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A ramjet engine is analyzed using the air standard method. Given specific operating conditions determine the...
A ramjet engine is analyzed using the air standard method. Given specific operating conditions determine the...
A ramjet engine is analyzed using the air standard method. Given specific operating conditions determine the temperature, pressure, and enthalpy at each state, the exit velocity, and the rate of heat addition (kJ/kg). --Given Values-- T1 (K) = 236 P1 (kPa) = 54 V1 (m/s) = 632 rc = 2.03 a) Determine the specific enthalpy (kJ/kg) at state 1. b) Determine the relative pressure at state 1. c) Determine the specific enthalpy (kJ/kg) at state 2. d) Determine the temperature...
An ideal turbojet engine is analyzed using the cold air standard method. Given specific operating conditions...
An ideal turbojet engine is analyzed using the cold air standard method. Given specific operating conditions determine the temperature, pressure, and enthalpy at each state, and the exit velocity. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- T1 (K) = 236 P1 (kPa) = 56 V1 (m/s) = 217 rp = 11.1 rc = 1.78 a) Determine the temperature (K) at state 2. b) Determine the pressure (kPa)...
A four-cylinder four-stroke engine is modelled using the air standard Otto cycle (two engine revolutions per...
A four-cylinder four-stroke engine is modelled using the air
standard Otto cycle (two engine revolutions per cycle). Given the
conditions at state 1, total volume (V1) of each cylinder,
compression ratio (r), rate of heat addition (Q), and engine speed
in RPM, determine the efficiency and other values listed below. The
gas constant for air is R=0.287 kJ/kg-K.
--Given Values--
T1 (K) = 335
P1 (kPa) = 175
V1 (cm^3) = 600
r = 11
Q (kW) = 57
Speed...
Problem-2 (200) Air at 30 kPa, 200 K, and 250 m/s enters a turbojet engine in...
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...
A) Steam enters a horizontal pipe operating at steady state with a specific enthalpy of 2,663 kJ/...
A) Steam enters a horizontal pipe operating at steady state with a specific enthalpy of 2,663 kJ/kg and a mass flow rate of 0.1 kg/s. At the exit, the specific enthalpy is 1,531 kJ/kg. If there is no significant change in kinetic energy from inlet to exit, determine the rate of heat transfer between the pipe and its surroundings, in kW. B) Refrigerant 134a enters a horizontal pipe operating at steady state at 40°C, 3.1 bar and a velocity of...
Q.4 Air at 26 kPa,230 K, and 220 m/s enters a turbojet engine in flight as...
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...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Problem #3 (Total marks-14) Given: An engine has the following operating conditions per air-standard Otto cycle:...
Problem #3 (Total marks-14) Given: An engine has the following operating conditions per air-standard Otto cycle: Gasolina (SI) TYCO engine Pressure at beginning of compression process (Pal state 1 Temperature at beginning of compression process state 1) Volumetric compression ratio , Specific heat added during combustion process ( k g) (process 273) 300 1400 Data used for constant Specific Heat (standard cold-air assumption) Method: Ic ... 1.005 kJ/kg. K(C) = 0.718 kJ/kg.K. k=1.400, R -0.287 kJkgK Required: Draw a clear...
2. An aircraft with a single turbojet engine (with an inlet area of 1 m2) is...
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)....
The diffuser in a jet engine is designed to decrease the kinetic energy of the air...
The diffuser in a jet engine is designed to decrease the kinetic energy of the air entering the engine compressor without any work or heat interactions. Calculate the velocity at the exit of a diffuser when air at 100 kPa and 30°C enters it with a velocity of 358 m/s and the exit state is 200 kPa and 90°C. The specific heat of air at the average temperature of 60°C = 333 K is cp = 1.007 kJ/kg·K.
A four-cylinder four-stroke engine is modelled using the air
standard Otto cycle (two engine revolutions per cycle). Given the
conditions at state 1, total volume (V1) of each cylinder,
compression ratio (r), rate of heat addition (Q), and engine speed
in RPM, determine the efficiency and other values listed below. The
gas constant for air is R=0.287 kJ/kg-K.
--Given Values--
T1 (K) = 335
P1 (kPa) = 175
V1 (cm^3) = 600
r = 11
Q (kW) = 57
Speed...
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...
Air flows through a converging-diverging nozzle/diffuser. Assuming isentropic flow, air as an ideal gas, and constant specific heats determine the state at several locations in the system. Note: The specific heat ratio and gas constant for air are given as k=1.4 and R=0.287 kJ/kg-K respectively. --Given Values-- Inlet Temperature: T1 (K) = 360 Inlet pressure: P1 (kPa) = 583 Inlet Velocity: V1 (m/s) = 105 Area at inlet (cm^2) = 8.2 Mach number at the exit = 1.86 a) Determine...
Problem #3 (Total marks-14) Given: An engine has the following operating conditions per air-standard Otto cycle: Gasolina (SI) TYCO engine Pressure at beginning of compression process (Pal state 1 Temperature at beginning of compression process state 1) Volumetric compression ratio , Specific heat added during combustion process ( k g) (process 273) 300 1400 Data used for constant Specific Heat (standard cold-air assumption) Method: Ic ... 1.005 kJ/kg. K(C) = 0.718 kJ/kg.K. k=1.400, R -0.287 kJkgK Required: Draw a clear...
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)....
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