)An axial-flow turbine operating with an overall stagnation pressure of 8to 1 has a polytropic efficiency...
)An axial-flow turbine operating with an overall stagnation pressure of 8to 1 has a polytropic efficiency of 0.85. Determine the total-to-total efficiency of the turbine.b)If the exhaust Mach number of the turbine is 0.3, determine the total-to-static efficiency.c)If, in addition, the exhaust velocity of the turbine is 160 m/s, determine the inlet total temperature.Assume for the gas that Cp=1.175 kJ/(kg K) and R=287 kJ/(kg K).
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)An axial-flow turbine operating with an overall stagnation
pressure of 8to 1 has a polytropic efficiency...
A high-pressure axial compressor for a jet engine rotates at 15,000 rpm with an overall stagnation...
A high-pressure axial compressor for a jet engine rotates at 15,000 rpm with an overall stagnation pressure ratio of 8.5. The mass flow rate of air through the compressor is 16 kg/s and the stagnation conditions at inlet are 200 kPa and 450 K. The polytropic efficiency is 91%. a. If the mean radius is 0.24 m and this is constant throughout the compressor, calculate the total-to-total isentropic efficiency of the compressor and show that, for the stage loading to...
The isentropic efficiency of an axial flow compressor from the following data, pressure ratio=6, polytropic efficiency=0.85,inlet...
The isentropic efficiency of an axial flow compressor from the following data, pressure ratio=6, polytropic efficiency=0.85,inlet temperature=285K
Hi Can you please solve the question? Regards QUESTION 8 On a Mollier diagram show all the stagnation and static points...
Hi
Can you please solve the question?
Regards
QUESTION 8 On a Mollier diagram show all the stagnation and static points required to represent the complete flow process in a diffuser. Air enters a diffuser with an average velocity of 375 m/s at a stagnation pressure and temperature of 360 kPa and 470 K respectively and leaves at a stagnation pressure of 300 kPa with an average velocity of 120 m/s and a static pressure of 280 kPa. Determine (i)...
TURBO MACHINES SUBJECT QUESTION 10 A multi-stage high -pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa and a stagnation temperature of 500°C. The corresponding specifi...
TURBO MACHINES SUBJECT
QUESTION 10 A multi-stage high -pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa and a stagnation temperature of 500°C. The corresponding specific enthalpy is 3410kJ.kg. The steam exhaust from the turbine at a stagnation pressure of 0.7 MPa abs., the steam having been in a super-heated condition throughout the expansion. It can be assumed that the steam behaves like a perfect gas over the range of the expansion and that v...
A gas-turbine power plant operating on an ideal Brayton cycle has a pressure ratio of 9....
A gas-turbine power plant operating on an ideal Brayton cycle has a pressure ratio of 9. The gas temperature is 438 K at the compressor inlet and 1582 K at the turbine inlet. Utilizing the air-standard assumptions (A-17 tables), determine (1) The gas temperature at the exit of the compressor K (2) The gas temperature at the exit of the turbine K (3) Work input to the compressor kJ/kg (4) Work output of the turbine kJ/kg (5) Total heat input...
Consider the flow of combustion gases, withyand R 287 J/(kg K), through a normal turbine stage (G-constant, αι α3.rn-constant), such that the flow angle at the exit of the rotor is the same as...
Consider the flow of combustion gases, withyand R 287 J/(kg K), through a normal turbine stage (G-constant, αι α3.rn-constant), such that the flow angle at the exit of the rotor is the same as that entering the stator, and q a,- 3 14.4o. The inlet total temperature is To1 1200K. The axial velocity is constant cx- 280 m/s. The flow leaves the stator at angle α2 = 57.70. The mean radius of the rotor sr 17 cm, and the rotor...
The following data is given for a Francis turbine with an axial discharge Overall efficiency Hydraulic...
The following data is given for a Francis turbine with an axial discharge Overall efficiency Hydraulic efficiency Power produced Net head 75 % 78 % 148.25 kW 7.62 m 3.179 m/s The wheel peripheral velocity at inlet The radial velocity of the flow at inlet The runner diameter at inlet 11.738 m/s 0.4047 m The guide blade angle (with respect to the radial direction) is 57.4 36 5 30.8 28.8 e following data is given for a Fra... The following...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor ro...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
Question A.1 A schematic of a gas turbine combined cycle generating plant is shown in Figure...
