[Q7~8] The figure below shows the major components of an air…

[Q7~8] The figure belоw shоws the mаjоr components of аn аircraft gas-turbine engine. [Q7, 5 pts] Write the name of each numbered component. _________________________________ _________________________________ _________________________________ _________________________________ _________________________________ _________________________________ [Q8, 5 pts] Which statements correctly describe the functions or thermodynamic behavior of the numbered components? (Select all that apply.) Component 1 conditions and generally decelerates the incoming flow before it reaches Component 2. Its static pressure may increase, while its stagnation pressure cannot increase in an adiabatic inlet. Component 2 extracts shaft work from the airflow, causing both stagnation pressure and stagnation temperature to decrease. Component 3 adds energy through combustion, substantially increasing the stagnation temperature. In a real engine, some stagnation-pressure loss occurs across this component. Component 4 extracts work from the hot gas to drive Component 2, causing the stagnation temperature and stagnation pressure of the gas to decrease. Component 5 is located upstream of Component 4 so that its additional heat release increases the work produced by Component 4. Component 6 expands the gas and converts part of its stagnation enthalpy into directed kinetic energy. For an adiabatic nozzle, the static temperature decreases while the stagnation temperature remains constant.