Computer-aided design and calculation of the blade front cavity cooling system of the gas turbine engine

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


Аuthors

Remchukov S. S.1*, Yaroslavtsev N. L.2**, Lepeshkin A. R.2***

1. Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia
2. Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: remchukov.sviatoslav@yandex.ru
**e-mail: yaroslavcevnl@mati.ru
***e-mail: lepeshkin.ar@gmail.com

Abstract

The gas temperature increasing prior to a gas turbine engine (GTE) turbine is one of the key ways to its efficiency increasing. Operating temperatures in the turbine are limited by the heat resistance of the material, which the parts, interacting with hot gases are made from. In this regard, the task of developing and improving complex cooled blades that use compressed compressor air as a cooler becomes urgent.

Improvement of front cavity cooling system of the GTE turbine blade was performed in the course of the presented work. Analysis of thermo-hydraulic characteristics of various cooling systems options was performed to determine the most suitable structure.

The best option is the structure of the “Frankel packing” type, which represents the aggregate of channels crossing at a certain angle.

The study of the turbine blade cooled front cavity module was being realized according to the developed technique for computer aided design and calculation of heat exchangers. The technique for computer aided design and calculation of the plate-type heat exchanger may be applied for solving the wide range of tasks, including gas turbine engine design.

The proposed technique allows evaluating thermal and hydraulic characteristics of the cooling system with minimal costs, as well as optimizing the geometry of the heat exchange surface. Thermal characteristics for the three pen cross-sections under consideration were obtained by the results of the computational study according to the proposed technique.

Experimental study of the blade, being considered, was conducted according to the modular finishing technology by the calorimetric measurement in a liquid metal thermostat. Modular finishing technology envisages experimental studies of simplified blade modules.

Thermal characteristics for the three pen cross-sections under consideration were obtained by the results of experimental study of the blade front cavity.

Comparative analysis results of the calculated and experimental thermal characteristics of the cooling system of the front cavity module revealed the following:

- the most significant discrepancy of thermal characteristics occurs in the area of the entry edge of the front cavity;

- the less activity of heat removal is observed at the entry edge section, which indicates the fact that the structure under consideration has a potential for the heat removal increasing in the entry edge;

- the characteristics discrepancy over all sections is no more than 10%, which fits into the error of the experiment.

Application of the computer-aided design and calculation of thermal and hydraulic characteristics technique allows evaluating the thermal state of the designed blade with minimal costs and sufficient accuracy. It is advisable to use the coefficient of heat transfer from the blade outer surface to the cooling air as an evaluating criterion of the blade cooling system efficiency.

Keywords:

computer-aided design and calculation, compact heat exchanger calorimetric measurement in a liquid metal thermostat

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