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A major objective in advancing gas turbine engine technologies is to increase the temperature limit associated with operation of the gas turbine blades

 A major objective in advancing gas turbine engine technologies is to increase the temperature limit associated with operation of the gas turbine blades. This limit determines the permissible turbine gas inlet temperature, which, in turn, strongly influences overall system performance. In addition to fabricating turbine blades from special, high-temperature, high-strength superal- loys, it is common to use internal cooling by machining flow channels within the blades and routing air through the channels. We wish to assess the effect of such a scheme by approximat- ing the blade as a rectangular solid in which rectangular channels are machined. The blade, which has a thermal conductivity of k- 25 W/m-K, is 6 mm thick, and each channel hasa 2 mm × 6 mm rectangular cross section, with a 4-mm spacing between adjoining channels. Air channel Combustion gases 2 mm 6 mm 6 mm 4 mm CombustionTo Turbine blade, k gases EXAMPLE 4.3 A major objective in advancing gas turbine engine technologies is to increase the temperature limit associated with operation of the gas turbine blades. This limit determines the permissible turbine gas inlet temperature, which, in turn, strongly influences overall system performance. In addition to fabricating turbine blades from special, high-temperature, high-strength superal- loys, it is common to use internal cooling by machining flow channels within the blades and routing air through the channels. We wish to assess the effect of such a scheme by approximat- ing the blade as a rectangular solid in which rectangular channels are machined. The blade, which has a thermal conductivity of k- 25 W/m-K, is 6 mm thick, and each channel hasa 2 mm × 6 mm rectangular cross section, with a 4-mm spacing between adjoining channels. Air channel Combustion gases 2 mm 6 mm 6 mm 4 mm CombustionTo Turbine blade, k gases

Apr 27 2020 View more View Less

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