A Freon 22 air conditioning under standard operating conditions of 35°C condensing and 5°C evaporating temperatures. The volume flow rate entering the compressor is 23.72 L/s. Determine the refrigerating capacity if the refrigerating effect is 164 kJ/kg. From the table for R22 the specific volume at the compressor entrance is 40.46 L/kg.

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. 

An ideal Otto cycle with Argon as the working fluid has a compression ratio of 6.8. The minimum and maximum temperatures in the cycle are 450 R and 2,260 R. Assuming constant specific heats, determine

(a) the amount of heat transferred to the argon during the heat-addition process

(b) the thermal efficiency

(c) the thermal efficiency of a Carnot cycle operating between the same temperature limits

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