Quantitative: In the 1950s liquid hydrogen was considered as a fuel for a new type of...
please solve h to m .A-7 The gas turbine engines that are used on a military jet air plane likely consists of a diffuser, compressor, combustor, turbine, afterburmer, and nozzle that are arranged in series as shown in Figure 4.A-7(a) and flying with a velocity of 350 mph. The analysis will be carried out on a component-by component basis. Model the air as an ideal gas and assume that it has constant c and cp R 287.1 Ikg-K and c-1005...
Problem-2 (200) Air at 30 kPa, 200 K, and 250 m/s enters a turbojet engine in flight. The air mass flow rate is 28 kg/s. The compressor pressure ratio is 13, the turbine inlet temperature is 1460 K, and air exits the nozzle at 30 kPa. The diffuser and nozzle processes are isentropic, the compressor and turbine have isentropic efficiencies of 81% and 88%, respectively, and there is no pressure drop for flow through the combustor. Kinetic energy is negligible...
Q.4 Air at 26 kPa,230 K, and 220 m/s enters a turbojet engine in flight as shown below. The mass flow rate of air is 25 kg/s, the compression pressure ratio is 11, inlet temperature to the turbine is 1400 K, and air exits the nozzle at 26 kPa. The diffuser and nozzle processes are isentropic, but the compressor and turbine have isentropic efficiencies of 85 and 90 percent, respectively and there is no pressure drop for flow through the...
A turboprop engine consists of a diffuser, compressor, combustor, turbine, and nozzle. The turbine drives a propeller as well as the compressor. Air enters the diffuser with a volumetric flow rate of 63.7 m3/s at 40 kPa, 240 K, and a velocity of 180 m/s, and decelerates essentially to zero velocity. The compressor pressure ratio is 9 and the compressor has an isentropic efficiency of 85%. The turbine inlet temperature is 1240 K, and its isentropic efficiency is 85%. The...
A turbojet engine consists of a diffuser, compressor, combustor, turbine and a converging nozzle. The engine is operating on an aircraft flying at 260 m/s at an altitude where the air is at 61 kPa and -11 °C. The inlet diameter of this engine is 1.6 m; the thrust produced by the engine under ideal cruising conditions is 93,625 N; and the temperature at the turbine inlet is 750 °C. Assume constant specific heat values at room temperature, choked flow...
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)....
A motor car gas turbine unit has two centrifugal compressors in series giving an overall pressure ratio of 6/1. The air leaving the HP compressor passes through a heat exchanger before entering the combustion chamber. The expansion is in two turbine stages, the first stage driving the compressors and the second stage driving the car through gearing. The gases leaving the LP turbine pass through the heat exchanger before exhausting to the atmosphere. The HP turbine inlet temperature is 800...
A turbojet aircraft has its compressor rated at the pressure ratio of 10. Given that the aircraft flies with a velocity of 289 m/s at an altitude where the air is at a pressure of 29.5 kPa and temperature of-31.0·C. The air enters the compressor at 54 kg/s. The fuel used during the flight is rated to provide 39300 kJ of heat energy from every kilogram burnt and the temperature of the air entering the turbine is 1047.744 K. Calculate...
Part 6 Question 1 (3 marks) The power cycle shown below operates at steady state. Air (constant k = 1.4) enters the compressor at 0.1 MPa and 15.C. The pressure leaving the compressor is 1.0 MPa, and the maximum temperature in the cycle is 1100-C. Deterinine the temperature at the exit of the turbine, in Kelvin. Heat exchanger 2 3 Compressor Turbino Inel Heat exchanger
Flow enters the combustor of a jet engine at a Mach number of 0.5, a temperature of 390K and a pressure of 200kPa. (a) Determine the maximum amount of heat that can be added to this flow, assuming that the combustion chamber has the form of a constant area duct, and the properties of the air/fuel mixture flowing through the combustor are the same as those of air. (b) The flow entering the combustor 1 has a fuel to air...