Early commercial vapor power plants operated with turbine inlet conditions of about 12 bar and 200C. ants are under development today that can operate at over 34 MPa, with turbine inlet temperatures 650C or higher. How have steam generator and turbine designs changed over the years to allow for 1 Dienue

Early commercial vapor power plants operated with turbine inlet conditions of about 12 bar and 200C. ants are under development today that can operate at over 34 MPa, with turbine inlet temperatures 650C or higher. How have steam generator and turbine designs changed over the years to allow for 1 Dienue

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

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Pls. answer thank you! The following performance data were generated by a gas turbine having intercooling: LP compressor inlet conditions of 14.7 psia and 520’’R: LP compressor isentropic discharge temperature, 743.8 R. compressor isentropic efficiency. 78 percent; HP.compressor inlet temperature, S20 degree R: HP compressor isentropic discharge temperature, 743.8 R. HP compressor isentropic efficiency, 82%; turbine inlet temperature, 2000R; and turbine isentropic efficiency, 90%, Calculate the net cycle work Btu/lb.
7.15. A steam turbine operates adiabatically at a power level of 3500 kW. Steam enters the turbine at 2400 kPa and 500°C and exhausts from the turbine as saturated vapor at 20 kPa. What is the steam rate through the turbine, and what is the turbine efficiency?
Based on a gas turbine with superheat and intercooling, determine: 1) The thermal efficiency (ƞterm), in %. Use the expression ƞterm= 1 –(qL/ qH)2) How does gas turbine intercooling influence thermal efficiency?3) How and why? It is said that the gas turbine cycle with intercooling, reheating and regeneration is close to the Ericsson cycle.
An isentropic turbine has air entering the turbine where h = 1855.50 kJ/kg, p = 4.0 MPa and so = 3.58335 kJ/(kg · K). If the air leaves the turbine at a temperature of 397 °C, what is the final pressure and the specific work output of the turbine with variable specific heats [R = 0.287 kJ/(kg•K)]?
For example, suppose you had 5.0 kg/s of water at 1 MPaa and 500 degrees Celsius that enters an ideal steadystate, steady-flow turbine and, following isentropic expansion, exhausts at 0.025 MPaa: ΔP = 0, and ΔK = 0. The following values are given: a) final temperature; b) quality of steam at turbine exhaust; c) turbine work; and (d) if the turbine's efficiency is 90 percent, calculate the steam quality or temperature of steam at turbine exhaust, as well as the turbine output. (Draw the diagram)
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As a car gets older, will its compression ratio change? How about the mean effective pressure?
Q1) Which type of boiler is selected in certain thermal power plant discuss the effects depend upon the natural circulation of water?
There are required 2000 kW of compressor power to handle air adiabaticallyfrom 1 atmosphere, 27 oC, to 305 kPaa. The initial air velocity is 20 m/s and the finalvelocity is 85 m/s. a) If the compression is isentropic, find the compressor capacity, inm3/s. b) If the compression process is irreversible adiabatic to a temperature of 160 oC,with the capacity found in c), determine the compressor power input, in Hp.
A steady-flow, well-insulated turbine accepts steam at 4 MPa and 500°C with negligible kinetic and potential energy change, and exhausts at 100 kPa as saturated vapor. Calculate on a per-unit mass basis:(a) the actual work of the steam flowing through the turbine,(b) the entropy generation,(c) the quality x2s at the outlet if the process is reversible,(d) the maximum work output,(e) the isentropic efficiency. Assume the environment is at 100 kPa and 25°C.
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor, delivering a net power of 1 MW to the propeller. Air enters the diffuser at 8000 m altitude (Ta = 236K, pa = 36 kPa) with a velocity of 550 km/h, and decelerates essentially to zero velocity. The compressor pressure ratio is 5.3 and the compressor has an isentropic efficiency of 83%. The turbine inlet temperature is 1360 K, and its isentropic efficiency is 86%. The turbine exit pressure is 10 kPa higher than the ambient pressure at that altitude. Flow through the diffuser and nozzle is isentropic. Neglect kinetic energy except at the diffuser inlet and the nozzle exit. Using an air-standard analysis, determine: a) The mass and volumetric flow rates entering the diffuser, in kg/s and m3/s, respectively.b) The rate of heat addition to the combustor, in MW.c) The velocity at the nozzle exit, in m/s.
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 83.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 10 and the compressor has an isentropic efficiency of 85 %. The turbine inlet temperature is 1,140 K, and its isentropic efficiency is 85 %. The turbine exit pressure is 50 kPa. Flow through the diffuser and nozzle is isentropic. Sketch the process on the T-s diagram and using an air-standard analysis, determine, the power delivered to the propeller, in MWt the velocity at the nozzle exit, in m/s. Neglect kinetic energy except at the diffuser inlet and the nozzle exit.