (en) * | 2014-10-23 | 2017-08-03 | Siemens Energy, Inc. | Gas turbine engine with a turbine blade tip clearance control system |
US20200072070A1 (en) * | 2018-09-05 | 2020-03-05 | United Technologies Corporation | Unified boas support and vane platform |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1286810B (de) * | 1963-11-19 | 1969-01-09 | Licentia Gmbh | Laufschaufelradialspalt-Abdeckring einer Axialturbomaschine, insbesondere -gasturbine |
DE3018621C2 (de) * | 1980-05-16 | 1982-06-03 | MTU Motoren- und Turbinen-Union München GmbH, 8000 München | Außengehäuse für Axialverdichter oder -turbinen von Strömungsmaschinen, insbesondere Gasturbinentriebwerken |
US4921401A (en) * | 1989-02-23 | 1990-05-01 | United Technologies Corporation | Casting for a rotary machine |
US5221096A (en) * | 1990-10-19 | 1993-06-22 | Allied-Signal Inc. | Stator and multiple piece seal |
NL1014013C2 (nl) * | 2000-01-05 | 2001-07-18 | Ventilatoren Sirocco Howden Bv | Behuizingsdeel voor een ventilatorwaaier. |
JP6271077B2 (ja) | 2014-07-24 | 2018-01-31 | シーメンス アクチエンゲゼルシヤフトSiemens Aktiengesellschaft | ガスタービンエンジン内で使用可能なステータベーンシステム |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR625938A (fr) * | 1926-03-24 | 1927-08-23 | Rateau Sa | Dispositif de fixation de tuyères distributrices pour turbines à vapeur |
US2510606A (en) * | 1943-05-22 | 1950-06-06 | Lockheed Aircraft Corp | Turbine construction |
CH270334A (de) * | 1945-01-16 | 1950-08-31 | Power Jets Res & Dev Ltd | Schaufelträger in axialen Kreiselmaschinen. |
US2584899A (en) * | 1945-01-23 | 1952-02-05 | Power Jets Res & Dev Ltd | Construction of stator elements of turbines, compressors, or like machines |
GB679916A (en) * | 1949-04-29 | 1952-09-24 | Geoffrey Bertram Robert Feilde | Improvements in gas turbines |
US2685429A (en) * | 1950-01-31 | 1954-08-03 | Gen Electric | Dynamic sealing arrangement for turbomachines |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE185427C (xx) * | 1904-11-17 | 1907-06-11 | ||
GB597165A (en) * | 1945-01-23 | 1948-01-20 | Power Jets Res & Dev Ltd | Improvements relating to the construction of stator elements of turbines, compressors or like machines |
GB618525A (en) * | 1946-06-18 | 1949-02-23 | Adrian Albert Lombard | Improvements in or relating to gas-turbine engines |
GB721453A (en) * | 1951-10-19 | 1955-01-05 | Vickers Electrical Co Ltd | Improvements relating to gas turbines |
-
0
- NL NL103792D patent/NL103792C/xx active
- NL NL202529D patent/NL202529A/xx unknown
- BE BE543709D patent/BE543709A/xx unknown
-
1954
- 1954-12-16 GB GB36510/54A patent/GB785466A/en not_active Expired
-
1955
- 1955-12-03 DE DEN11537A patent/DE1080119B/de active Pending
- 1955-12-07 US US551583A patent/US2863634A/en not_active Expired - Lifetime
- 1955-12-15 CH CH345766D patent/CH345766A/fr unknown
- 1955-12-16 FR FR1138118D patent/FR1138118A/fr not_active Expired
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR625938A (fr) * | 1926-03-24 | 1927-08-23 | Rateau Sa | Dispositif de fixation de tuyères distributrices pour turbines à vapeur |
US2510606A (en) * | 1943-05-22 | 1950-06-06 | Lockheed Aircraft Corp | Turbine construction |
CH270334A (de) * | 1945-01-16 | 1950-08-31 | Power Jets Res & Dev Ltd | Schaufelträger in axialen Kreiselmaschinen. |
US2584899A (en) * | 1945-01-23 | 1952-02-05 | Power Jets Res & Dev Ltd | Construction of stator elements of turbines, compressors, or like machines |
GB679916A (en) * | 1949-04-29 | 1952-09-24 | Geoffrey Bertram Robert Feilde | Improvements in gas turbines |
US2685429A (en) * | 1950-01-31 | 1954-08-03 | Gen Electric | Dynamic sealing arrangement for turbomachines |
Cited By (35)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3408044A (en) * | 1965-07-23 | 1968-10-29 | Bbc Brown Boveri & Cie | Combustion gas turbine with cooled guide vane support structure |
US3391904A (en) * | 1966-11-02 | 1968-07-09 | United Aircraft Corp | Optimum response tip seal |
