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Month in the Patent Office

Month in the Patent Office AIRCRAF T ENGINEERING 24 January, 1931 A Selection of the More Important Aircraft and Engine Specifications Published Recently 334,405 . Aircraft structures. Wallis, controls the pressure in the chamber c2 ant B . N., of Vickers (Aviation), Ltd., Weybridge ma y lead the air released from c2 back to the Works, Byfleet Road, Weybridge, Surrey. compressor. U gauges or other means are Sept. 26, 1929, Nos. 29167 and 39440. used to indicate the pressure differences exist- [Class 4.] ing between the chamber c2 and, on one hand Framework; fuselages; planes, construction th e compressor-delivery pressure, and on the of.—Frame structures for wings and fuselages other hand, the pressure of the atmosphere. comprise longitudinal members composed of An electric circuit 3 is closed when a maximum thin tubular members arranged in bays, some, permissible pressure in the chamber c2 is reached and operates warning means such as or all of which, are non-rectangular, each short-circuiting the engine sparking-plugs. The tubula r member terminates in a strengthening controls of the valves m and o may be inter sleeve adapted to connect the tubular member connected. Fig. 3 illustrates a modification in one bay to the continuing tubular member of the adjacent bay, the sleeves being formed in which two spring-loaded valves 10 by-pas plate 26 is clamped between the key plate and a with terminal flanges, all t o opposed flanges at air from the compressor into a box 7 when ; flange 18 on assembly and serves for the con­ the end of each bay being contained in a single nection of lateral members. Cups 31 for plane transverse to the structure and being receiving diagonal bracing members 33 are clamped together. Lateral members have their threaded externally to opposite hands to engage ends connected to and located by the flanges, with internal screw threads 29, 30 on the and each joint is so arranged that the forces ferrules 20. The screw threads 19 in the in the longitudinal and lateral members are sleeves are normal to the flanges 18, which may all directed to a common point of intersection in addition be extended outwardly. The between the flanges. In a fuselage or wing bearing plate 26 may be omitted and lateral structur e comprising upper and lower pairs of members be attached to the key plate. The bearing plates and lateral members may be employed for connection of other framing control valve 9 is open to the delivery. An members such as those for supporting engine alternative means of control consists in pro- or petrol tan k and the internal cups may serve viding a hinged cover to part of the compressor also for attachment of stays for these members. casing which opens either inside or outside the Alternatively the cups may be omitted and delivery channel. The cover may be hinged diagonal members be attached to external in two parts. Specifications 313,417 and flanges on the sleeve. A wing spar is illustrated 326,172 are referred to. built-up from longitudinal built-up tubular booms having square transverse panels com­ prising vertical, and cruciform diagonal, struts, Aluminium Alloy Data and diagonal bracing members between the The British Aluminium Company, Limited, o transverse panels; the outer bays of the spar Adelaide House, King William Street, London are shown as tapering to the wing tips and E.C.4, send data sheets for insertion in their pub embody tubular members of progressively lication, "Aluminium. Facts and Figures." Among reduced diameter. these are two valuable treatises-in-little on the important subjects of heat treatment of casting spaced longitudinals connected by lateral 336,295 . Rotary Pumps. Eyston, (B. 27), and forging (B. 42), which are newly members dividing the structure into bays of G. E . T., 329, High Holborn, London. July 12, written. Another useful sheet (A. 115) contains irregular shape, longitudinal tubular members 1929. No. 21506. [Classes 7 (ii), 7 (iii), and the full details of all B.E.S.A. specifications on 1, Fig. 4, which may be formed from helically- 110 (ii).] aluminium alloy, now current, while a new sheet wound tubular strip, have sleeves 2 at each (A. 121-2) includes approximate melting point: Fixed-abutment type; valve-gear and valve- end formed with flanges 3, the outer surfaces for all alloys listed, against the B.S. specification actuating mechanism; compensating for irregu­ of which subtend predetermined angles to the numbers. larity of flow; governing and regulating.