ZrO2/Ni系完全傾斜機能型燃焼器の高空性能試験

• Material Type: 規格・テクニカルリポート類
• Title: ZrO2/Ni系完全傾斜機能型燃焼器の高空性能試験
• Author/Editor: 黒田, 行郎; 佐藤, 政裕; 只野, 真; 森谷, 信一; 日下, 和夫; 熊谷, 達夫; 毛呂, 明夫; 田口, 秀之; 川又, 善博; 三木, 陽一郎; Kuroda, Yukio; Sato, Masahiro; Tadano, Makoto; Moriya, Shinichi; Kusaka, Kazuo; Kumagai, Tatsuo; Moro, Akio; Taguchi, Hideyuki; Kawamata, Yoshihiro; Miki, Yoichiro
• Author Heading: 黒田, 行郎; 佐藤, 政裕; 只野, 真; 森谷, 信一; 日下, 和夫; 熊谷, 達夫; 毛呂, 明夫; 田口, 秀之; 川又, 善博; 三木, 陽一郎; Kuroda, Yukio; Sato, Masahiro; Tadano, Makoto; Moriya, Shinichi; Kusaka, Kazuo; Kumagai, Tatsuo; Moro, Akio; Taguchi, Hideyuki; Kawamata, Yoshihiro; Miki, Yoichiro
• Publication, Distribution, etc.: 航空宇宙技術研究所
• Publication Date: 1997-05
• Publication Date (W3CDTF): 1997-05
• Alternative Title: High altitude performance tests of perfect ZrO2/Ni FGM chamber
• Periodical title: 航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory
• No. or year of volume/issue: 1327
• Volume: 1327
• Pages: 1-18
• ISSN (Periodical Title): ISSN : 0389-4010
• Text Language Code: jpn
• Subject Heading: 2液式ロケットエンジン; 軌道変換用エンジン; FGM; 完全傾斜機能材料; 完全傾斜機能型燃焼器; ZrO2/Ni系FGM燃焼機; 熱応力緩和層; 高空性能試験; HAPT; 噴射器着火確認試験; 冷却特性; bipropellant rocket engine; orbiting maneuvering engine; functionally graded material; functionally graded type combustor; ZrO2 Ni FGM combustion chamber; thermal stress relaxation layer; high altitude performance test; injector ignition check test; cooling characteristics
• Target Audience: 一般
• Note (General): 出版タイプ： NA; 将来の宇宙往還機用軌道制御システムの実現には、既存の2液式エンジンより高性能で耐久性を有する再使用型エンジンの実用化が不可欠である。この要求に応えるため、エンジンの高性能化に対してはフィルム冷却率を0%とした噴射器を用い、また燃焼器の耐久性向上の対応にはセラミックス系の傾斜機能コーティングを燃焼器の内壁面に施した推進システムを構成した。燃焼器の内面に施したZrO2コーティング層と金属の接合界面の強度を高めるために、燃焼器の内壁面から冷却側の金属までの材料組成を連続的に変えたZrO2/Ni系の完全傾斜機能構造を有する熱応力緩和層を適用した。試作した燃焼器を用いて、高空性能試験を行いエンジンの性能に関する基礎データを取得し、合わせて燃焼の安全性を確認した。また、高空性能試験に先立って製作した噴射器の着火確認試験を行い、長秒時試験ではエンジンの熱特性に関する基礎データを取得した。; Ceramic thermal barrier coating systems will be of growing importance for the reusable high performance Orbiting Maneuvering Engine (OME). These coatings have been previously studied for many years aiming to improve the resistance to extreme conditions of high temperatures and oxidizing atmosphere at the inner walls of the combustion chamber. These are very attractive ways to achieve a high performance engine because of their potential for reducing the film-cooling requirements in the rocket chamber. However, as shown in the test results of the thermal fatigue properties of Functionally Graded Materials (FGM) specimens, due to the large difference in thermal coefficient of expansion between the coating materials and the metal wall and the low ductility of the ceramic coating, cracks occur in the ceramic coating layer or spalling occurs during repeated thermal cycles. One method of improving adhesion of the coating to the metal wall is to apply FGM. In this test series, High Altitude Performance Tests (HAPT) of a regeneratively cooled 1,200 N thrust engine composed of ZrO2/Ni FGM chambers were conducted with Nitrogen Tetroxide/Monomethyl Hydrazine (NTO/MMH) bipropellant. To enhance the engine performance, the high performance unlike quadlet element injector was employed. The film cooling fraction was reduced to zero percent of the total fuel flow rate to obtain high performance. The combustion chamber used in HAPT was composed of perfect ZrO2/Ni FGM, i.e., the chamber inner wall was made of ZrO2-8 percent Y2O3 (8YSZ: 100 vol percent), the cooling wall side was made of pure Ni and intermediate materials were ZrO2/Ni FGM. The method of applying perfect FGM is to spray 8YSZ mixed with NiCoCrAlY onto a mandrel and electro-form onto the sprayed 8YSZ (24.5 vol percent)/NiCoCrAlY (75.5 vol percent) FGM layer. It is believed that this reversed process of composing perfect FGM will provide an improved ceramic-metal bond between the sprayed FGM layer and electro-formed FGM layer. This series of tests was initiated at Kakuda Research Center (KRC) to evaluate the real engine performance and to study the effect of FGM coatings on thrust chamber life. A total of 50 firing tests including sea level tests were performed to evaluate the engine performance in terms of vacuum specific impulse (I(sub spv)), and also to obtain chamber thermal data. The high performance of the engine, i.e., I(sub spv) = 318 s at P(sub c) = 1.4 MPa, was verified. This paper also presents the preliminary design concept of FGM, used for the thrust chamber, which prolongs thrust chamber life.; 資料番号: AA0001078000; レポート番号: NAL TR-1327
• Data Provider (Database): 国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）; https://irdb.nii.ac.jp
• Original Data Provider (Database): 宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