Required information Problem 05.042 Nozzle flow Air enters an adiabatic nozzle steadily at 300 kPa, 200°C, and 45 m/s and leaves at 110.0 kPa and 180 m/s. The inlet area of the nozzle is 110 cm². The gas constant of air is 0. 287 kPa m³/kg K. The specific heat of air at the anticipated average temperature of 450 K is Cp 1.02 kJ/kg. C. . P₁ = 300 kPa T₁ =200°C Air P₂ kPa V₁ -45 m/s V₂ = 180 m/s A₁ = 110 cm² Problem 05.042.a- Nozzle flow Determine the mass flow rate through the nozzle. The mass flow rate through the nozzle is kg/s. 0 Required information Problem 05.042 Nozzle flow Air enters an adiabatic nozzle steadily at 300 kPa, 200°C, and 45 m/s and leaves at 110.0 kPa and 180 m/s. The inlet area of the nozzle is 110 cm2. The gas constant of air is 0.287 kPa m³/kg K. The specific heat of air at the anticipated average temperature of 450 K is cp = 1.02 kJ/kg. C. - P₁ = 300 kPa T₁ =200°C V₁=45 m/s A₁ = 110 cm² Air P2 kPa V2 180 m/s Problem 05.042.b - Nozzle flow Determine the exit temperature of the air. The exit temperature of the air is °C.

Air is compressed in an adiabatic compressor. Inlet and outlet conditions are 120kPa, 30 oC and 20 m/s; 1.4 MPa, 530 oC and 80 m/s.  The surrounding air temperature is 25 oC. The inlet cross-sectional area is  0.013 m2. Assume Cp = 1005 J/kgK, R = 287 J/kgK, k = 1.4.   Enter the amount of heat loss due to irreversibility resulting from the heat transfer from the compressor in kW (correct up to one decimal place.)

A turbine operates under steady flow conditions, receiving steam at the following state: pressure 1200 kPa, temperature 1880C, enthalpy 2785 kJ/kg, speed 33.3 m/s, and elevation 3 m. The steam leaves the turbine at the following pressure 20 kPa, enthalpy 2512 kJ/kg, speed 100 m/s, and elevation 0 m. Heat is lost to the surroundings at the rate of 0.29 kJ/s. If the rate of steam flow through the turbine is 0.42 kg/s, what is the power output of the turbine in kW?

Required information Problem 05.051-Turbine flow Steam flows steadily through an adiabatic turbine. The inlet conditions of the steam are 4 MPa, 500°C, and 80 m/s and the exit conditions are 30 kPa, 92 percent quality, and 50 m/s. The mass flow rate of the steam is 11.80 kg/s. The properties of the steam are V₁ = 0.086442 m³/kg, h₁ = 3446 kJ/kg, and h₂ P₁ =4 MPa T₁ = 500°C V₁ = 80 m/s 3446 kJ/kg, and h₂ 2437. 7 kJ/kg. Steam m kg/s P₂= 30 kPa x2=0.92 V2= 50 m/s Problem 05.051.c - Turbine flow Determine the turbine inlet area. (Round the final answer to three decimal places.) The turbine inlet area is m².

Apply SFEE for the steam nozzle used in the steam powerplant and determine the outlet velocity of the steam using thefollowing details.Steam at 18 bar and 350°C steadily enters a nozzle whose inletarea is 200 cm2. The mass flow rate of the steam is 4.5 g/s. Heatlosses from the nozzle per unit mass of the steam are estimatedto be 2.8 kJ/kg. Steam leaves the nozzle at 14 bar, 300 °C.Determine the outlet velocity of the steam.

Steam enters an adiabatic nozzle at 1378 kPa, a velocity of 3.05 m/s, a specific volume of 0.147 m³xkg1 and a specific internal energy of 2510 kJ/kg. The exit conditions are 137.8 kPa, specific volume of 1.099 m³xkg and internal energy of 2263 kJ/kg. Determine: a. Exit velocity of stream; and b. Ratio of inlet diameter to exit diameter

Air (MW=29 g/mol) at 115.00 kPa and 285.00  is compressed steadily to 600.0 kPa. The mass flow rate of the air is 2.00 kg/s and a heat loss of 32.1 kW occurs during the process. You may assume that changes in kinetic and potential energy are negligible, the temperature of the surroundings is 25 ∘C, and that the CP of air is 3.5 R. Given the compressor operates with a second law (reversible) efficiency of 0.60,calculate the following. What is the actual work interaction term in kW? What is the actual exit temperature of the air in Celcius?

Air at a static temperature and pressure of 8°C and 75 kPa respectively enters the intake of an aircraft gas turbine engine with a velocity of 196 m/s. The intake may be regarded as a diffuser with an inlet area of 0.4 m2 and an exit area that reduces the air flow velocity essentially to zero. Calculate the mass flow rate (kg/s) of air through the intake, given the specific gas (air) constant as 287 J/(kg.K), keeping three decimal places.

Air at a static temperature and pressure of 9°C and 100 kPa respectively enters the intake of an aircraft gas turbine engine with a velocity of 206 m/s. The intake may be regarded as a diffuser with an inlet area of 0.4 m2 and an exit area that reduces the air flow velocity essentially to zero. Calculate the mass flow rate (kg/s) of air through the intake, given the specific gas (air) constant as 287 J/(kg.K)

Air at a 800 kPa and 1300 K enters an adiabatic and reversible turbine with a mass flow rate 6 kg/s. The outlet pressure is 100 kPa and assume that specific heats are constant and evaluated at 600 K. What is the specific heat at constant pressure for this problem? What is the temperature of the outlet in K? Round your answer to one decimal place. How much power is produced in kW? Round your answer to the nearest whole number.