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Aviation History
1952
1952 - 1230.PDF
540 FLIGHT, 2 May 1952 THE INDUSTRY D.H. Annual Report A DOCUMENT both instructive and beautifully produced (with colour and half-tone illustrations) is the 32nd annual report of the de Havilland Aircraft Co., Ltd. It has been circulated to shareholders in advance of the annual general meeting, which takes place on May 20th. As announced in Flight of March 28th, the net profit of the group, as compared with the previous year, has increased to £i>773>594 from £1,071,101, after provision for all charges except U.K. and Dominion taxation. It is proposed to pay a -]\ per cent dividend (less tax) on £2,740,912 of Ordinary Stock and at \\ per cent on £1,664,547 of Ordinary Stock for the year ended Septem ber 30th last. In the chairman's address, printed in the report, an interesting reference is made to the D.H no. Performance of this machine, it is stated, is "very high indeed," and is exceeding expectations. It is foreseen that the type will be capable of considerable develop ment in both performance and versatility, and that its variants may well fill several operational roles, as have the Mosquito, Vampire and Venom. Handley Page Appointments FOLLOWING the recent reorganization of the technical depart ment of Handley Page, Ltd., six re-appointments have been made. The technicians conceraed are Messrs. C. F. Joy, G. H Lee, R. H. Sandifer, C. O. Vernon, F. Tyson and K. C. Pratt. Their new posts, and the degrees, etc., which they hold, are given in the caption to their portraits below. Mr, Joy has been Handley Page's assistant chief designer since 1947, having joined the company eight years ago as assistant chief draughtsman. Previously, he was with A. W. Hawksley (1941-44), Gloster (1940-41), and Armstrong Whitworth Aircraft (1927-40). Mr. Lee joined Handley Page's in 1937, following a post-gradu ate aeronautics course at Imperial College and two-and-a-half years with Saunders-Roe (1934-37). In 1940 he was in charge of development of the "Manx flying wing and later was appointed research engineer. He became chief aerodynamicist in 1949. Mr. Sandifer joined the firm in 1927 after spending two years with Boulton-Paul Aircraft (1925-27) and was appointed chief stressman in 1939. During the past 25 years he has been associated with the design of eight production and five experimental types of H.P. aircraft. Mr. Vernon, a "Silver C " glider pilot, has been connected with the aerodynamics department since completing his apprenticeship with the company in 1935. He was appointed deputy chief of the aerodynamics department in 1949. Mr. Tyson, after taking a mathematics degree at Cambridge, went to the Fairey company's technical office in 1935, and spent a year on the technical staff of C. W. Aircraft, Slough, before joining Handley Page's stress office in 1938. He was appointed assistant chief stressman in 1947. Mr. Pratt joined Handley Page, Ltd., in 1934 and worked in the experimental department until 1938. He has been in charge of the test department since 1939. The subjects of the Handley Page appointments (see above) and the posts which they will occupy. (Left to right) C.F. Joy,A.F.R.Ae.S., deputy chief designer; G. H. Lee, A R.C.S., R.Sc, D.I.C., F.R.Ae.S., assistant chief de signer, aerodynamics; R. H. Sandifer, F.R.Ae.S., assistant chief designer, structures; C. 0. Vernon, A.F.R.Ae.S., chief aerodynamicist; F. Tyson, B.A., A.F.R.Ae.S., chief stressman; K. C. Pratt, A.M.l.Mech.E., A.F.R.AeS., de velopment and test engineer. Stainless-steel Flexible Piping VJ'ODERN aircraft power-plants are increasingly demanding -1"* the use of flexible hose with greater resistance to corrosive fluids at both lower and higher temperatures than can be obtained with ordinary synthetic-rubber hose. One of the most highly developed flexible-hose systems to meet these stringent require ments is the range of metallic assemblies manufactured by Avica Equipment, Ltd. (Avica Works, London N.7). This equipment is based on an electrically welded lightweight metal cored tube, convoluted into what is known as a "sylphon" form to provide greater flexibility. Over this core is wrapped either one or two layers of wire braiding to give the required mechanical strength and pressure-resistance. End couplings of a Afica standard-type SM.1 45-deg. angle coupling, and type SM coupling fitted with stand-pipe end, variety of types can be provided in light alloy, mild steel, stainless steel or brass. It is stated that such piping, in stainless steel, can be used in ambient temperatures of up to 350 deg C without ill effect. Working pressure is largely dependent upon whether one or two braids are specified, but will normally be up to 700 lb/sq in (corresponding bursting pressure 7,000 lb/sq in). One of the most important applications for such hose is the transmission of various fuels and oxidants in rockets and guided missiles. Other installations include the passage of water/methanol, hot air and use as engine drain-pipes. More stringent conditions are offered by engine cartridge-starter lines—in which, it is claimed, no other hose available can meet the requirements. The Avica company has issued a booklet describing the hose assemblies; it lists the range currently available and also includes guidance on the installation and care of the hose. Gas-turbine Ring Stretcher A NEW special-purpose tool is the "segmental sizing machine" developed by Daniel Smith, Ltd., Castle Iron Works, Wolverhampton. This apparatus is primarily used for stretching the stiffener-rings commonly employed in aircraft gas-turbines, both to bring the ring to exact size without distortion and also to provide a simple tensile test of the weld. A centrally mounted vertical pneumatic ram is employed to force a carefully profiled cam into the central orifice between a set of radial segments. The segments are moved radially out ward, rapidly at first, until their outer periphery meets the ring under test; the movement is then progressively arrested until, at full diameter, a period of dwell is provided to allow for ring elasticity. The expansion is adjustable from zero up to ^ in, while air con sumption of about ij cu ft per cycle is quoted; the maximum thrust is stated to be about 15 tons.
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