Homework Answers
ANSWER:-
Air enters this engine at 14 psia and 50 degrees F
each stage of compression is 2.7
a turbine is 940 derees F
engine prodoces 1040 hp
![O The properties of air room temperature. <p>0.24 874116m.R K=1.4 T,= Sot T-50.9672 72 = 1, 1 cop, CX-11/K] . 509.67 (2.714-1](http://img.homeworklib.com/questions/c972b870-cf6b-11ea-9536-0140d90a7a81.png?x-oss-process=image/resize,w_560)
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5. Similar to 9-127 A gas turbine operates with a regenerator and two stages of reheating...
Do problem 9.128E using variable specific heat assumptions instead of constant. Please don't use constant specific...
Do problem 9.128E using
variable specific heat assumptions instead of constant.
Please don't use constant specific heat
assumption
Solution 9.128E Problem Statement Reconsider Prob. 9–127E. Determine the change in the rate of heat addition to the cycle when the isentropic efficiency of each compressor is 88 percent and that of each turbine is 93 percent. Problem 9.127E A gas turbine operates with a regenerator and two stages of reheating and intercooling. Air enters this engine at 14 psia and 60°F;...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 20°C. The compressor pressure ratio is 7.8; the maximum cycle temperature is 865°C; and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assuming both the compressor and the turbine to be isentropic, determine the rates of heat addition and rejection...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling,...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling, the pressure ratio and the air inlet temperature of 20°C is the same for both stages. The overall compression ratio is 10:1. The isentropic efficiency of both stages is 89.0% For air take y=1.4 and Co=1.005 KJ/kg.k Determine the specific work required to drive both compressors, your answer should be in KJ/kg to 1 decimal place. DO NOT INCLUDE UNITS IN YOUR ANSWER 5...
Problem 9.106 using varaiable specific heat assumption (Non-Ideal Regenerative Brayton Cycle) 9-105 A gas turbine for...
Problem 9.106 using varaiable specific heat assumption
(Non-Ideal Regenerative Brayton Cycle)
9-105 A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 30°C. The compressor pressure ratio is 8; the maximum cycle temperature is 800°C; and the cold airstream leaves the regenerator 10°C cooler than the hot airstream at the inlet of the regenerator. Assuming both the compressor and the tur- bine to be isentropic, determine the rates...
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stag...
please solve by exact analysis
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stages with intercooling, and each stage has a pressure ratio of 2.38 and an efficiency of 84%, with intercooling to 26.7°C The maximum temperature of the cycle is 676.7°C Turbine efficiency is 82%. The turbine and compressor are assumed adiabatic. A regenerator heats the compressed air to 326.7°C before sending it to the combustor. Calculate (a) the back...
Air is the working fluid in a gas-turbine power system which rotates an electric generator. The...
Air is the working fluid in a gas-turbine power system which rotates an electric generator. The system includes a compressor, a two-stage turbine and a regenerator. Air enters a compressor with a compression ratio of 16 at 14 lbf/in2 and 70°F. For each stage of the turbine, compression ratio is 8 and temperature of air entering is 2000°F. The reported isentropic efficiency for each turbine and the compressor is 85%. Regeneration system is 70% efficient. Considering specific heat capacities varying...
A regenerative gas turbine power plant has two stages of compression and two stages of expansion....
A regenerative gas turbine power plant has two stages of compression and two stages of expansion. The overall pressure ratio of the cycle is 12. The air enters each stage of compressor at 300 K and each stage of turbine at 1,180 K. Assume ideal Brayton cycle and effectiveness of regenerator as 100%. The compression or expansion ratios across each compression or expansion stage are also identical. The heating value of the fuel is 39,000 kJ/kg. The minimum fuel consumption...
Problem 1 (15 pts) A gas turbine cycle operates with a compressor pressure ratio of 12...
Problem 1 (15 pts) A gas turbine cycle operates with a compressor pressure ratio of 12 and a mass flow rate of 5.0 kg/s. Air enters the compressor at 1 bar, 290 K. The maximum cycle temperature is 1600 K. For the compressor, the isentropic efficiency is 85%, and for the turbine the isentropic efficiency is 90%. Using an air-standard analysis with air as ideal gas with constant specific heats, calculate: a) the volumetric flow rate of air entering the...
Design a small gas turbine engine to produce 150 kW of net power. Use an air-standard...
Design a small gas turbine engine to produce 150 kW of net power. Use an air-standard analysis (constant gas properties) and assume air enters the compressor at 100kPa and 20°C. The compressor pressure ratio is 8, the maximum cycle temperature is 800°C, and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assume a compressor isentropic efficiency of 87% and a turbine isentropic efficiency of 93%. Determine the rates...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of 14.7 and 200 psia. Air enters the compressor at 77°F at a rate of 28 lbm/s and leaves at 750°F. Fuel is burned in the combustion chamber and the combustion gases enter the turbine at 2000°F. Combustion gases leave the turbine whose isentropic efficiency is 85 percent. Treating the combustion gases as air and using constant specific heats evaluated at 900°F, determine (a) the...
