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2 1. Diffuser Compressor Combustion Turbine Nozzle chamber TA 6. 3 Iin P = const. 2 P= const. Figure 1: Simple schematic of a basic jet engine. 5 Yout 6 The thrust produced by the engine is due to the difference in momentum of the inlet and outlet fluid velocities (measured relative to the aircraft - so $v_{inlet}$ is equal to the speed of the plane), F = (mv)$_{exit}$ - (mv)$_{inlet}$ = m ($v_{exit}$ - $v_{inlet}$) The propulsive power of the engine is then W = F$v_{aircraft}$ = m$v_{inlet}$ ($v_{exit}$ - $v_{inlet}$) And finally, the propulsive efficiency of the engine is defined as Propulsive Power W $\eta_P = \frac{Propulsive Power}{Energy input rate} = \frac{W}{Q_{in}}$ where $Q_{in}$ is the heating value of the fuel used in the combustion process. (1) (2) (3)

          2
1.
Diffuser Compressor Combustion Turbine Nozzle
chamber
TA
6.
3
Iin
P = const.
2
P= const.
Figure 1: Simple schematic of a basic jet engine.
5
Yout
6
The thrust produced by the engine is due to the difference in momentum of the inlet and outlet
fluid velocities (measured relative to the aircraft - so $v_{inlet}$ is equal to the speed of the plane),
F = (mv)$_{exit}$ - (mv)$_{inlet}$ = m ($v_{exit}$ - $v_{inlet}$)
The propulsive power of the engine is then
W = F$v_{aircraft}$ = m$v_{inlet}$ ($v_{exit}$ - $v_{inlet}$)
And finally, the propulsive efficiency of the engine is defined as
Propulsive Power W
$\eta_P = \frac{Propulsive Power}{Energy input rate} = \frac{W}{Q_{in}}$
where $Q_{in}$ is the heating value of the fuel used in the combustion process.
(1)
(2)
(3)

Show more…

2
1.
Diffuser Compressor Combustion Turbine Nozzle
chamber
TA
6.
3
Iin
P = const.
2
P= const.
Figure 1: Simple schematic of a basic jet engine.
5
Yout
6
The thrust produced by the engine is due to the difference in momentum of the inlet and outlet
fluid velocities (measured relative to the aircraft - so vinlet is equal to the speed of the plane),
F = (mv)exit - (mv)inlet = m (vexit - vinlet)
The propulsive power of the engine is then
W = Fvaircraft = mvinlet (vexit - vinlet)
And finally, the propulsive efficiency of the engine is defined as
Propulsive Power W
= (Propulsive Power)/(Energy input rate) = (W)/(Qin)
where Qin is the heating value of the fuel used in the combustion process.
(1)
(2)
(3)

Added by Gregory C.

Chemistry: Structure and Properties

Nivaldo Tro 2nd Edition

Instant Answer

Solved by Expert Adi S

07/21/2023

Step 1

To determine the pressure and temperature at the turbine exit, we need to go through the cycle of the jet engine. The cycle consists of the following steps: diffuser, compressor, combustion chamber, turbine, and nozzle. Step 2: Diffuser The diffuser is the Show more…

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Texts: A turbojet aircraft is flying at an altitude of 10,000 m, where the ambient pressure is 37 kPa and the temperature is -50°C. When it is cruising at a speed of 700 km/h, air enters the compressor at 42 kg/s, which has a pressure ratio of 10 (meaning the air is compressed by a factor of 10), and the temperature of the gases after the combustion process (into the turbine - location 4) is 1100°C. 1. Determine the pressure and temperature of the gases at the turbine exit (location 5). (Hint: You will have to go through the cycle for this, and you may assume that the fluid stream is entirely made up of air, with a constant value of the specific heat). 2. Determine the velocity of the fluid stream at the nozzle exit (location 6). 3. What is the propulsive efficiency of this cycle? We were given the following advice to guide us in solving this problem: Diffuser Compressor Combustion chamber Turbine Nozzle Figure 1: Simple schematic of a basic jet engine The thrust produced by the engine is due to the difference in momentum of the inlet and outlet fluid velocities (measured relative to the aircraft - so vinlet is equal to the speed of the plane), F = (mv)exit - (mv)inlet = m (vexit - Vinlet) (1) The propulsive power of the engine is then W = Fvaircraft = nVinlet (Vexit - Vinlet) (2) And finally, the propulsive efficiency of the engine is defined as Propulsive Power np = Energy input rate / Qin (3) where Qin is the heating value of the fuel used in the combustion process.

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