Question A.1 A schematic of a gas turbine combined cycle generating plant is shown in Figure A1.1 on the next page. Exhaust gas from the gas turbine generator pass througha heat recovery steam generator (HRSG) which generates steam to drive a steam turbine generator. The following data is provided for the plant: Gas turbine 18.9:1 Pressure ratio Compressor air inlet temperature Turbine inlet temperature 15°C t 273 288 1350°C +273- 1623 588 kg/s T, T3 Exhaust gas mass flow Isentropic...
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio...
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall...
Hi
Can you please solve the question?
Regards
QUESTION 8 On a Mollier diagram show all the stagnation and static points required to represent the complete flow process in a diffuser. Air enters a diffuser with an average velocity of 375 m/s at a stagnation pressure and temperature of 360 kPa and 470 K respectively and leaves at a stagnation pressure of 300 kPa with an average velocity of 120 m/s and a static pressure of 280 kPa. Determine (i)...
TURBO MACHINES SUBJECT
QUESTION 10 A multi-stage high -pressure steam turbine is supplied with steam at a stagnation pressure of 7 MPa and a stagnation temperature of 500°C. The corresponding specific enthalpy is 3410kJ.kg. The steam exhaust from the turbine at a stagnation pressure of 0.7 MPa abs., the steam having been in a super-heated condition throughout the expansion. It can be assumed that the steam behaves like a perfect gas over the range of the expansion and that v...
Consider the flow of combustion gases, withyand R 287 J/(kg K), through a normal turbine stage (G-constant, αι α3.rn-constant), such that the flow angle at the exit of the rotor is the same as that entering the stator, and q a,- 3 14.4o. The inlet total temperature is To1 1200K. The axial velocity is constant cx- 280 m/s. The flow leaves the stator at angle α2 = 57.70. The mean radius of the rotor sr 17 cm, and the rotor...
The following data is given for a Francis turbine with an axial discharge Overall efficiency Hydraulic efficiency Power produced Net head 75 % 78 % 148.25 kW 7.62 m 3.179 m/s The wheel peripheral velocity at inlet The radial velocity of the flow at inlet The runner diameter at inlet 11.738 m/s 0.4047 m The guide blade angle (with respect to the radial direction) is 57.4 36 5 30.8 28.8 e following data is given for a Fra... The following...
ta Vew Wiadcw Helpr Home Tocls 101 2019.0.Cot QUESTION 9 In a jet engine rotor the high pressure axial compressor rotates at a speed of 15000 rpm. The overall stagnation pressure ratio due to compression is 10.1, it was recorded that the air flows at a rate of 16 kg/s. The stagnation properties at the inlet are 215 kPa and 460K. The poly-tropic efficiency of the compressor is 90%. Assume the mean radius of the compressor is constant and equal...
Question A.1 A schematic of a gas turbine combined cycle generating plant is shown in Figure A1.1 on the next page. Exhaust gas from the gas turbine generator pass througha heat recovery steam generator (HRSG) which generates steam to drive a steam turbine generator. The following data is provided for the plant: Gas turbine 18.9:1 Pressure ratio Compressor air inlet temperature Turbine inlet temperature 15°C t 273 288 1350°C +273- 1623 588 kg/s T, T3 Exhaust gas mass flow Isentropic...
A single-spool turbofan engine has the following data Ambient temperature Ambient pressure BPR Overall pressure ratio Fan pressure ratio Fuel heating value Turbine inlet temperature Diffuser pressure recovery factor Compressor efficiency Fan efficiency Combustion efficien Burner pressure recovery factor Turbine efficiency Nozzle efficiency Flight Mach number 288 K 101.3 kN/m2 0.7 25 3.375 44,000 kJ/kg 2000 K 0.9 0.89 0.91 0.98 0.95 0.98 1.0 0.3 Calculate 1. 2. 3. Thrust per unit mass flow rate TSFC Thermal, propulsive and overall...
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