Abstract
Abstract The paper presents a method of calculation gas turbine engine compressor or low-pressure turbine working blade profile for student training. This method of calculation was prepared for working blades with and without shroud shelves. This method provides a calculation technique to reduce the load on blade root part and the determination of blade profile stress distribution and the comparison before and after reduction of load.
Highlights
One of the most loaded and, as follows, the most expensive parts in civil aviation is the engine
The manuscript considers the method of calculation the working blade, that can provide an in-depth understanding for aviation specialty students of details calculation of a complex form, the nuances and issues, and for those who are interested in calculation of such algorithms
Is to note that for the student training the high accuracy of calculations that computer modelling can provide is not so important, but it is important that clear picture of the whole calculation process that lead to understanding of the concept logic
Summary
One of the most loaded and, as follows, the most expensive parts in civil aviation is the engine. The manuscript considers the method of calculation the working blade, that can provide an in-depth understanding for aviation specialty students of details calculation of a complex form, the nuances and issues, and for those who are interested in calculation of such algorithms Nowadays, calculations of this kind of details are done using computer modelling techniques, but during the training process, such type of modelling is not always able to provide clear calculation details. Clear is the connection link between the output data, the wide range of intermediate and final results, which provide additional possibilities for the convenience of an in-depth analysis of the calculations This allows to implement further improvements, increasing the accuracy of the calculation. The analysis of the results can be expanded by changing blades materials and by varying engine operating modes
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