An Analysis Of The High-Temperature Highpressure Turbine Working Blades Cooling System For Next-Generation Gas Turbine Engines

The topic of this work is relevant and has great practical importance.At present,the high-pressure turbine of an aircraft engine has a service life approximately half that of a compressor,for example.This problem is particularly relevant when creating engines of new generations,because at the same time it is necessary to solve several problems:improving the design,the use of new,high-strength materials and coatings,etc.Since the working and nozzle blades of the turbine work in direct contact with high-temperature gas,the greatest difficulty lies in ensuring the operability of the turbine design at such high temperatures,as well as in the reliability and service life of nozzle and rotor blades,especially in a high pressure turbine.The aim of this work is to investigate a new type of cooling blade of a high-pressure turbine of a bypass turbojet engine,which would exceed the currently used blade designs in its characteristics.This work is divided into four main parts.First,an in-depth review of the literature on existing research in the field of cooling turbine blades of GTE,a review of the operational parameters of modern engines,considered the design features of cooled turbine blades.In the second part the description of the software in which calculation of the investigated blade will be made is resulted and the basic methods of calculation used for calculation of its temperature condition are described.In the third part,the design features of the impeller blade of the high-pressure slit cooling turbine are considered and its design schemes and three-dimensional models used in the further calculation are given.Based on the research results,the final part of this work presents calculations of the temperature state of the blade in the ANSYS CFX workspace.The results showed that the created cooling air shroud coming out on the high-pressure side covers a large area of the blade wall,which provides a higher cooling efficiency than with the known film cooling.These results clearly reflect the technical novelty of this work and provide reasonable recommendations for the continuation of the development of this design scheme for its further use.