Assignment 10, Question 3, Problem Book #198Problem StatementConsider a Brayton cycle with a regenerator. The regenerator has an effectiveness of 75%.The compressor inlet conditions are 1.2 bar and 300 K and the mass flowrate is 4.5 kg/s. Thecompressor outlet pressure is 9 bar. Both the compressor and turbine consist of a singleisentropic stage. What minimum power output must be achieved before the regeneratorbegins to have a benefit? Use an air-standard analysis.Answer TableCorrect AnswerStageDescriptionYour AnswerDue DateGrade(%)PartWeight Attempt Action/MessageТуре1Power output (MW)Dec 5, 2024 11:59 pm0.011/5Submit* Correct answers will only show after due date has passed.

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Answered: Assignment 10, Question 3, Problem Book…

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

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Assignment 10, Question 1, Problem Book #189 Problem Statement An ideal Brayton cycle operates with no reheat, intercooling, or regeneration. The com- pressor inlet conditions are 30°C and 1 bar. The compression ratio is 11. The turbine inlet temperature is 1,300 K. Determine the turbine exit temperature, the thermal efficiency, and the back work ratio. Use an air standard analysis. Answer Table Correct Stage Description Your Answer Answer * 1 Compressor inlet enthalpy (kJ/kg) Due Date Grade (%) Weight Attempt Action/Message Part Type 1 2 1 Compressor inlet relative pressure 1 Compressor exit relative pressure 1 Compressor exit enthalpy (kJ/kg) Compressor work (kJ/kg) Turbine inlet enthalpy (kJ/kg) Dec 5, 2024 11:59 pm Dec 5, 2024 11:59 pm Dec 5, 2024 11:59 pm 0.0 0.0 1 1/5 Submit Stage 1 0.0 1 1 Dec 5, 2024 11:59 pm 0.0 1 Dec 5, 2024 11:59 pm 0.0 1 2 Turbine inlet relative pressure Dec 5, 2024 11:59 pm Dec 5, 2024 11:59 pm 0.0 1 1/5 0.0 1 2 Combustion chamber heat addition (kJ/kg) Dec…
4.3 A gas turbine with reheat has a TIT of 1230°C, a compressor pressure ratio of 16, and compressor and turbine efficiencies of 0.88 and 0.91, respectively. The pressure ratios of both the HP and LP turbine stages are the same. The reheat occurs up to a temperature of 1230°C. The compres- sor inlet conditions are 20°C and 1.01 bar. The fuel mass flow rate may be ignored. Determine (a) the pressures and temperatures at all real states of the cycle, (b) the turbine and compressor specific works and their ratio, and (c) the cycle thermal efficiency.
On the axis provide, draw a corresponding T-s diagram for the Brayton cycle shown given the following information: iv. V. vi. Compressor 1 is reversible, but Compressor 2 and the turbine are irreversible. The pressure drops through the regenerator are combustors are negligible. The pressures at state (1) and state (10) are equal to the atmospheric pressure. T 8 Regenerator fmm mmm Qin Combustor Compressor Compressor Turbine W cycle Intercooler mm Cour
Thermodynamics 2
A GPP uses a simple Brayton cycle. Air enters the compressor at pressure, P = 1 bar, temperature, T = 20°C and exits the compressor at a pressure of 7 bar. Combustion chamber temperature = 800°C. Compressor efficiency, nk = 0.82, turbine efficiency, nT = 0.85. Turbine power 4 MW. Define: System installation diagram and cycle process on the P-v and T-s diagram P-v and T-swK, wt and rl cycles. BWR, mair, Wtnet, mfuel (qfuel : 40,000 kj/kg) Note : Air, cp,d : 1 ,005 kj/kg.k, k : 1 ,4 1 .15 kl/kg.k, k gas : 1 .3
I do not understand the chapter in general. May you please explain why you completed each step as you have. Thank you.
I need unique and correct answer. Don't try to copy from anywhere. Do not give answer in image formet and hand writing
1. An open Brayton cycle using air operates with a maximum cycle temperature of 1300°F .The compressor pressure ratio is 6.0. Heat supplied in the combustion chamber is 200 Btu/lb. The ambient temperature before the compressor is 95°F, and the atmospheric pressure is 14.7 psia. Using constant specific heat, calculate the temperature of the air leaving the turbine, °F; A. 959 °F C. 837°F D. 647°F B. 595°F
Show how an ideal Otto cycle can estimate the operation of a spark ignition piston engine [NOTE: Diagrams may be used to explain this question]
I only need help with letter i. At the beginning of the compression process of an air standard Otto cycle, p1 = 1 bar, T1 = 300 K. The maximum temperature in the cycle is 2250 K and the compression ratio is 9.8. The engine has 4 cylinders and an engine displacement of Vd = 2.1 L. Determine per cylinder: a) the volume at state 1.b) the air mass per cycle.c) the heat addition per cycle, in kJ.d) the heat rejection per cycle, in kJ.e) the net work per cycle, in kJ.f) the thermal efficiency.g) the mean effective pressure, in bar.h) Develop a full exergy accounting per cycle, in kJ. Let T0 = 300 K, p0 = 1 bar.i) Devise and evaluate the exergetic efficiency for the cycle.
(Thermodynamics) A steady-flow system operating on the ideal Ericsson cycle can achieve the Carnot efficiency. One of the salient features of this cycle is the isothermal expansion through a heated turbine, as shown in Fig. a. Heat is added to the turbine such that the outlet temperature is equal to the inlet temperature, i.e. T₁=T₂, and the overall pressure ratio for this process is rₚ=P₁/P₂. However, an isothermal expansion through a heated turbine is very difficult to achieve in practical engineering applications. An alternate approach is two use a multi-stage expansion process with reheating. In this approach, the gas expansion process is carried out in multiple stages with reheating in between each stage. Consider the two-stage turbine expansion with reheating shown in Fig. b. The gas enters the first stage of the turbine at state A1, is expanded isentropically to an intermediate pressure Pₐ₂, is reheated at constant pressure to state B1, and is expanded in the second stage…
Assume a basic (non-regenerative) ideal Brayton cycle where air modeled as IG with variables specific heat. The gas-turbine engine has the following operational parameters: Inlet Air Temperature:537 R Inlet Air Pressure:14.696 psia Compressor Pressure Ratio (rp):6.0 Firing Temperature:2400 R Heat Recovery Steam Generator: Assume that the exhaust from the gas turbine engine is directed to a heat recovery steam generator (HRSG)to produce wet steam (i.e. saturated vapor) at a pressure of 600 psia. Liquid water is supplied to the HRSG at 100F and 600 psia. The exhaust gas from the gas-turbine engine leaves the HRSG at the saturation temperature of the wet steam. With these conditions determine: a) the exit temperature of the wet steam (F), b) the intensive steam production rate, lbm-steam/lbm-exhaust gas. Absorption Chiller CHP: Assume the process steam from the HRSG is now used to drive an absorption chiller with COP of 0.7, and that the mechanical power of the gas-turbine engine is used…

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