Download Advanced Gas Turbine Cycles: A Brief Review of Power by J. H. Horlock PDF

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By J. H. Horlock

Primarily this ebook describes the thermodynamics of fuel turbine cycles. the quest for top fuel turbine potency has produced many diversifications at the uncomplicated "open circuit" plant, concerning using warmth exchangers, reheating and intercooling, water and steam injection, cogeneration and mixed cycle vegetation. those are defined totally within the text.

A overview of contemporary proposals for a couple of novel fuel turbine cycles can also be incorporated. long ago few years paintings has been directed in the direction of constructing gasoline generators which produce much less carbon dioxide, or crops from which the CO2 should be disposed of; the consequences of a carbon tax on electrical energy pricing are thought of.

In providing this huge survey of fuel turbine cycles for energy new release the writer calls on either his educational adventure (at Cambridge and Liverpool Universities, the gasoline Turbine Laboratory at MIT and Penn country college) and his business paintings (primarily with Rolls Royce, plc.) The e-book should be crucial examining for ultimate yr and masters scholars in mechanical engineering, and for practicing engineers.

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Extra info for Advanced Gas Turbine Cycles: A Brief Review of Power Generation Thermodynamics

Sample text

COMPRESSOR LOSS 4. TURBINE LOSS 5. EQOUT= 0 6. 05 0 n 3 n 4 COMPONENT 5 Fig. 9. Work output and exergy losses in CBT gas turhine plant (all as fractions of fuel exergy). 9, and the combustion pressure loss is 3% of the inlet pressure to the chamber. The method of calculation is given in Chapters 4 and 5, but it is sufficient to say here that it involves the assumption of real semi-perfect gases with methane as fuel for combustion and no allowance for any turbine cooling. The work terms associated with the abstraction and delivery to the atmosphere are ignored in the valuation of the fuel exergy, which is thus taken as [-AGO].

But fixed values are assumed to cover a reasonable range of conditions. Accordingly, the fuel-air ratio may be expressed as + f = { T3 - TI [ 1 + ( x - 1)/7)c] - b}/u. 35) Using this expression to determinef for given T3 and Tl, mean values of (yg)% and (cpg)34 for the turbine expansion may be determined from data such as those illustrated graphically in Fig. 12. For the weak combustion used in most gas turbines, with excess air between 200 and 400%,f << 1. Strictly, for given T3 and Tl, the mean value of (cpg)34, and indeed (y&, will vary with pressure ratio.

1), with a maximum temperature T3 = TB and a pressure ratio r. The minimum temperature is taken as TA, the ambient temperature, so that TI = TA. For unit air flow rate round the cycle, the heat supplied is 4 B = cp(T3- T2),the turbine work output is WT = c (T - T4) and the compressor work input is wc = cp(T2- T I ) . 1) where x = r ( r l y y = T2/Tl= T3/T4is the isentropic temperature ratio. Initially this appears to be an odd result as the thermal efficiency is independent of the maximum and minimum temperatures.

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