The comparative analysis of the selected construction types of axial compressor stage including the modal analysis

Abstract

The article concerns the issues of the scope of optimization of the gas turbine jet engine. These issues include limiting the weight and number of engine parts. One way to reduce the weight and number of components, including the compressor assembly, is to use the BLISK's replacement construction. The replacement construction should meet the strength requirement and the vibration spectrum as well. The paper presents a comparative analysis of the influence of rotational speed on the characters and the vibration frequency of the single rotor stage of the high pressure compressor. The analysis was carried out for two different design solutions of the blade-disk connection: the classical and integral. The comparative analysis focused on three important from the point of view of operation, the engine operating ranges: work on the ground (idle) and work during take-off and climb the aircraft.

FSI Application in the Parametric Analysis of Blade-Disc Connection of Turbojet Engine Compressor

“…where 𝑭 𝒓 is the resultant loading force of the part of the blade above the section of dimensions b and c [10]. An important aspect in the methods of designing blade connections with discs is the use of numerical methods and parametric models to optimize and assess the impact of specific variables on the strength and operation of such a structure [11][12][13][14][15][16][17][18]. Parameters, in this case, may be characteristic geometric dimensions and operating factors, e.g., such as rotational speeds or pressures affecting the distribution of aerodynamic loads acting on the blade.…”