Gas Turbines

Explain briefly the difference between direct and indirect cycle for gas turbine. Derive a relation between compressor and turbine outlet temperature for getting maximum specific power.

A gas turbine inlet receives air at $1 \text{ bar}$ and $300 \text{ K}$ and compresses it adiabatically to $6 \text{ bar}$. The compressor efficiency is $90$ where the fuel has heating value of $44000 \text{ kJ/kg}$ and fuel-air ratio is $0.017$. The turbine efficiency is $92$. Calculate the work of the turbine and compressor and also find the thermal efficiency. For air $c_p = 1.005 \text{ kJ/kg-K}$, $\gamma = 1.4$. For products of combustion, $c_p = 1.47 \text{ kJ/kg-K}$, $\gamma = 1.33$.

Derive a relation between compressor and turbine outlet temperature for getting maximum specific power consumption.

Explain with the help of schematic and $T-s$ diagrams the compressor intercooling method of increasing gas turbine efficiency.

In a gas turbine plant, maximum and minimum temperature are $830^{\circ}\text{C}$ and $30^{\circ}\text{C}$ respectively. The pressure ratio is 4.2. Calculate the specific power output and cycle efficiency. Assume isentropic efficiency of the compressor and the turbine are 90 and 92 percent respectively. Given, $C_p = 1.005 \text{ kJ/kg-K}$.

Define pressure ratio is gas turbine. Find the optimum pressure for gas turbine.

Can Brayton cycle be modified? Why is it necessary?

In a gas turbine plant, maximum and minimum temperatures are $830^\circ\text{C}$ and $30^\circ\text{C}$ respectively. The pressure ratio is 4.2. Calculate the specific crank output and cycle efficiency. Assume isentropic efficiency of the compressor and the turbine are 90 and 92 percent respectively. Given, $C_p = 1.005 \text{ kJ/kg-K}$.

Explain briefly the difference between direct and indirect cycle for gas turbines. Derive a relation between compressor and turbine outlet temperature for getting maximum specific power consumption.

A gas turbine inlet receives air at 1 bar and 300K and compresses it adiabatically to 6.0 bar. The compressor efficiency is 90% where the fuel has heating value of 44,000 kJ/kg and fuel-air ratio is 0.017. The turbine efficiency is 92%. Calculate the work of the turbine and compressor per kg of air compressed and also find the thermal efficiency. For air $c_p = 1.005$ kJ/kg-K, $\gamma = 1.4$. For products of combustion $c_p = 1.47$ kJ/kg-K, $\gamma = 1.33$.

Show that the specific power of a single gas turbine cycle is maximum when the pressure ratio is such that the compressor and turbine outlet temperatures are equal.

In a gas turbine plant, maximum and minimum temperatures are $825^\circ\text{C}$ and $25^\circ\text{C}$ respectively. The pressure ratio is $4.5$. Calculate the specific work output, and cycle efficiency. Assume isentropic efficiencies of the compressor and the turbine are $85$ and $90$ respectively. Given $C_p = 1.005\text{ kJ/kgK}$.