[4] A radial turbine is proposed as the gas expansion element of a nuclear powered Brayton cycle space power system. The pressure and temperature conditions through the stage at the design point are to be as follows: Upstream of nozzles, Poi = 699 kPa, ToI 1145 K; %3| Nozzle exit, P2 = 527.2 kPa, T2 = 1029 K; Rotor exit, P3 = 384.7 kPa, T3 = 914.5 K, T03 = 924.7 K. The ratio of rotor exit mean diameter to rotor inlet tip diameter is chosen as 0.5 and the required rotational speed as 24,000 rev/min. Assuming the relative flow at rotor inlet is radial and the absolute flow at rotor exit is axial, determine (i) the total-to-static efficiency of the turbine; (ii) the rotor diameter; (iii) the implied enthalpy loss coefficients for the nozzles and rotor row.

[4] A radial turbine is proposed as the gas expansion element of a nuclear powered Brayton cycle space power system. The pressure and temperature conditions through the stage at the design point are to be as follows: Upstream of nozzles, Poi = 699 kPa, ToI 1145 K; %3| Nozzle exit, P2 = 527.2 kPa, T2 = 1029 K; Rotor exit, P3 = 384.7 kPa, T3 = 914.5 K, T03 = 924.7 K. The ratio of rotor exit mean diameter to rotor inlet tip diameter is chosen as 0.5 and the required rotational speed as 24,000 rev/min. Assuming the relative flow at rotor inlet is radial and the absolute flow at rotor exit is axial, determine (i) the total-to-static efficiency of the turbine; (ii) the rotor diameter; (iii) the implied enthalpy loss coefficients for the nozzles and rotor row.

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

See similar textbooks

Similar questions

None
FINAL DISCUSSION IN ME 3215 COMBUSTION ENGINEERING PROBLEM: 1. (a) Find the optimum pressure ratio for maximum specific work a non- ideal air Gas Turbine cycle. Initial Temperature and pressure at 27 °C and 104 kPa, respectively. Turbine inlet Temperature is 1,800 °C. n7 = 90 %, nc = 85 %. Take č, = 1.005 and k = 1.4 for air. kg k (b) Evaluate this maximum specific work for the cycle. (c) Prove that this specific cycle work is a maximum.
For the given question determine optimum velocity of steam, asap
P = 10 MPa T= 600°C =0.2 MPa 2 21 C. For the actual turbine; mechanical efficiency,n = 84% and generator efficiency, ng= 93%, calculate: 6. Combined steam rate, w 7. Combined heat rate, kHR 8. Brake engine thermal efficiency, e 9. Brake engine efficiency, n
GA: In a reaction turbine, the angles of receiving tips are 35° and of discharging tips, 20°. The blade speed is 100 m/s. Calculate the tangential force, power developed, diagram efficiency, and axial thrust of the turbine, if its steam consumption is 1 kg/min. Draw the velocity diagram on scale. B: What are the objects of using the condensers in steam plants?
4. For Francis turbine with the following specifications: Paev= 225 MW, H=250 m, nov= 90 % , If the velocity of water at spiral case entering =24 m/s, and the volumetric efficiency is 0.98, thus the diameter of the spiral case entering is: a. 2.3 m. b. 2.8 m. c. 3.1 m. d. 3.6 m. e. None of them.
An ideal reheat turbine with one stage of reheat receives steam at 8.0 Mpa, 480 °C. Reheat pressure is 0.83 Mpa and exhaust pressure is 0.007 Mpa. The work is 1559 kJ/kg and thermal efficiency is 41.05%. h2 = || kJ/kg h3 = kJ/kg t3 = °C Continue >
A single acting two-stage air compressor deals with 4 m^3/min of air under atmospheric conditions of 1.013 bar and 15°C with aspced of 250r.p.m. The delivery pressure is 80 bar. Assuming complete inlercooling, find the minimum power required by the compressor and the bore and stroke of the compressor. Assume a pistonspeed of 3 m/s, mechanical efficiency of 75 percent, and volumetric efficiency of 80 percent per stage. Assumethe polytropic index of compression in both the stages to be it = 1.25 and neglect clearance.
Q - The rotor of an impulse turbine is 60 cm diameter and runs at 9,600 r.p.m. The nozzles are at 20° to the plane of the wheel, and the steam leaves them at 600 m/sec. The blades outlet angle are 30° and the friction factor is 0.8. Calculate the power developed per kg of steam per second and the diagram efficiency.
The first stage of a turbine is a two-row velocity compounded wheel. Steam at 40 bar and 400 C is expanded in the nozzles to 15 bar, and has a velocity at discharge of 700 m/s. The inlet velocity to the stage is negligible. The relevant exit angles are: nozzle 18°; first row blades 21°; fixed blades 26.5"; second row blades 35°. Take the blade velocity coefficient for all blades as 0.9. The mean diameter of the blading is 750 mm and the turbine shaft speed is 3000 rev/min. Draw the velocity diagram for this whel and calculate: (i) the diagram efficiency; (ii) the stage efficiency. (70.8%; 67.4%)
Q4// The nozzles of the impulse stage of turbine receive steam at 15 bar, 300 °C and discharge it at 10 bar. The nozzle efficiency is 95 % and the nozzle angle is 20°. The blade speed is that required for maximum power and the inlet angle of the blades is that required for entry of steam without shock .the blade exit angle is 5° less than the inlet angle. The blade velocity coefficient is 0.9. Calculate for steam flow rate 1350 kg/hr: 1. The diagram power. Answer (30.3 kW , 86.3 % ) 2. The diagram efficiency.
There are two turbine stages with a reheater in between, as shown below and the following conditions are provided. Assume the mass flow rate of air = 1 Kg/s. Turbine stage 1 Stream 1 2 3 4 Reheat combustor P (kPa) T (K) 1200 350 350 100 1200 1200 3 Turbine stage 2 h (kJ/kg) W cycle • Determine the total work developed, which is the sum of the work developed by the first stage and the work developed in the second stage. • Determine the heat added in the reheater. • If the reheat is turned off, streams 2 and 3 no longer exist and we go directly from 1 to a new state at stream 4. What is h4 and what is the work generated in the turbine in this case?