8. (With regeneration and two-stage compression) Air enters the compressor of a Brayton cycle with regeneration at 100 kPa, 300K with a mass flow rate of 6 kg/s. The compressor pressure ratio is 10, and the turbine inlet temperature is 1400K. The pressure ratios across each compressor stage are equal. The intercooling is perfect. The turbine and compressor each have isentropic efficiencies of 80%. The regenerative effectiveness is 80%. Determine: (a) the thermal efficiency of the cycle (b) the back work ratio (c) the net power developed in kW

8. (With regeneration and two-stage compression) Air enters the compressor of a Brayton cycle with regeneration at 100 kPa, 300K with a mass flow rate of 6 kg/s. The compressor pressure ratio is 10, and the turbine inlet temperature is 1400K. The pressure ratios across each compressor stage are equal. The intercooling is perfect. The turbine and compressor each have isentropic efficiencies of 80%. The regenerative effectiveness is 80%. Determine: (a) the thermal efficiency of the cycle (b) the back work ratio (c) the net power developed in kW

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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4. (Without regeneration) Air enters the compressor of a Brayton cycle at 100 kPa, 300K with a mass flow rate of 6 kg/s. The compressor pressure ratio is 10, and the turbine inlet temperature is 1400K. The turbine and compressor each have isentropic efficiencies of 80%. For k= 1.4, determine: (a) the thermal efficiency of the cycle (b) the back work ratio (c) the net power developed in kW The back work ratio is the ratio of the compressor work to the turbine work.
A turbojet aircraft is travelling at 925 km/h in atmospheric conditions of 0.45 bar and -26oC. The compressor pressure ratio is 8, the air mass flow rate is 45kg/s, and the maximum allowable cycle temperature is 800oC. The compressor, turbine, and jet pipe stagnation isentropic efficiencies are 0.85, 0.89, and 0.9 respectively, the mechanical efficiency of the drive is 0.98, and the combustion efficiency is 0.99. Assuming a convergent propulsion nozzle, a loss of stagnation pressure in the combustion chamber of 0.2 bar, and a fuel of calorific value 43 300kJ/kg, calculate: i) The required nozzle exit are; ii) The net thrust developed; slader For a gases in the turbine & propulsion nozzle take γ = 1.333 & Cp = 1.15kj/kg.k For the combustion process assume an equivalent Cp value of 1.15 kJ/kg.k
6.
|The typical cruising altitude of a commercial jet airliner is 10,700 m above sea level where the local atmospheric temperature is 219 K, and the pressure is 0.25 bar. The aircraft utilizes a cold air-standard Brayton cycle as shown with a volume flow rate of 1450 m³/s. The compressor pressure ratio is 50, and the maximum cycle temperature is 1700 K. The compressor and turbine isentropic efficiencies are 90%. Neglect kinetic and potential energy effects in this problem. Assume constant specific heats with k=1.4, Ra=0.287 kJ/kg- K, Cp=1.0045 kJ/kg-K, and cv = 0.7175 kJ/kg-K. a) Draw a T-s diagram for this cycle on the diagram provided. b) Fill in the table below with the missing information. T[K] Heat exchanger Heat exchanger State P [bar] 1 0.25 2s 2 3 4s 4 Turbine c) (5pts) Determine the inlet air density in [kg/m³] (at state 1), and the system mass flowrate in [kg/s]. d) (10pts) Determine the net power developed in [MW]. Be sure to draw each component you are analyzing, define the…
MODIFIED NON-IDEAL BRAYTON CYCLE GAS TURBINE: Use Air Standard Analysis SHOW COMPLETE SOLUTION.
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
Thermodynamics 1 Pls help me asap
Air enters the compressor of a regenerative ideal air-standard Brayton cycle at 100kPa,300K, with a volumetric flow rate of 4 m3/s. The compressor pressure ratio is 8, theregenerator effectiveness is 75% and the turbine inlet temperature is 1300K.Determine:(a) The back work ratio.(b) The net power developed.(c) The thermal efficiency
Consider a Brayton cycle with two stages of compression with intercooling, two stages ofexpansion with reheating and regeneration. Air enters the first stage compressor at 100kPa and 17 °C. The pressure ratio across each compressor and each turbine is 4.Temperature at the inlet of both the compressor is same. Heat transfer in combustionchamber as well as in reheater is 300 kJ/kg. The regenerator increases the temperature ofcold air by 20 °C. Calculate:a. Temperatures at all the salient points b. Heat added and heat rejected in the cycle c. Thermal efficiency
Air at 100 kPa, 300 K enters an ideal Otto cycle. The initial volume is 500 cm3. The compression ratio is 8.5, and the maximum temperature in the cycle is 2100 K. Using a cold-air standard analysis, determine the following:a. The heat addition (in kJ)b. The heat rejection (in kJ)c. The net work (in kJ)d. The cycle thermal efficiency
A gas-turbine power plant operating on an ideal Brayton cycle has a pressure ratio of(9.6). Air enters the compressor at 100 kPa, 300 K, with a volumetric flow rate of8 m3/s. The turbine inlet temperature is 1430 K.Universal gas constant (R) = 8.314 J K-1 mol-1, molar mass of air (M) = 28.97 g mol-1Neglecting all pressure losses, changes in kinetic energy determine;1. the thermal efficiency of the cycle2. the back work ratio3. the net power developed, in kW.4. Suppose in actual situation, the compressor has isentropic efficiency of 75 percent andthe turbine has isentropic efficiency of 80 percent because of irreversibilities present.Compare and evaluate the actual plant and theoretical efficiencies accounting for anydiscrepancies found.
Consider an ideal Brayton cycle operating on air. The inlet to the compressor is 300 K, 100 kPa. The compressor and turbine pressure ratios are 10. The maximum temperature in the system is 2000 K. Treat the air as an ideal gas with constant specific heats. a. What is the efficiency of this cycle? (Note: see derivation in section 10.1) b. What would the efficiency be for a Carnot cycle operating between the same temperature limits? c. You should have found that the efficiency of this cycle is less than the Carnot efficiency. So, there must be some irreversibility and entropy generation. For each of the four processes (compressor, heat addition, turbine, heat rejection), find the entropy generation per kg of air. For this analysis, assume the best-case scenario – heat is transferred to the high-T heat exchanger from a reservoir at 2000 K and heat is removed from the low-T heat exchanger to a reservoir at 300 K. d. If entropy is generated during this cycle, where does it go? e. What is…