Consider a 5-stage axial compressor. From the stator outlet of one stage, to the rotor inlet...
Consider a 5-stage axial compressor. From the stator outlet of one stage, to the rotor inlet of the next stage. Maintaining continuity, what changes and what is generally assumed constant? (total pressure and temperature, static pressure and temperature, density, absolute flow angle (alpha), relative flow angle (beta), axial velocity, etc
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Consider a 5-stage axial compressor. From the stator outlet of
one stage, to the rotor inlet...
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...
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...
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...
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...
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...
P 8.1 (100 points) The stator exit flow angle in an axial steam turbine is 69o....
P 8.1 (100 points) The stator exit flow angle in an axial steam turbine is 69o. The flow angle of the relative velocity leaving the rotor is 65°. Steam leaves the stator at V2- 190 m/s, and the axial velocity is Vx2 0.46U. At the exit of the rotor blades the axial steam velocity is V-0.45U. The mass flow rate is m2-2.2 kg/s. Draw the velocity triangles and find (a) the flow angle of the relative velocity entering the rotor;...
The axial flow steam turbine rotor shown in Fig. P12.69 has a blade outer radius RO 2.40 ft, a blade inner radius Ri 2.00 ft, a steam inlet pressure p1 200 psia, a steam inlet density p1- 0.296 lbm/t...
The axial flow steam turbine rotor shown in Fig. P12.69 has a blade outer radius RO 2.40 ft, a blade inner radius Ri 2.00 ft, a steam inlet pressure p1 200 psia, a steam inlet density p1- 0.296 lbm/t3, and an inlet absolute velocity V1 1000 f/s making an angle of 70° with the axial direction. The steam outlet pressure p2 50 psia and outlet density is 0.1014 Ibm/t3. B2 40 The rotor rotates at 3600 rpm. Using a blade...
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 =...
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...
5.3 An axial-flow fan rotor with the dimensions shown is rotating at 1800rpm. Draw the velocity d...
5.3 An axial-flow fan rotor with the dimensions shown is rotating at 1800rpm. Draw the velocity diagrams at the mean radii of both the inlet and outlet at the design condition. Estimate the lift coefficient, the design flow rate, and the ideal static pressure rise across the rotor at the mean radius. Neglect the flow interference between the blades. -6.0 in-4.6 in 2-6 -45 in Page 12 of 16
5.3 An axial-flow fan rotor with the dimensions shown is rotating...
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...
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...
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...
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...
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...
P 8.1 (100 points) The stator exit flow angle in an axial steam turbine is 69o. The flow angle of the relative velocity leaving the rotor is 65°. Steam leaves the stator at V2- 190 m/s, and the axial velocity is Vx2 0.46U. At the exit of the rotor blades the axial steam velocity is V-0.45U. The mass flow rate is m2-2.2 kg/s. Draw the velocity triangles and find (a) the flow angle of the relative velocity entering the rotor;...
The axial flow steam turbine rotor shown in Fig. P12.69 has a blade outer radius RO 2.40 ft, a blade inner radius Ri 2.00 ft, a steam inlet pressure p1 200 psia, a steam inlet density p1- 0.296 lbm/t3, and an inlet absolute velocity V1 1000 f/s making an angle of 70° with the axial direction. The steam outlet pressure p2 50 psia and outlet density is 0.1014 Ibm/t3. B2 40 The rotor rotates at 3600 rpm. Using a 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 =...
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...
5.3 An axial-flow fan rotor with the dimensions shown is rotating at 1800rpm. Draw the velocity diagrams at the mean radii of both the inlet and outlet at the design condition. Estimate the lift coefficient, the design flow rate, and the ideal static pressure rise across the rotor at the mean radius. Neglect the flow interference between the blades. -6.0 in-4.6 in 2-6 -45 in Page 12 of 16
5.3 An axial-flow fan rotor with the dimensions shown is rotating...
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