並列タイトル等Evaluation of thermocouple and thermal radiation instrumentation for measuring gas turbine combustor liner temperature
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-784
一般注記Temperature measurement techniques for a practical combustion chamber liner wall were investigated. Fourteen ways of sheathed thermocouple installations on thin stainless steel plated simulating a combustor liner wall were tested by flowing a hot gas on one side and cold air on the other side under atmospheric conditions. Temperature ranges of the hot gas and the cold air were 542～612K and 317～326K, respectively. The tested stream velocities were in the ranges of 70～87m/s for the hot gas and 14～70m/s for the cold gas. It was found that Reynolds numbers of the hot and cold streams have no significant effects on the magnitude of the error and that only the method of installation determines the accuracy of the measurements. It was also found that radiation measurements of the black coated wall surface may cause significant error because there is a big temperature gradient across the coating layer.
資料番号: NALTR0784000
レポート番号: NAL TR-784
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=45042&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース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