Temperature Field Change at the Multi-Nozzle Combustion Chamber Outlet at Various Engine Operating Modes

Aeronautical and Space-Rocket Engineering


Аuthors

Baklanov A. V.

Kazan Motor Production Association, 1, Dementyeva str., Kazan, 420036, Russia

e-mail: andreybaklanov@bk.ru

Abstract

Introduction of a new combustion process in the combustion chamber requires conducting a number of research works aimed at the basic chamber parameters determining. One of the combustion chamber key parameters is the temperature field at the outlet from the flame tube. This parameter ensuring affects a lifespan of the nozzle guide vanes and the engine at large. Turbine blades are being subjected to the high temperature of the gas. These temperatures distribution by blade height (radial temperature distribution) is being set from the thermal stability condition and stresses occurring along the working blade pen. 
Dissection of the working blades of the nozzle guide was performed, and gas temperature at the outlet of the combustion chamber at various operating modes of the gas turbine engine (GTD) was determined in this work. The article presents the structure of the converted aviation GTD serving as a drive for the gas pumping unit supercharger.
Specifics of the multi-nozzle combustion chamber design operating on the natural gas consisted in the two-stage location of nozzles in the ring-type head are presented.
The article presents the test-bench equipment and describes the features of the experimental study conduction.
Thermal fields were determined for various operating modes of the engine and radial temperature distributions as well as relative ones were plotted. Comparison of the radial temperature distributions with maximal circumferential unevenness obtained while the HK-16-18CT, HK-16CT engine testing with the mass production combustion chamber and the NK-8-2U aviation liquid fuel engine was performed for the obtained results analysis. The positive and negative circumferential unevenness evaluation of the temperature field of these chambers was accomplished.
Inferences that the temperature field of the natural gas operating multi-nozzle combustion chamber is as close as possible by its parameters to the temperature field parameters of the NK-8-2U combustion chamber were drawn by the results of the works being performed.
The aviation combustion chamber transition from kerosene to the gaseous fuel can be realized without the temperature field parameters degradation.
Radial temperature distribution along the height of a nozzle corresponds to the traditional distribution.

Keywords:

combustion chamber, double-deck flame tube head, jet nozzle, temperature field, unevenness of temperatures, gas turbine engine

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