—In a axes of the tubes so that these can extend at supercharging installation for internal-combus­ an y desired angle relatively to each other. tion, preferably aircraft engines, the pressure Latera l members 4 may be clamped between throughout the delivery system is maintained th e flanges 3 or as shown be provided with Classified Advertisements constan t by controlling the pressure of air bifurcated end fittings 13 clamped to the delivered by a rotary compressor a which 2/- per Line, 2 Line Minimum, Payable in Advance. flanges 3 by one of the bolts 12 securing the supplies a carburettor chamber c2. A sliding flanges to each other. Diagonal bracing mem­ valve m operated through a pinion and rack bers 5 pass through holes 9, 10 in sleeve and mechanism n, moves to vary the number of tube , respectively, and are attached by internal holes g covered, in the casing. When moved AEROMARINE ADVERTISING, LTD cups 14 formed with coned surfaces 15 bearing right back the top casing are covered is less on similar surfaces 16 in the flanges. In a Advertising Consultants. Specialists in tha n the circumferential pitch of the vanes f modified form, Fig. 5, th e sleeves 2 have internal the preparation of advertisements and the and no compression takes place. A valve o flanges 18 threade d internally a t 19, th e threads conduct of advertising campaigns. 56-57, Flee of adjacent flanges being left and right-handed Street, London, E.C.4. (Central 2423; 3220 respectively. These are clamped together by a n externally-threaded ferrule 20, Fig. 8, upon which is mounted a key 23, Fig. 9. A bearing "AIRCRAFT ENGINEERING," Vol. II. * These abstracts of complete specifications of Patents recently published ate specially compiled, by permission of H.M. Stationery The title page and index to Volume II are Office, from abridgements appearing in the Patent Journal. Printed copies of the full specifications can be obtained from the Patent now ready. These are being enclosed free Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. with this issue to subscribers. The price to Except where otherwise stated, the specification is unaccompanied non-subscribers is 6d. post free. by drawings if none is reproduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 3 (1): 1 – Jan 1, 1931
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029361
Publisher site
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Abstract

AIRCRAF T ENGINEERING 24 January, 1931 A Selection of the More Important Aircraft and Engine Specifications Published Recently 334,405 . Aircraft structures. Wallis, controls the pressure in the chamber c2 ant B . N., of Vickers (Aviation), Ltd., Weybridge ma y lead the air released from c2 back to the Works, Byfleet Road, Weybridge, Surrey. compressor. U gauges or other means are Sept. 26, 1929, Nos. 29167 and 39440. used to indicate the pressure differences exist- [Class 4.] ing between the chamber c2 and, on one hand Framework; fuselages; planes, construction th e compressor-delivery pressure, and on the of.—Frame structures for wings and fuselages other hand, the pressure of the atmosphere. comprise longitudinal members composed of An electric circuit 3 is closed when a maximum thin tubular members arranged in bays, some, permissible pressure in the chamber c2 is reached and operates warning means such as or all of which, are non-rectangular, each short-circuiting the engine sparking-plugs. The tubula r member terminates in a strengthening controls of the valves m and o may be inter sleeve adapted to connect the tubular member connected. Fig. 3 illustrates a modification in one bay to the continuing tubular member of the adjacent bay, the sleeves being formed in which two spring-loaded valves 10 by-pas plate 26 is clamped between the key plate and a with terminal flanges, all t o opposed flanges at air from the compressor into a box 7 when ; flange 18 on assembly and serves for the con­ the end of each bay being contained in a single nection of lateral members. Cups 31 for plane transverse to the structure and being receiving diagonal bracing members 33 are clamped together. Lateral members have their threaded externally to opposite hands to engage ends connected to and located by the flanges, with internal screw threads 29, 30 on the and each joint is so arranged that the forces ferrules 20. The screw threads 19 in the in the longitudinal and lateral members are sleeves are normal to the flanges 18, which may all directed to a common point of intersection in addition be extended outwardly. The between the flanges. In a fuselage or wing