Question 6 At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the static pressure at the rotor's exit. [1.96 bar]
Question 6 At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the static pressure at the rotor's exit. [1.96 bar]
Chapter2: Loads On Structures
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![Question 6
At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar
and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow
angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if
both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the
static pressure at the rotor's exit. [1.96 bar]](/v2/_next/image?url=https%3A%2F%2Fcontent.bartleby.com%2Fqna-images%2Fquestion%2Ff2225437-fa64-4f56-99af-2e3142b592d7%2Ff68ae7e5-0555-4ad2-a5cd-5e8a38db4aea%2Fiig3jn_processed.png&w=3840&q=75)
Transcribed Image Text:Question 6
At the inlet of the nozzle of an axial gas turbine, the total pressure and total temperature are 6 bar
and 750 K, respectively. At the nozzle outlet, the static pressure is 3.4 bar and the absolute flow
angle is 65°. If the rotor angles and velocities are identical to those of the nozzle (i.e. 50% blading), if
both blades have an efficiency of 85%, and if the absolute rotor exit flow is purely axial, calculate the
static pressure at the rotor's exit. [1.96 bar]
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