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In the power cycles so far considered the high-temperature, high-pressure gas expands in a turbine (steam power plant, gas turbine) or in the cylinders of an Otto or Diesel engine with reciprocating pistons In either case, the power becomes available through a rotating shaft Another device for expanding the hot gases is a nozzle Here the power is available as kinetic energy in the jet of exhaust gases leaving the nozzle The entire power plant, consisting of a compression device and a combustion chamber, as well as a nozzle, is known as a jet engine Since the kinetic energy of the exhaust gases is directly available for propelling the engine and its attachments, jet engines are most commonly used to power aircraft There are several types of jet-propulsion engines based on different ways of accomplishing the compression and expansion processes Since the air striking the engine has kinetic energy (with respect to the engine), its pressure may be increased in a diffuser The turbojet engine (usually called simply a jet engine) illustrated in Fig 813 takes advantage of a diffuser to reduce the work of compression The axial-flow compressor completes the job of compression, and then the fuel is injected and burned in the combustion chamber The hot combustion-product gases first pass through a turbine where the expansion provides just enough power to drive the compressor The remainder of the expansion to the exhaust pressure is accomplished in the nozzle Here, the velocity of the gases with respect to the engine is increased to a level above that of the entering air This increase in velocity provides a thrust

grub> find /grub/stage1 (hd0,0)

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(force) on the engine in the forward direction If the compression and expansion processes are adiabatic and reversible, the turbojet-engine cycle is identical to the ideal gas turbine cycle shown in Fig 812 The only differences are that, physically, the compression and expansion steps are carried out in devices of different types A rocket engine differs from a jet engine in that the oxidizing agent is carried with the engine Instead of depending on the surrounding air for burning the fuel, the rocket is selfcontained This means that the rocket can operate in a vacuum such as in outer space In fact, the performance is better in a vacuum, because no 'thrust' is required to overcome friction forces In rockets burning liquid fuels the oxidizing agent (eg, liquid oxygen) is pumped from tanks into the combustion chamber Simultaneously,fuel (eg, hydrogen, kerosene) is pumped into the chamber and burned The combustion takes place at a constant high pressure and produces high-temperatureproduct gases that are expanded in a nozzle, as indicated in Fig 814 In rockets burning solid fuels the fuel (organic polymers) and oxidizer (eg, ammonium perchlorate) are contained together in a solid matrix and stored at the forward end of the combustion chamber

The output means that the stage1 image was located on the (hd0,0) device 4 Finally, install the GRUB boot loader directly on the MBR of the hard disk Type

In an ideal rocket, the combustion and expansion steps are the same as those for an ideal jet engine (Fig 812) A solid-fuel rocket requires no compression work, and in a liquid-fuel rocket the compression energy is small, since the fuel and oxidizer are pumped as liquids

grub> setup (hd0) Checking if "/boot/grub/stage1" exists no Checking if "/grub/stage1" exists yes Checking if "/grub/stage2" exists yes Checking if "/grub/e2fs_stage1_5" exists yes Running "embed /grub/e2fs_stage1_5 (hd0)" 16 sectors are embedded succeeded Running "install /grub/stage1 (hd0) (hd0)1+16 p (hd0,0)/grub/stage2 / grub/grubconf" succeeded Done

81 The basic cycle for a steam power plant is shown by Fig 81 Suppose the turbine operates adiabatically with inlet steam at 6800 kPa and 82315 K (550 C) and the exhaust steam enters the condenser at 32315 K (50 C) with a quality of 096 Saturated liquid water

leaves the condenser, and is pumped to the boiler Neglecting pump work and kineticand potential-energy changes, determine the thermal efficiency of the cycle and the turbine efficiency

You are done But you should note that you really didn t make any serious changes to the system, because you simply reinstalled GRUB to the MBR (where it used to be) You would normally reboot at this point to make sure that everything is working as it should

82 A Carnot engine with H 2 0 as the working fluid operates on the cycle shown in Fig 82 The H 2 0 circulation rate is 1 kg s-' For TH = 475 K and Tc = 300 K, determine: (a) The pressures at states 1, 2, 3, and 4 (b) The quality xu at states 3 and 4 ( c ) The rate of heat addition

6:

If you need to create another variable, start by clicking the Edit menu at the top of the NXT-G software. Click the menu option labeled Define Variables. A small window, like the one shown in Figure 18-7, opens.

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