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THE HISTORICAL EVOLUTION OF TURBOMACHINERY

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298 PROCEEDINGS OF THE 29TH TURBOMACHINERY SYMPOSIUM Figure 43. Interference Diagram for Turbine Blading. (Voysey, 1945; Courtesy IMechE, UK) Figure 44. Impeller Failure Due to Fatigue. (Development of the British Gas Turbine Unit, 1945; Courtesy IMechE, UK) Figure 45. Disk Failure of Experimental Engine (De Laval Type Pin Blade Attachment) After 168 Run Hours. (Development of the British Gas Turbine Unit, 1945; Courtesy IMechE, UK) Figure 46. Cracking of Turbine Blade Root Serrations, W.1A Turbojet. (Development of the British Gas Turbine Unit, 1945; Courtesy IMechE, UK) Combustion Problems The first model of the experimental engine had severe problems with hot spots and improper heat distribution. Whittle made an attempt to utilize the primus principle and the single combustion chamber was fitted with a vaporizer. On this engine, poor compressor delivery pressure compounded the problem and diffusers were fitted to improve compressor performance. Numerous tests and modifications were attempted on the flame tubes, vaporizers, baffle systems, and spray patterns. Whittle (1945) states that in January 1939 alone, 10 types of vaporizers were tried in the combustion rig and nine flame tube modifications made. There were also problems with repeatability of results derived from the test rigs on the engine. Whittle struggled hard with the combustion problem until the fall of 1940 when Mr. Isaac Lubbock, head of Shell Fulham Laboratory who was advising Power Jets, developed and tested a combustor utilizing atomized spray injection. Power Jets continued development of this combustor, and from that point, the combustion problems diminished. A combustion chamber with a vaporizer as well as the Shell type combustion chamber are shown in Figure 47. The combustors and jet pipe end of the W.1X are depicted in Figure 48. More details of design related problems of the early jet engines may be found in Constant (1948). Other Turbojet Engine Developments in England In June 1941, The Bristol Engine Company undertook a survey of the gas turbine field and, by the spring of 1942, had completed the design for what would become the Theseus turboprop (Figure 49). Metropolitan Vickers worked on an axial RAE design that resulted in the F2 engine. De Havilland Aircraft Company worked on the development of the Goblin, which powered the Vampire fighter. The De Havilland Goblin is shown in Figure 50. A detailed description of axial gas turbine development work in England is made by Constant (1945). A lot of careful development work was done on axial compressors by Constant and his group, including the pioneering work of Howell, whose contributions are detailed in Dunham (2000). A small 6 inch diameter axial flow test compressor designated “Anne” is shown in Figure 51. The British even experimented with water-cooled turbine blading in the early 1940s, as can be seen in Figure 52. GERMAN JET ENGINE DEVELOPMENTS Turbojet development in Germany initially included two independent programs that were not, at least initially, under the auspices of the German Air Ministry known as the Riechluftfahrt- ministerium, or RLM for short. As is typical of revolutionary technological changes, these two programs did not initiate at the traditional aeroengine companies, but started at Heinkel Air- frame and at Junkers Airframe Company. Ultimately, both these

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