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 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.

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 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 system and method for controlling gas turbine engines with maximum thrust of less than 500 kgf. The control system includes electronic control unit (“ECU”), sensors and actuators. To ensure the requirement of compactness, physical control system simplicity but maintain stability and accurate operation for the engine, the control system does not include components such as Fuel Control Unit (“FCU”), alternator and corresponding rectifier circuits. A sensor, instead of alternator's wave form signal, is used to detect the rotational speed of the engine. Voltage regulation into the electric motor driving the fuel pump controls fuel flow, instead of the FCU. The control method consists of upper and lower limits computation calculation blocks of the control signal, and PID control algorithm block with coefficients designed to be suitable for the engine operating ranges. Control is implemented through a 7-step calculation process. Piecewise linearization modeling and tuning PID coefficients is also presented.