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By I. E. Smith

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Extra info for Combustion in Advanced Gas Turbine Systems. Proceedings of an International Propulsion Symposium Held at the College of Aeronautics, Cranfield, April 1967

Example text

Such a snout has never progressed beyond the development stage on the Conway, but the principle had just been demonstrated as design work started on the Spey. 48 κ . G R A D O N A N D S . C. M I L L E R FIG. 4. Flame tube cooling devices. FIG. 5. Tubo-annular dilution zone. THE ROLLS-ROYCE S P E Y 49 ENGINE Also from the Conway came the pilot nozzle spray-bar configuration on the fuel burner known as the microcage which was added to the basic duple burner to give consistent ignition (see Fig. 7).

12. Since there is now no air bleed from the compressor, the work required from the high temperature turbine (Γχ) is lower than in the previous scheme 38 W. TIPLER H E = Heat e x c h a n g e r o t h e r symbols a s in figure II Compression ratio FIG. 1 2 . Thermal efficiency of high temperature gas turbine with intermediate high temperature heat exchanger. (Fig. 11). The exhaust gas temperature is greater than 900°C throughout the range considered. Deposit thickness on the turbine blading should therefore be kept within reasonable limits.

A New Gas Turbine Cycle Hitherto discussion has been limited to conventional gas turbines either alone or in conjunction with other cycles. In theory it appears that a solution of the ash problem might be obtained by the use of a turbine with cooled blading in the cycle discussed below. It was postulated that the thickness of ash deposits formed on a cooled surface would reach equilibrium at a thickness which could be calculated from the equation ^ _ k(T^ - Ό KT, - TJ C O M B U S T I O N IN I N D U S T R I A L GAS T U R B I N E S 35 where t = equiHbrium thickness of deposit, k = thermal conductivity of deposit, h = transfer coefficient between gas and deposit surface, Tg = temperature of the gas stream, = melting temperature of ash deposit, = temperature of cooled metal surface.

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