US3520635A (en) * | 1968-11-04 | 1970-07-14 | Avco Corp | Turbomachine shroud assembly |
US3689174A (en) * | 1971-01-11 | 1972-09-05 | Westinghouse Electric Corp | Axial flow turbine structure |
US3854843A (en) * | 1971-12-01 | 1974-12-17 | R Penny | Composite elongate member having a predetermined effective coefficient of linear expansion |
US3824031A (en) * | 1972-01-12 | 1974-07-16 | Rolls Royce 1971 Ltd | Turbine casing for a gas turbine engine |
US3807891A (en) * | 1972-09-15 | 1974-04-30 | United Aircraft Corp | Thermal response turbine shroud |
US3986720A (en) * | 1975-04-14 | 1976-10-19 | General Electric Company | Turbine shroud structure |
US3981609A (en) * | 1975-06-02 | 1976-09-21 | United Technologies Corporation | Coolable blade tip shroud |
US4013376A (en) * | 1975-06-02 | 1977-03-22 | United Technologies Corporation | Coolable blade tip shroud |
US4595345A (en) * | 1979-01-15 | 1986-06-17 | Varga John M J | Gas compressor or blower |
US4317646A (en) * | 1979-04-26 | 1982-03-02 | Rolls-Royce Limited | Gas turbine engines |
US4398864A (en) * | 1979-05-02 | 1983-08-16 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Sealing device between two elements of a turbomachine |
US4355952A (en) * | 1979-06-29 | 1982-10-26 | Westinghouse Electric Corp. | Combustion turbine vane assembly |
US4741669A (en) * | 1983-04-27 | 1988-05-03 | Tatsuji Shimokawabe | Shroud |
US5145316A (en) * | 1989-12-08 | 1992-09-08 | Rolls-Royce Plc | Gas turbine engine blade shroud assembly |
US5131811A (en) * | 1990-09-12 | 1992-07-21 | United Technologies Corporation | Fastener mounting for multi-stage compressor |
US5158430A (en) * | 1990-09-12 | 1992-10-27 | United Technologies Corporation | Segmented stator vane seal |
US5180281A (en) * | 1990-09-12 | 1993-01-19 | United Technologies Corporation | Case tying means for gas turbine engine |
US5297932A (en) * | 1990-09-12 | 1994-03-29 | United Technologies Corporation | Fastener for multi-stage compressor |
US5088888A (en) * | 1990-12-03 | 1992-02-18 | General Electric Company | Shroud seal |
US5823741A (en) * | 1996-09-25 | 1998-10-20 | General Electric Co. | Cooling joint connection for abutting segments in a gas turbine engine |
US6464453B2 (en) * | 2000-12-04 | 2002-10-15 | General Electric Company | Turbine interstage sealing ring |
US7011493B2 (en) | 2003-03-06 | 2006-03-14 | Snecma Moteurs | Turbomachine with cooled ring segments |
US20040219009A1 (en) * | 2003-03-06 | 2004-11-04 | Snecma Moteurs | Turbomachine with cooled ring segments |
US20050232752A1 (en) * | 2004-04-15 | 2005-10-20 | David Meisels | Turbine shroud cooling system |
US7063503B2 (en) | 2004-04-15 | 2006-06-20 | Pratt & Whitney Canada Corp. | Turbine shroud cooling system |
US9334754B2 (en) | 2010-11-29 | 2016-05-10 | Alstom Technology Ltd. | Axial flow gas turbine |
US20170218788A1 (en) * | 2014-10-23 | 2017-08-03 | Siemens Energy, Inc. | Gas turbine engine with a turbine blade tip clearance control system |
US10830083B2 (en) * | 2014-10-23 | 2020-11-10 | Siemens Energy, Inc. | Gas turbine engine with a turbine blade tip clearance control system |
EP3187690A1 (en) * | 2016-01-04 | 2017-07-05 | General Electric Company | System for an inlet guide vane shroud and baffle assembly |
CN107023333A (zh) * | 2016-01-04 | 2017-08-08 | 通用电气公司 | 用于入口导叶护罩和挡板组件的*** |
CN107023333B (zh) * | 2016-01-04 | 2019-03-19 | 通用电气公司 | 用于入口导叶护罩和挡板组件的*** |
US10502233B2 (en) | 2016-01-04 | 2019-12-10 | General Electric Company | System for an inlet guide vane shroud and baffle assembly |
US20200072070A1 (en) * | 2018-09-05 | 2020-03-05 | United Technologies Corporation | Unified boas support and vane platform |
Also Published As
Publication number | Publication date |
---|---|
CH345766A (fr) | 1960-04-15 |
FR1138118A (fr) | 1957-06-11 |
NL103792C (xx) | |
NL202529A (xx) | |
BE543709A (xx) | |
DE1080119B (de) | 1960-04-21 |
GB785466A (en) | 1957-10-30 |
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