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給氣冷却器の性能 : 第2報 逆流型冷却器の裝備性能
https://jaxa.repo.nii.ac.jp/records/35228
https://jaxa.repo.nii.ac.jp/records/35228b108b031-27b8-4dee-b5d6-21e9aa9ece59
| 名前 / ファイル | ライセンス | アクション |
|---|---|---|
SA4146354.pdf (1.5 MB)
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| Item type | 紀要論文 / Departmental Bulletin Paper(1) | |||||||||
|---|---|---|---|---|---|---|---|---|---|---|
| 公開日 | 2015-03-26 | |||||||||
| タイトル | ||||||||||
| タイトル | 給氣冷却器の性能 : 第2報 逆流型冷却器の裝備性能 | |||||||||
| 言語 | ||||||||||
| 言語 | jpn | |||||||||
| 資源タイプ | ||||||||||
| 資源タイプ識別子 | http://purl.org/coar/resource_type/c_6501 | |||||||||
| 資源タイプ | departmental bulletin paper | |||||||||
| その他のタイトル（英） | ||||||||||
| その他のタイトル | Characteristics of the Installed Engine-Air-Cooler System. : Part II: -Overall Performance of the Aero-Engine, Using an Engine-Air-Cooler of Parallel-Counter-Flow Type. | |||||||||
| 著者 |
西脇, 仁一
× 西脇, 仁一
× NISIWAKI, Niiti
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| 出版者 | ||||||||||
| 出版者 | 東京帝國大學航空研究所 | |||||||||
| 出版者（英） | ||||||||||
| 出版者 | Aeronautical Research Institute, Tokyo Imperial University | |||||||||
| 書誌情報 |
東京帝國大學航空研究所報告 en : Report of Aeronautical Research Institute, Tokyo Imperial University 巻 18, 号 246, p. 477-499, 発行日 1942-12 |
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| 抄録（英） | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 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. | |||||||||
| 書誌レコードID | ||||||||||
| 収録物識別子タイプ | NCID | |||||||||
| 収録物識別子 | AA00387631 | |||||||||
| 資料番号 | ||||||||||
| 内容記述タイプ | Other | |||||||||
| 内容記述 | 資料番号: SA4146354000 | |||||||||