bearing plate 26 may be omitted and lateral structur e comprising upper and lower pairs of members be attached to the key plate. The bearing plates and lateral members may be employed for connection of other framing control valve 9 is open to the delivery. An members such as those for supporting engine alternative means of control consists in pro- or petrol tan k and the internal cups may serve viding a hinged cover to part of the compressor also for attachment of stays for these members. casing which opens either inside or outside the Alternatively the cups may be omitted and delivery channel. The cover may be hinged diagonal members be attached to external in two parts. Specifications 313,417 and flanges on the sleeve. A wing spar is illustrated 326,172 are referred to. built-up from longitudinal built-up tubular booms having square transverse panels com­ prising vertical, and cruciform diagonal, struts, Aluminium Alloy Data and diagonal bracing members between the The British Aluminium Company, Limited, o transverse panels; the outer bays of the spar Adelaide House, King William Street, London are shown as tapering to the wing tips and E.C.4, send data sheets for insertion in their pub embody tubular members of progressively lication, "Aluminium. Facts and Figures." Among reduced diameter. these are two valuable treatises-in-little on the important subjects of heat treatment of casting spaced longitudinals connected by lateral 336,295 . Rotary Pumps. Eyston, (B. 27), and forging (B. 42), which are newly members dividing the structure into bays of G. E . T., 329, High Holborn, London. July 12, written. Another useful sheet (A. 115) contains irregular shape, longitudinal tubular members 1929. No. 21506. [Classes 7 (ii), 7 (iii), and the full details of all B.E.S.A. specifications on 1, Fig. 4, which may be formed from helically- 110 (ii).] aluminium alloy, now current, while a new sheet wound tubular strip, have sleeves 2 at each (A. 121-2) includes approximate melting point: Fixed-abutment type; valve-gear and valve- end formed with flanges 3, the outer surfaces for all alloys listed, against the B.S. specification actuating mechanism; compensating for irregu­ of which subtend predetermined angles to the numbers. larity of flow; governing and regulating.—In a axes of the tubes so that these can extend at supercharging installation for internal-combus­ an y desired angle relatively to each other. tion, preferably aircraft engines, the pressure Latera l members 4 may be clamped between throughout the delivery system is maintained th e flanges 3 or as shown be provided with Classified Advertisements constan t by controlling the pressure of air bifurcated end fittings 13 clamped to the delivered by a rotary compressor a which 2/- per Line, 2 Line Minimum, Payable in Advance. flanges 3 by one of the bolts 12 securing the supplies a carburettor chamber c2. A sliding flanges to each other. Diagonal bracing mem­ valve m operated through a pinion and rack bers 5 pass through holes 9, 10 in sleeve and mechanism n, moves to vary the number of tube , respectively, and are attached by internal holes g covered, in the casing. When moved AEROMARINE ADVERTISING, LTD cups 14 formed with coned surfaces 15 bearing right back the top casing are covered is less on similar surfaces 16 in the flanges. In a Advertising Consultants. Specialists in tha n the circumferential pitch of the vanes f modified form, Fig. 5, th e sleeves 2 have internal the preparation of advertisements and the and no compression takes place. A valve o flanges 18 threade d internally a t 19, th e threads conduct of advertising campaigns. 56-57, Flee of adjacent flanges being left and right-handed Street, London, E.C.4. (Central 2423; 3220 respectively. These are clamped together by a n externally-threaded ferrule 20, Fig. 8, upon which is mounted a key 23, Fig. 9. A bearing "AIRCRAFT ENGINEERING," Vol. II. * These abstracts of complete specifications of Patents recently published ate specially compiled, by permission of H.M. Stationery The title page and index to Volume II are Office, from abridgements appearing in the Patent Journal. Printed copies of the full specifications can be obtained from the Patent now ready. These are being enclosed free Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. with this issue to subscribers. The price to Except where otherwise stated, the specification is unaccompanied non-subscribers is 6d. post free. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jan 1, 1931

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