TESTING OF GAS TURBINE HIGH VELOCITY DUCT SYSTEMS.
Final rept. 1 Sep-31 Aug 66,
CATHOLIC UNIV OF AMERICA WASHINGTON D C DEPT OF MECHANICAL ENGINEERING
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A study is made of incompressible and subsonic compressible up to Mach number 0.4 flow losses associated with intake and exhaust ducting components and systems for shipboard boiler-turbine and gas turbine engines. An extensive literature survey is made to determine what design data are available and the areas where more design data are needed. A mathematical model covering one-dimensional diabatic and adiabatic gas flow is presented. Good comparisons are obtained between the model and laboratory tests for circular and square cross-sectional ducts with Mach numbers up to 0.4. Based on additional tests, new design data are presented in three areas Reynolds number effects on short-radius elbow pressure loss coefficients, subsonic Mach number at which compressibility effects on the elbow pressure loss coefficient begins, and how the position of an elbow in a system affects its pressure loss coefficient. Using data found in the literature and the new data mentioned above, a design data sheet for shipboard engine ducting systems is evolved. A good comparison is obtained between losses calculated using the design data sheet and a limited number of model systems tested in the laboratory. Author
- Marine Engineering
- Jet and Gas Turbine Engines