Combustion in Advanced Gas Turbine Systems. Proceedings of by I. E. Smith

By I. E. Smith

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Additional 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

It was the influence of the Avon which was the most strongly felt. F r o m that engine came the principles of flame tube cooling—the hemispherical flare and the discharge nozzle by splash cooling strips, and the body of the flame tube by wigglestrips (see Fig. 4). Further, Avon work had demonstrated the necessity for a sphtter and back stop system in the annulus to control the difficult dilution airflow problems on a tubo-annular design (see Fig. 5). From the Conway came the idea of the common entry snout to give a uniform annulus velocity distribution.

TiPLER, W. Combustion in European Industrial Gas Turbines. E. Paper N o . 61-WA-82. 3. LUBBOCK, I. Combustion Problems of the Gas Turbine. Trans. North-East Coast Institution of Engineers and Shipbuilders, 6 7 , 1951, 131. 4. TiPLER, W. The Present Position and Future Prospects concerning the use of Residual Fuel Oils in Gas Turbines. Revue (M) de Mecanique, 4, N o . 3, 1958, 171. 5. TiPLER, W. Combustion Chambers and Control of the Temperature at which they operate. Proc. Joint Conf. E. and I.

2) is an interesting example to investigate because it will probably be the last Rolls-Royce tubo-annular design. As the last, it has inherited the 45 κ . GRADON AND S. C . MILLER 46 nntsNtT FIG. 1. Rolk-Royce Spey engine. 0ISCHAR6E NOZZLE OUPIE SNOU FIG. 2. Spey combustion system. THE ROLLS-ROYCE SPEY ENGINE 47 experience of previous tubo-annular systems, which in turn drew on the experi­ ence gained with the earlier tubular designs. 141, which was an engine of approxi­ mately 14,000 lb thrust.

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