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.

The article describes the impact of the gas turbine engine low-pressure turbine blade shroud shelf on the blade profile stress position. Attention is focused directly on the impact of the location of the gravity centre of the shroud shelf on blade stress distribution at the three most critical points of the profile. The paper describes the details of the calculation and the required expressions provided, as well as the results of the calculation example with clear graphical dependencies.

Within the Institute of Aeronautics, a working diagnostic device was developed, which is able to perform remote temperature monitoring of bearings with a set periodicity, as well as warns the technical staff about temperature rises above the operating limit. The article describes the components of the device and the conditions for their selection. Relatively long-term experimental tests were performed to fully test the device and verify its performance. In the course of these tests, a comparison of the developed device with other bearing control devices was also made in order to be able to draw conclusions as to whether our device is effective in controlling the technical condition of bearings. This article summarizes the results of these researches.