Air enters a turbojet engine at 200 m/s at a rate of 20 kg/s and exits at 800 m/s relative to the aircraft. The thrust developed by the engine is?

The otto-cycle engine in a Mercedes-Benz slk230 has a compression ratio of 8.8. What is the ideal efficiency of the engine?

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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 83.7 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 10 and the compressor has an
isentropic efficiency of 85%. The turbine inlet
temperature is 1140 K, and its isentropic efficiency
is 85%. The turbine exit pressure is 50 kPa. Flow
through the diffuser and nozzle is isentropic. Using
an air-standard analysis, determine: (a) the power
delivered to the propeller, in MW. (b) the velocity at
the nozzle exit, in m/s. Neglect kinetic energy
except at the diffuser inlet and the nozzle exit

A regenerative gas turbine power plant is
shown in Fig. P1. Air enters the compressor at 1
bar, 27ºC with a mass flow rate of 0.562 kg/s and
is compressed to 4 bar. The isentropic efficiency of
the compressor is 80%, and the regenerator
effectiveness is 90%. All the power developed by
the high-pressure turbine is used to run the
compressor. The low-pressure turbine provides the
net power output. Each turbine has an isentropic
efficiency of 87% and the temperature at the inlet
to the high-pressure turbine is 1200 K. Sketch the
corresponding T – s diagram and determine: (a) The net power output, in kW. (b) The thermal
efficiency. (c) The temperature of the air at states
2, 3, 5, 6, and 7, in K.