By F. Whittle
For the 1st time simplified tools of facing gasoline turbine thermal cycles, and additional theoretical thoughts, were embodied right into a concise textbook. the entire significant elements of the topic are coated in a accomplished and lucid demeanour. Examples are incorporated for larger readability
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Additional resources for Gas Turbine Aero-Thermodynamics. With Special Reference to Aircraft Propulsion
105 = 1282'/sec. 98 lb/sec. z :. 49 lb/sec. 6 :• ue /ue = 755. 6 = . 926. 1 Ib/sec/ft. :. /ft. 0304 lb/ft. 49 lb/sec. For h) the max. 893 .. 0331 lb/ft. 6 0 :. e. e. 49 S = 3000 x 1282 = 776 lbs. 5(3000 — 2116) = 442 lbs. The difference, of course, is due to the reduction of internal pressure as the air accelerates into the nozzle. 43 or 43%. 6 = 1481 32. 2 lbs. e. 2% of the thrust. When the pressure ratio to a convergent nozzle exit is the value corresponding to max. e. 893, the nozzle is said to be `choking'.
6. 0, what is the wave velocity u 0 when ° Ts0 = 220 K? 7429 :. e. nearly three times acoustic speed at 220° K. In Fig. 0 and brings out very clearly the very large reduction of kinetic energy which can occur across a normal shock wave. e. 3% of u0 . 7 Fo Fig. 0 28 to a reduction of kinetic energy of 89% approximately. e. e. a loss. This matter will be discussed below. From z = + O0 it is evident that the asymptotic limit of z is 1with the assumption 6 600 of constant Kr,. ' The Efficiency of Shock Compression energy out but the efficiency energy in of shock-compression is not so easily defined, and there is some inconsistency among engineers in definition.
D. 15 1 -fE ~6(ts2 -1) (5-13) 56 Case 4. 2. In this case the situation reverts to that in which the system is unaffected by the static pressure at exit from the choking nozzle. The system is represented in Fig. 8. Fig. 5-8 Using the relationships shown on Fig. 5774 RTT (1 — fe)t . s \/6(ts 1 -~E - 1)(1 -Fe) (5-17) HE from which it is more readily seen that, for a given value of ~~E , if any two of are fixed, so is the third. 4203 1680 ft/sec, utz = 147. :. 02 5 77 :. 616. D. 5774\/6(t8 -1) [ts (1 0E)] 3 which is again relevant to relatively moving nozzles (see over).