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
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 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 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...
throat area of 0.25m2 and exit to throat area ratio (Ae/At) of 35.5 are measured to be 1500 kPa and 3000 K respectively. Assuming that the combustion product is steam ( 1.33, R 461.52 J/kg K), calculate the following: (e) The radius of the throat and exi plane of the nozde if the nozle has a circular cos- section. (b) The nozzle-exit plane conditions, i.e. Mach number, mass flow rate, velocity, pressure, าน temperature, and density. (c) The thrust and...
A converging-diverging nozzle has a throat area of 1 cm2 and an exit area of 4 cm2. The inlet stagnation conditions are Po 500 kPa and To 300 K. The nozzle discharges to an infinite surroundings at Po. The flowing medium is air as a perfect gas with k-1.4 Answer the following: i What are the two isentropic flow solutions for this nozzle with M 1 at the throat? What are the Mach number, P, Po and T, To at...
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 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...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
1. (15 pts) A converging-diverging nozzle has an area ratio of 2, i.e., the exit (or duct) area is 2 times the throat area, which is 80 cm2. The nozzle is supplied from a tank containing air (y 1.4 and R 287 J/kg K) at 100 kPa and 300K. For both cases shown in Fig. , find the maximum mass flow possible through the nozzle and the range of back pressures over which the mass flow can be attained. For...
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...
Air expands through a turbine from 8 bar, 960 K to 1 bar, 450 K. The inlet velocity is small compared to the exit velocity of 90 m/s. The turbine operates at steady state and develops a power output of 2500 kW. Heat transfer between the turbine and its surroundings and potential energy effects are negligible. Modeling air as an ideal gas, calculate the mass flow rate of air, in kg/s, and the exit area, in m2.