題目：Jet Engine Performance and Condition Monitoring – Science and Complex Engineering Craftsmanship / Challenges in Testing Micro Gas Turbines
題目：Jet Engine Performance and Condition Monitoring – Science and Complex Engineering Craftsmanship
報告人：Prof. Stephan Staudacher（德國斯圖加特大學）
(Acatech) 院士，德國斯圖加特大學航空發動機研究所 (ILA) 所長，長期從事航空發動機性能建模及仿真、發動機性能試驗等研究。斯圖加特大學航空發動機研究所 (ILA) 現有20多名研究人員,他是德國宇航局 (DLR) 理事，曾擔任過德國航空航天技術學會 (DGLR) 主任委員。他領導和參與了多項德國工業界及經濟與能源部 (BMWI) 重大研究項目，研究團隊在航空發動機及燃氣輪機性能及測試研究領域處于國際領先地位。該研究所具有德國唯一的航空發動機性能測試臺，實驗設施和研究方法先進；并與世界著名航空發動機及燃氣輪機公司緊密合作，如羅-羅公司、MTU等工業企業，致力于將基礎研究成果應用于航空發動機性能提升。
NASA has established the basic methods of jet engine performance modelling already at the beginning of the 1970's, i.e. at the dawn of the computing age. Since that, decades of development have made the numerical methods of jet engine performance to be highly reliable, efficient and precise.
Even today the base of these methods form similarity parameters, which already have been developed and reported in the 1930's. With this in mind, the application of engine performance programs in today's engine development programs and engine condition monitoring approaches is reviewed. It becomes obvious how rigorous scientific approaches and complex engineering craftsmanship are merged in today's application of engine performance.
Some of the challenges still to be mastered are derived from the above. They lead to engineering questions which again need a mixture of rigorous scientific and mathematical approaches as well as complex engineering craftsmanship.
題目：Challenges in Testing Micro Gas Turbines
報告人：Dr. Christian Koch（德國斯圖加特大學）
Today, Micro gas turbines are used in a variety of applications. The range is from scaled flight vehicles for scientific use and military drones to R/C modelling. The focus of this paper is the application in scaled flight vehicles for free flight experiments in a scientific environment. These micro gas turbines are used in the flight vehicle itself, but are also tested intensively in ground test beds. The basic layout of such engines is as a single spool engine with a single stage radial compressor, a combustor with vaporiser sticks and a single stage axial turbine. This design is used for both as a jet engine and for power shaft application. When it comes to test the performance of engines, the typical instrumentation for this purpose has to be implemented into the engine. Due to the small size of the gas path and the small diameter of micro gas turbines this is very challenging. Therefore, no rakes for multi radius measurements are used but there are pressure and temperature probes in different circumferential positions installed. The averaging of the measured data is both needed in time to reduce noise and in space to get a representative value for each engine station. The challenge of designing a combustion chamber for a micro gas turbine was successfully solved by the Institute of Aircraft Propulsion Systems. This was done by using CAD-modelling, CFD-calculations, tests in a water table and the final test in the engine. By operating a micro gas turbine under transient conditions like a cold start or a hot reslam manoeuvre, differences between the performance simulations and the test data has been seen. One explanation is the characteristic of the combustor with its vaporising sticks under acceleration manoeuvres, which leads to a partial combustion outside the whole engine.
For all issues mentioned above solutions are found and are presented.