Do problem 9.128E using
variable specific heat assumptions instead of constant.
Please don't use constant specific heat
assumption
Solution 9.128E Problem Statement Reconsider Prob. 9–127E. Determine the change in the rate of heat addition to the cycle when the isentropic efficiency of each compressor is 88 percent and that of each turbine is 93 percent. Problem 9.127E A gas turbine operates with a regenerator and two stages of reheating and intercooling. Air enters this engine at 14 psia and 60°F;...
Heat exchanger 5 Comb. Compressor Turbine A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 20°C. The compressor pressure ratio is 7.8; the maximum cycle temperature is 865°C; and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assuming both the compressor and the turbine to be isentropic, determine the rates of heat addition and rejection...
Question 10 10 pts A gas turbine operates with a two stage air compressor incorporating intercooling, the pressure ratio and the air inlet temperature of 20°C is the same for both stages. The overall compression ratio is 10:1. The isentropic efficiency of both stages is 89.0% For air take y=1.4 and Co=1.005 KJ/kg.k Determine the specific work required to drive both compressors, your answer should be in KJ/kg to 1 decimal place. DO NOT INCLUDE UNITS IN YOUR ANSWER 5...
Problem 9.106 using varaiable specific heat assumption
(Non-Ideal Regenerative Brayton Cycle)
9-105 A gas turbine for an automobile is designed with a regenerator. Air enters the compressor of this engine at 100 kPa and 30°C. The compressor pressure ratio is 8; the maximum cycle temperature is 800°C; and the cold airstream leaves the regenerator 10°C cooler than the hot airstream at the inlet of the regenerator. Assuming both the compressor and the tur- bine to be isentropic, determine the rates...
please solve by exact analysis
Problem 1 A Brayton-cycle power plant takes in air at 100 kPa and 26.7°C. Compression in two stages with intercooling, and each stage has a pressure ratio of 2.38 and an efficiency of 84%, with intercooling to 26.7°C The maximum temperature of the cycle is 676.7°C Turbine efficiency is 82%. The turbine and compressor are assumed adiabatic. A regenerator heats the compressed air to 326.7°C before sending it to the combustor. Calculate (a) the back...
Air is the working fluid in a gas-turbine power system which rotates an electric generator. The system includes a compressor, a two-stage turbine and a regenerator. Air enters a compressor with a compression ratio of 16 at 14 lbf/in2 and 70°F. For each stage of the turbine, compression ratio is 8 and temperature of air entering is 2000°F. The reported isentropic efficiency for each turbine and the compressor is 85%. Regeneration system is 70% efficient. Considering specific heat capacities varying...
A regenerative gas turbine power plant has two stages of compression and two stages of expansion. The overall pressure ratio of the cycle is 12. The air enters each stage of compressor at 300 K and each stage of turbine at 1,180 K. Assume ideal Brayton cycle and effectiveness of regenerator as 100%. The compression or expansion ratios across each compression or expansion stage are also identical. The heating value of the fuel is 39,000 kJ/kg. The minimum fuel consumption...
Problem 1 (15 pts) A gas turbine cycle operates with a compressor pressure ratio of 12 and a mass flow rate of 5.0 kg/s. Air enters the compressor at 1 bar, 290 K. The maximum cycle temperature is 1600 K. For the compressor, the isentropic efficiency is 85%, and for the turbine the isentropic efficiency is 90%. Using an air-standard analysis with air as ideal gas with constant specific heats, calculate: a) the volumetric flow rate of air entering the...
Design a small gas turbine engine to produce 150 kW of net power. Use an air-standard analysis (constant gas properties) and assume air enters the compressor at 100kPa and 20°C. The compressor pressure ratio is 8, the maximum cycle temperature is 800°C, and the cold air stream leaves the regenerator 10°C cooler than the hot air stream at the inlet of the regenerator. Assume a compressor isentropic efficiency of 87% and a turbine isentropic efficiency of 93%. Determine the rates...
3a. A gas-turbine power plant operates on the simple Brayton cycle between the pressure limits of 14.7 and 200 psia. Air enters the compressor at 77°F at a rate of 28 lbm/s and leaves at 750°F. Fuel is burned in the combustion chamber and the combustion gases enter the turbine at 2000°F. Combustion gases leave the turbine whose isentropic efficiency is 85 percent. Treating the combustion gases as air and using constant specific heats evaluated at 900°F, determine (a) the...
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