給氣冷却器の性能 : 第2報 逆流型冷却器の裝備性能
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概要
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1. Performance of the Aero-Engine. Assuming FP_e≒kG_t k=1/w, w≒0.00085kg/FP/sec. where FP=(propeller horsepower)+(the horsepower necessary to drive supercharger)=FP_b+FP_s G_t=rate of flow of the engine air (kg/sec.) then [numerical formula] where suffix o indicates the case without cooler, and suffix 3 the state of the engine air in front of the suction port. FP_e is calculated with the aid of equations (3. 2. 9) or (3. 2. 9'), and the ratio FP_b/FP_<b0> with the aid of equations (3. 2. 10). 2. Drag of the installed cooler system FP_d=Drag horsepower of the cooler [numerical formula] Assume the weight of the cooler per unit area, [numerical formula] 3. Overall performance of the aero-engine, using the above mentioned equations and the relations explained in the first report. The overall performance of the aero-engine, using engine-air-coolers of the parallel-ccunter-flow type is examined for a number of cases, namely, Flying height=6, 8, 10, 12, 14km.; Boost pressure=760, 760+300mm Hg; Flowing speed of engine-air in the cooler core, v_t=20, 50, 100m/sec.; Temperature efficiency of cooler, η_t, η_θ=40, 60, 80, 90%; Area ratio, (b_1'=F_k'/F_1), (b_4'=F_k'/F_4), =1, 2, 3, 5. and putting the Adiabatic overall efficiency of supercharger=65% Adiabatic thormal efficiency of supercharger=55% Flying velocity=650km/hr. Figs.4〜32 illustrate the calculated performance, where the convex full-line curves indicate (FP_b/FP_<b0>-FP_d/FP_<b0>). 4. Results. (i) In order to obtain better overall performance (FP_b/FP_<b0>-FP_d/FP_<b0>) of the aeroplane by using the engine-air cooler, it is preferable to use a) in which the cooler has a higher temperature efficiency value, namely 80〜90〜95%, b) in which the flowing velocity values of the engine-air in the cooler-core are smaller, namely 20〜30〜50m/sec. and c) in which the area ratio b_4' of the cooler area to the outlet area of the cooler-duct. is larger, (ii) in which the maximum gains in the performance in these examples are 10%, for flying height 10km, boost pressure 760mm Hg, 14%, for flying height 10km, boost pressure 760+300mm Hg 14%, for flying height 12km, boost pressure 760mm Hg. (iii) In the case of the inter-cooler, it is desirable to take the pressure ratio of the first stage supercharger as large as possible.
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