the back work ratio and the thermal efficiency of the cycle assuming a regenerator with 75 and constant specific heats is used with C0.718 kJ/kg.K and Cy-1.005 kJ/kg.K. Determine expansion. The pressure ratio across each stage of the compressor and turbine is 3. The air Q2: Consider an ideal gas-turbine cycle with two stages of compression and two stages of kinetic and potential energy changes are negligible. The air standard assumptions are applicable enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. The percent effectiveness is used.

the back work ratio and the thermal efficiency of the cycle assuming a regenerator with 75 and constant specific heats is used with C0.718 kJ/kg.K and Cy-1.005 kJ/kg.K. Determine expansion. The pressure ratio across each stage of the compressor and turbine is 3. The air Q2: Consider an ideal gas-turbine cycle with two stages of compression and two stages of kinetic and potential energy changes are negligible. The air standard assumptions are applicable enters each stage of the compressor at 300 K and each stage of the turbine at 1200 K. The percent effectiveness is used.

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

A turbojet aircraft moving with a velocity of 790 ft/s at a runway where the pressure& temperature is found to be 14.7psi & 546R. The axial flow compressor provides apressure ratio of 14 to 1. Temperature at the turbine inlet is 2000R. The mass flowrate of airinside the engine is 133 lbm/s. Determine the following:a. T-S diagramb. Pressure & temperature at each statec. Thrust force (lbf)d. Propulsive power developed (BTU/min)e. Propulsive Efficiency
3- Air enters the compressor of a gas turbine at 120 kPa, 310 K. The air compressed to 1100 kPa, the turbine inlet temperature is 1460 K and the expansion occurs in two stages, with reheat to 1420 K between the stages at a pressure of 300 kPa. The compressor efficiency is 85 %. The net power developed is 2.2 MW. sketch T -S diagram then Determine: The thermal efficiency of the cycle. Qin Qin The back work ratio. Combustor Reheat combustor Turbine Turbine stage 1 stage 2 cycle Compressor
A four-cylinder spark-ignition engine with a compression ratio of 8 has a pistonswith a bore of 9 cm and a stroke of 10 cm. The air pressure at the beginning of thecompression is 98 kPa, and the temperature is 37 oC. The engine may be modeled by theair-standard Otto cycle. The maximum cycle temperature is 1700 oK. If the engineproduces 75 kW of power, determine a) the heat supplied per cylinder; b) the thermalefficiency; and c) the rpm required.
In an ideal otto cycle, heat supplied is 920 Kj/kg and the highest temperature inthe cycle is 1600 deg. C. Calculate the following:a. Temperature at the end of the isentropic compression processb. Change in entropy of a process.
An air standard gas turbine engine operates on an overall pressure ratio of 4 and between the temperature limits of 70 F and 1600 F Assuming constant specific heats, evaluate the compressor work. Find: (a) For ideal cycle: (b) calculate the turbine work (c) calculate the thermal efficiency Show complete solution on a paper.
for a rankine cycle, steam at 5.25 MPa. 435 degree celcius expands to 0.036 MPa. For 10kg/s of steam, determine heat added, heat rejected, work of turbine, thermal efficiency
Air enters the compressor of an Ideal Air Standard Brayton Cycle at 100kPa, 300K with a volume flow rate at 5m3/s. The compressor pressure ratio is 10. The turbine inlet temperature is 1400K, Determine: a. What is the back work ratiob. If the efficiency of the turbine and the compressor is 79%, Determine the back work ratioc. If the efficiency of the turbine and compressor efficiency is 85% and a regenerator efficiencyis 80%, what is the cycle efficiency
choose the most appropriate answer: In a Rankine Cycle, we are told that there is no heat transfer at the reversible turbine. this process is regarded as A. an isothermal process B. an adiabatic process C. the is no enthalpy change D. There is no temperature change E. an isentropic process F. an isobaric process
A four-cylinder compression-ignition engine with a compression ratio of 18 haspistons with a bore of 9 cm and a stroke of 10 cm. The air pressure at the beginning ofcompression is 98 kPaa, and the temperature is 37 oC. The engine may be modeled bythe air-standard Diesel cycle. The maximum cycle temperature is 1700 oK. If the engineproduces 75 kW of power, determine a) the heat supplied per cylinder; b) the thermalefficiency; and c) the rpm required.
Q.17 The given figure shows an open-cycle gas turbine employing reheating, on T-s plane. Assuming that the specific heats are same for both air and gas, and neglecting the increase in mass flow due to addition of. fuel, the efliciency is T. 1000 K 3. 800 K. G00 K 500 K 450 K- 9. 300 K %24
An air-standard Spark Ignition cycle has a compression ratio of 10.2. Air is at 30000R at the end ofthe heat addition process. Neglecting the variation of specific heats with temperature, determine thefollowing:a. Net output work of the cycleb. Heat rejection per unit mass, Btu/lbc. Thermal efficiency of the cycle(%). Compare this efficiency value if the cycle has to run on an airstandard Carnot Cycle
Q2) Air at 300 K and 100 kPa enters into the compressor of a gas turbine engine that operates on a Brayton cycle. The air mass fl ow rate is 5 kg/s and the maximum air temperature in the engine is 1200 K. If the pressure ratio of the cycle is (r = 4), a. Find the effi ciency of the engine, assuming ideal compression and expansion. b. Find the power output for( case a). e. What would be the isentropic efficiency of each device that would result in no work output from the engine if the compressor and turbine were not ideal? d. What are the exit temperatures from the turbine and the compressor for that case.