In a combustion turbine using natural gas as the fuel, air enters the compressor at 98...
1. A combustion turbine possesses the following characteristics: Compressor 97 kPa and 30。C inlet conditions Pressure ratio: 5.5 Isentropic compression efficiency: 0.84 Combustor Outlet temperature: 1000 °C Pressure loss: 3 percent Fuel: natural gas Turbine Exit pressure: 100 kPa Isentropic expansion efficiency: 0.88 Generator Generator efficiency: 0.98 Determine the overall thermal efficiency, the heat rate, and the fuel-to-air ratio
Problem 1 (Marks 3) Smithfield power station in NSW, Australia operates on 4 gas turbines. Each of the gas turbine unit operates on the regenerative Brayton Cycle between the pressure limits of 100 kPa and 700 kPa. Air enters the compressor at 30°C at a rate of 12.6 kg/s and leaves at 260°C. It is then heated in a regenerator to 400°C by hot combustion gases leaving the turbine. Diesel fuel with heating value of 42,000 kJ/kg is burned in...
(i) In a gas turbine plant, air enters the compressor at 150 C and it is compressed through a pressure ratio of 4 with isentropic efficiency of 85%. The air-fuel ratio is 80 and the calofific value of fuel is 42000kJ/kg. The turbine inlet air temperature is 1000 K and the isentropic efficiency of the turbine is 82%. Calculate the overall efficiency and air intake for à power output of 260 kW. Take the mass of fuel inG account. PSG...
II. In a gas turbine installation, shown in the Regenerator Fuel opposite figure, air is supplied at Pi of 1 bar and temperature Ti of 27 C intoa compressor which has a pressure ration t of 8. The air leaving the combustion chamber is heated up to a temperature T4 of 827 °C and expanded in a turbine up to a pressure Ps of 1 bar. A regenerator with an effectiveness ε of80 % is fitted at the turbine exit...
1. A combined gas-steam power cycle uses a single gas turbine cycle for the air cycle and a simple Rankine cycle for the water vapor cycle. Atmospheric air enters the compressor at a rate of 88.2 lbm / s, at 14.7 psia and 59 ° F, and the maximum gas cycle temperature is 1,742 ° F. The pressure ratio in the compressor is 7. The isentropic efficiency of both the compressor and the turbine is 80%. Gas exits the heat...
Question 3: In a gas turbine engine, the compressor takes in air at a temperature of 15°C, pressure of 100 kPa, and a volumetric flow rate of 5 m3/s and compresses it to four times the initial pressure with an isentropic efficiency of 82%. The air then passes through a heat exchanger heated by the turbine exhaust before reaching the combustion chamber. In the heat exchanger 78% of the available heat is given to the air. The maximum temperature after...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is flying at cruising condition with a flight Mach number of 0.7. The ambient temperature and pressure are 250 K and 100 kPa, respectively. The engine compressor pressure ratio is 12, and the turbine inlet temperature is 1200 K. Assume all mechanical components are operating at isentropic condition and the specific heat can be considered a constant (throughout the entire engine) of 1 kJ/(kg K)....
In a gas turbine engine, the compressor takes in air at a temperature of 15°C, pressure of 100 kPa, and a volumetric flow rate of 5 m3 /s and compresses it to four times the initial pressure with an isentropic efficiency of 82%. The air then passes through a heat exchanger heated by the turbine exhaust before reaching the combustion chamber. In the heat exchanger 78% of the available heat is given to the air. The maximum temperature after constant...
The refrigerant gas which is air, enters the compressor of a Brayton refrigeration cycle at 101 kPa, 280 K. If the compressor pressure ratio is 5 and the turbine inlet temperature is 330 K. The compressor has an isentropic efficiency of 70% and the turbine has an isentropic efficiency of 80%. Using air table rather than constant-specific-heat theory, determine (a) the net work input per unit mass of air flow, (b) the refrigeration capacity, in kJ/kg, (c) the coefficient of...
In a gas turbine engine, the compressor takes in air at a temperature of 15°C, pressure of 100 kPa, and a volumetric flow rate of 5 m/s and compresses it to four times the initial pressure with an isentropic efficiency of 82%. The air then passes through a heat exchanger heated by the turbine exhaust before reaching the combustion chamber. In the heat exchanger 78% of the available heat is given to the air. The maximum temperature after constant pressure...