Abstract: The invention offers an ultracapacitor-based power system solution with four main functional blocks which are power conditioning block, monitoring block, charge-discharge block and protection block. The proposed system has the advantage of working well in the environment of vibration, high temperature, has a large capacity to provide a large amount and radiates less heat compared to systems using traditional batteries. In addition, the system has functions to protect and stabilize the output voltage, and the operating parameters of the system is monitored continuously.

Abstract: This invention proposes the aerodynamic designing method for the central section of small size gas turbine engine type and it includes the following 8 steps: 1st step: checking to confirm if compressor outlet air meets demand specified by the central section; 2nd step: estimating the inner casing diameter based on practical experience; 3rd step: estimating the outer casing diameter; 4th step: estimating the combustor dome height and combustor length; 4th step: estimating the combustor dome height and combustor length; 5th step: estimating the combustor inner and outer liner diameters; 6th step: estimating the exit inner and exit outer diameters of the pre-diffuser; 7th step: estimating the dump gap; 8th step: verifying rotordynamic properties to determine if the shaft diameter assumption starting in the 2nd step is good enough.

Abstract: This invention proposes the aerodynamic designing method for the central section of small size gas turbine engine type and it includes the following 8 steps: 1st step: checking to confirm if compressor outlet air meets demand specified by the central section; 2nd step: estimating the inner casing diameter based on practical experience; 3rd step: estimating the outer casing diameter; 4th step: estimating the combustor dome height and combustor length; 4th step: estimating the combustor dome height and combustor length; 5th step: estimating the combustor inner and outer liner diameters; 6th step: estimating the exit inner and exit outer diameters of the pre-diffuser; 7th step: estimating the dump gap; 8th step: verifying rotordynamic properties to determine if the shaft diameter assumption starting in the 2nd step is good enough.

Abstract: A method for building a single-spool jet engine model consisting of five detailed steps: step 1: determining the structure of a turbojet engine to be modeled; step 2: Determine the thermodynamic information of the engine in detail; step 3: Put the engine information into the corresponding component module blocks, model structure according to the multi-loop algorithm and test the engine at the design point in a steady state; step 4: From the entire engine state at the starting point, save the sample as input to the dynamic model, describe the engine operation between the two stable operating points; step 5: Compare test data to make model errors and change unknown values to complete the model. With open source code for customizing and upgrading engine component modules, an open environment for research and development is provided, intended for research subjects of gas turbine engines used in industrial as well as aviation.

Abstract: This invention refers to the method of modeling and calculating aerodynamic characteristics of a multi-stage axial compressor using commercial software, method to identify the stable working range of module. The method includes step 1: object modeling; step 2: constructing the calculation model; step 3: problem solving. Step 4: results analysis.