Thermal protection of turbine blades

• Autorzy: Galitseyskiy B.
• Konferencja: Proceedings of the Fourth Seminar on Recent Research and Design Progress in Aeronautical Engineering and its Influence on Education/seminar(IV; 30.11-02.12.2000; Warszawa, Polska)
• Języki publikacji: EN

Abstrakty

EN

An algorithm of the first level computer-aided design of a gas turbine blade cooling system is described in the paper. Its main purpose is the choice of a rational cooling system. A general blade model is put forward for the decision on a given problem, which allows for arriving at majority of cases met in practice. The Monte Carlo method (LP-search) is used for construction of an algorithm searching for a optimum turbine blade cooling system. This algorithm is constructed on the basis of a generalised mathematical model of cooling system and a vector quality criterion. The generalised mathematical model of a cooled blade includes: limits imposed on functional geometrical parametere that ensure requirements of technology to be satisfied; evaluation technique of a target functions (criteria of quality), representing basic requirements of gas dynamics and strength; searching technique for a rational cooling system satisfying given requiremments to a large extent. Two criteria of quality are used as the target functions, one takes into account a degree of agreement between the given (calculated from the conditions of strength) and soughtafter (during search) blade temperature fields, and the second criterion of quality is represented by a relative charge of cooling air. The proposed searcging method for a rational cooling system of gas turbine blades enables one to choose from variants of blade cooling, thus, enabling the designer to shorten substantially the process of blade design.

Słowa kluczowe

EN

thermal protection; turbines; turbine blades

PL

ochrona termiczna; turbiny; łopatka turbiny

• Wydawca: Institute of Aeronautics and Applied Mechanics, Warsaw University of Technology
• Czasopismo: Research Bulletin / Warsaw University of Technology, Institute of Aeronautics and Applied Mechanics
• Rocznik: 2001
• Tom: nr 11
• Strony: 68--76
• Opis fizyczny: Bibliogr. 4 poz., rys., tab., wykr.

Twórcy

autor

Galitseyskiy B.

• Department of Avaition and Space Thermotechnics, Moscow Aviation Institute, Moscow, Russia