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 be less than 0.4 in all stages, eight stages are required. b. The compressor is designed with repeating stages and zero inlet swirl. If the inlet axial Mach number is 0.52, calculate the mean flow coefficient and sketch the velocity triangles for one stage. Show that the blade height at exit from the compressor is about 7.8 mm.
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A high-pressure axial compressor for a jet engine rotates at
15,000 rpm with an overall stagnation...
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...
Q2) an axial compressor takes air axially (no swirl) from ambient at a total temperature of 27° a...
Q2) an axial compressor takes air axially (no swirl) from ambient at a total temperature of 27° and atmospheric pressure (tota of 101.3 kPa. The air is compressed to a total pressure of 121.56 kPa. The blade hub radius is 28 cm and the flow area is 0.1 m2. The shaft speed is 7000 rpm. The rotor turns the relative flow velocity 15°. The inlet relative flow angle is-60°. Determine (a) the mean radius (b) the relative and absolute velocity...
A one stage axial air compressor consists of a rotor and a stator, it has a...
A one stage axial air compressor consists of a rotor and a stator, it has a mean diameter of Im for the rotor and a rotational speed of 7645 RPM. Furthermore: Mass flow rate is 50 kg/s .Inlet static temperature and pressure of Ti 276 K and Pi 85 kPa. .Inlet stagnation temperature and pressure of Toi 290 K and Poi 101.3 kPa. .Inlet absolute velocity C1 166.5 m/s Rotor exit static density (p2) equals to 1.3kg/m3 Axial component of...
)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).
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
mass flow rate 15 kh/s DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013...
mass flow rate 15 kh/s
DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013 kPa Inlet Stagnation Temperature 1200 K Mean Blade Diameter 25 cm Rotor Speed 26,500 rpm Fou usbine Axial Velocity- 180 m/s inlet to Rotor Angle, α= 700 Exit Rotor Angle as 0 Assuming variable specific heats and the axial velocity remains constant; (a) Construct the velocity diagrams for the stage (b) Calculate work, Aw (c) The power developed based on the mean blade diameter,...
15.04 Axial flow compressor blade angles are: a fixed and are correct for take off RPM...
15.04 Axial flow compressor blade angles are: a fixed and are correct for take off RPM b variable and are correct for take off RPM roc fixed and are incorrect for take off RPM 15.08 A labyrinth seal between compressor stages 8 and 9: . a allows air to flow from 8th stage to oth stage b does not allow air to flow C allows air to flow from 9ch to 8th stage
C) Axial-flow compressor Answer 3) Specifie speed (0.) for the compressor compressor should selected? application is 0.9. Which of the following type of 52 th Reciprocating compressor B) none of t...
C) Axial-flow compressor Answer 3) Specifie speed (0.) for the compressor compressor should selected? application is 0.9. Which of the following type of 52 th Reciprocating compressor B) none of these A) Centrifug al compressor 1,) compressor D) Centrifugal fan 6) &7) The compressor is tested at sea level on a stationary atmospheric temperature and pressure is design operating point, the mass flow rate through the compr rotational speed is 7000 rpm. Determine the flow compressor is operating at the...
TQi The rotor and stator rows arrangement of an axial compressor stage and their general velocity...
TQi The rotor and stator rows arrangement of an axial compressor stage and their general velocity diagrams are shown in Figure 1.1 (a) and (b), respectively. The compressor rotor blade speed is set at 100 m's and the inlet absolute flow velocity for rotor (C1) and stator (C:) are given in APPENDIX A (Each student will have different data) Consider normal stage condition and constant axial flow throughout the stage at 50 m's 01 C 0 SS 93 ROTOR t=100...
Question 3 Consider an axial compressor with blades installed at given angle with respect to inco...
Question 3 Consider an axial compressor with blades installed at given angle with respect to incoming airflow The ccmpressor has diameter of 1.0 m and rotates at 3000 rpm. Air mass flow rate through compre sso is 110 kg/s. Pressure and temperature of air at the inlet of the compressor are 1 atm and 300K. Compressor blades are installed at 50° with respect to the axial plane. Conclude whether this compressor can operate at the designed speed of 3000 rpm....
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...
Q2) an axial compressor takes air axially (no swirl) from ambient at a total temperature of 27° and atmospheric pressure (tota of 101.3 kPa. The air is compressed to a total pressure of 121.56 kPa. The blade hub radius is 28 cm and the flow area is 0.1 m2. The shaft speed is 7000 rpm. The rotor turns the relative flow velocity 15°. The inlet relative flow angle is-60°. Determine (a) the mean radius (b) the relative and absolute velocity...
A one stage axial air compressor consists of a rotor and a stator, it has a mean diameter of Im for the rotor and a rotational speed of 7645 RPM. Furthermore: Mass flow rate is 50 kg/s .Inlet static temperature and pressure of Ti 276 K and Pi 85 kPa. .Inlet stagnation temperature and pressure of Toi 290 K and Poi 101.3 kPa. .Inlet absolute velocity C1 166.5 m/s Rotor exit static density (p2) equals to 1.3kg/m3 Axial component of...
mass flow rate 15 kh/s
DATA: Mass Flow Rate 15 kg/s Inlet Stagnation Pressure = 1013 kPa Inlet Stagnation Temperature 1200 K Mean Blade Diameter 25 cm Rotor Speed 26,500 rpm Fou usbine Axial Velocity- 180 m/s inlet to Rotor Angle, α= 700 Exit Rotor Angle as 0 Assuming variable specific heats and the axial velocity remains constant; (a) Construct the velocity diagrams for the stage (b) Calculate work, Aw (c) The power developed based on the mean blade diameter,...
15.04 Axial flow compressor blade angles are: a fixed and are correct for take off RPM b variable and are correct for take off RPM roc fixed and are incorrect for take off RPM 15.08 A labyrinth seal between compressor stages 8 and 9: . a allows air to flow from 8th stage to oth stage b does not allow air to flow C allows air to flow from 9ch to 8th stage
C) Axial-flow compressor Answer 3) Specifie speed (0.) for the compressor compressor should selected? application is 0.9. Which of the following type of 52 th Reciprocating compressor B) none of these A) Centrifug al compressor 1,) compressor D) Centrifugal fan 6) &7) The compressor is tested at sea level on a stationary atmospheric temperature and pressure is design operating point, the mass flow rate through the compr rotational speed is 7000 rpm. Determine the flow compressor is operating at the...
TQi The rotor and stator rows arrangement of an axial compressor stage and their general velocity diagrams are shown in Figure 1.1 (a) and (b), respectively. The compressor rotor blade speed is set at 100 m's and the inlet absolute flow velocity for rotor (C1) and stator (C:) are given in APPENDIX A (Each student will have different data) Consider normal stage condition and constant axial flow throughout the stage at 50 m's 01 C 0 SS 93 ROTOR t=100...
Question 3 Consider an axial compressor with blades installed at given angle with respect to incoming airflow The ccmpressor has diameter of 1.0 m and rotates at 3000 rpm. Air mass flow rate through compre sso is 110 kg/s. Pressure and temperature of air at the inlet of the compressor are 1 atm and 300K. Compressor blades are installed at 50° with respect to the axial plane. Conclude whether this compressor can operate at the designed speed of 3000 rpm....
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