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![Rd). V (tean Al + tan B.) 0.5 = { varan (B) + teks)] بدع t dan (x1) + tan (B) = tan (22) dan (B) 02 B and [82 =21 40° 22: BI](http://img.homeworklib.com/questions/88fb4350-e908-11ea-a0ca-396e5d8fde84.png?x-oss-process=image/resize,w_560)
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15 Q4 (15 Marks) An axial flow compressor stage is...
An axial flow compressor stage is downstream of an IGV that turns the flow 15° in...
An axial flow compressor stage is downstream of an IGV that turns the flow 15° in the direction of the rotor rotation, as shown in figure 1. The axial velocity component remains constant throughout the stage at Cz = 150 M/S. The rotor rotational speed w = 3000 rpm and the pitchline radius is rm=0.5 m. The rotor relative exit flow angle is B2=-15°. The static temperature and pressure of air upstream of the rotor are T1 = 20°C and...
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...
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...
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
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...
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...
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,...
Problem 10.4 aircraft propulsion farokhi A turbine stage is designed with a constant axial velocity of...
Problem 10.4 aircraft propulsion farokhi
A turbine stage is designed with a constant axial velocity of
250 m/s and zero exit swirl. For a rotor rotational speed Um at the
pitchline of 600 m/s. Calculate and comment on your results
a) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.50
b) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.0
c) the rotor specific work at the pitchline radius, for ◦Rm =
0.50 and...
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...
Q2 Figure 2.1 shows the velocity diagram for an axial turbine stage. The turbine rotor blade...
Q2 Figure 2.1 shows the velocity diagram for an axial turbine stage. The turbine rotor blade speed is 80 m's. Exhaust gas flow through the turbine stage with a constant axial velocity (2) at 90 m/s. List of relative and absolute flow angles at the rotor inlet and outlet are given in APPENDIX D for each student, respectively. At rotor inlet At rotor outlet B3 Cx2 = 90 m/s B2 Cx3 = 90 m/s W2 0.3 Cys 44 U =...
An axial flow compressor stage is downstream of an IGV that turns the flow 15° in the direction of the rotor rotation, as shown in figure 1. The axial velocity component remains constant throughout the stage at Cz = 150 M/S. The rotor rotational speed w = 3000 rpm and the pitchline radius is rm=0.5 m. The rotor relative exit flow angle is B2=-15°. The static temperature and pressure of air upstream of the rotor are T1 = 20°C and...
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...
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...
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
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...
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,...
Problem 10.4 aircraft propulsion farokhi
A turbine stage is designed with a constant axial velocity of
250 m/s and zero exit swirl. For a rotor rotational speed Um at the
pitchline of 600 m/s. Calculate and comment on your results
a) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.50
b) the nozzle exit flow angle, ?2 in degrees for ◦Rm = 0.0
c) the rotor specific work at the pitchline radius, for ◦Rm =
0.50 and...
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...
Q2 Figure 2.1 shows the velocity diagram for an axial turbine stage. The turbine rotor blade speed is 80 m's. Exhaust gas flow through the turbine stage with a constant axial velocity (2) at 90 m/s. List of relative and absolute flow angles at the rotor inlet and outlet are given in APPENDIX D for each student, respectively. At rotor inlet At rotor outlet B3 Cx2 = 90 m/s B2 Cx3 = 90 m/s W2 0.3 Cys 44 U =...
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