Calculate the turbine nozzle (or stator) throat area for the following specifications: T0= 1600K P0=10 bar...
Calculate the turbine nozzle (or stator) throat area for the following specifications:
T0= 1600K
P0=10 bar
Mass flow rate = 18 kg/s
C1(at the throat) = 650 m/s (assumed to be uniform in the entire throat cross-section)
Gas constant = 286.66 J/kg/K
Homework Answers
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Calculate the turbine nozzle (or stator) throat area for the
following specifications:
T0= 1600K
P0=10 bar...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
A nozzle is designed to deliver a supersonic air flow, R = 287 J/Kg/K, of Mach...
A nozzle is designed to deliver a supersonic air flow, R = 287 J/Kg/K, of Mach M = 2.19 The reservoir has a pressure of p0 = 648kPa and T0= 300K. The nozzle exit has an area of 0.233 m^2. The nozzle flow exits into an environment that is kept at constant pressure pb which matches the exit pressure of the nozzle. As long as there are no shock waves appearing in – or outside the nozzle, the complete flow...
ANSWER [0.54 and 1.63] (b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to b...
ANSWER [0.54 and 1.63]
(b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K.
(b) Air flows through a converging-diverging...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm...
Fundamentals-of-Compressible-Fluid-Dynamics Balachandran CHAPTER 4 6. A conical diffuser of 15 cm has an area ratio of 4. If the pressure, temperature and velocity at the inlet section are 0.69 bar, 340 K and 180 m/s, estimate the exit pressure and exit velocity. What will be the change in impulse function. [Ans. p2 = 0.8074 bar; V2 = 45 m/s; F2 - F1 = 4167.5 N] 7. The Mach number at inlet and exit of a supersonic diffuser are 3 and...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 321 Inlet pressure: P1 (kPa) = 588 Inlet Velocity: V1 (m/s) = 97 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
c) A nozzle in a wind tunnel gives a test-section Mach number of 2.0. Alr etes th nozzle from a large reservoir at 0,69 bar and 310 K. The cross-sectional area of the throat is 1000 cm2. Determine the following quantities for the tunnel for one dimensional isentropic flow i) Pressures, temperature and velocities at the throat and test sections, i) Area of cross-section of the test section, Sim) Mass flow rate, F rate required to drive the compressor
c)...
ANSWER [0.54 and 1.63]
(b) Air flows through a converging-diverging nozzle. At point "A" in the converging section, the cross-sectional area is 50 cm2 and the Mach number was measured to be 0.4. At point "B" in the diverging section, the cross-sectional area is 40 cm2. Find the possible Mach numbers at point "B" Assume that the flow is isentropic and the air specific ratio γ-1.4 and the gas constant R: 287 J/kg K.
(b) Air flows through a converging-diverging...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 353 Inlet pressure: Pl (kPa) = 546 Inlet Velocity: V1 (m/s) = 61 Area at nozzle inlet: A1 (cm^2) = 7.24...
B4 (a) Ste the parameter that is normally used to differentiate between incompressible and compressible flow conditions. What value is normally chosen for this parameter to signify a change from one condition to another? (5%] For isentropic flow conditions, sketch a subsonic and a supersonic nozzle (b) Sketch also a subsonic and a supersonic diffuser. [1096] (c) A converging-diverging nozzle is attached at one end to a large supply tank that contains air, and at the other end to a...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) 370 Inlet pressure: P1 (kPa) = 576 Inlet Velocity: V1 (m/s) - 106 Area at nozzle inlet: A1 (cm^2) = 8.32...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Solve using equations rather than with the tables. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 348 Inlet pressure: P1 (kPa) = 544 Inlet Velocity: V1 (m/s) = 122 Area at nozzle inlet: A1 (cm^2) =...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
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