Numerical Study of the Work Processes in the Gaseous Fuel Derated Gas-Turbine Engine Combustion Chamber

Aeronautical and Space-Rocket Engineering


Аuthors

Baklanov A. V.1*, Sabirzyanov A. N.2**

1. Kazan Motor Production Association, 1, Dementyeva str., Kazan, 420036, Russia
2. Kazan National Research Technical University named after A.N. Tupolev, Kazan, Russia

*e-mail: andreybaklanov@bk.ru
**e-mail: ansabirzyanov@kai.ru

Abstract

The article describes specifics of the gas turbine engine converting. 
Converting means transformation of an aircraft gas-turbine jet, which created in the nozzle a force (thrust) that moves an aircraft due to the kinetic energy of the gas flow, into the turboshaft gas-turbine engine of a general industial type with free power turbine, which converts the gas flow potential energy into the power, which translated to various ground-application mechanical units.
The operating conditions of gas turbine engines in various ground installations have their own specifics, differing from the operating conditions of aircraft engines as part of aircraft power plants:
– the thermodynamic cycle processes in ground installations;
– the cyclogram, operating time and operating range of engines as part of installations;
– ground operating conditions.
This specificity determines new requirements for the converted engine and introduces changes to their design and engineering practices. It differs from the methods adopted for the aircraft gas turbine engines (GTEs) development.
The general principles of such engine main components designing, such as compressors and turbines, are being based on the methodology of adopted for the aircraft gas turbine engines thermo-gas-dynamic computations and design. However, the combustion chamber is the component that undergoes the most significant modifications during the conversion process. The combustion chambers design and development for the converted engines have not been widely discussed in the technical literature. Thus, this article aims to provide an overview of the principles involved in developing a combustion chamber. These data should be a useful source for the designers of combustion chambers operating on gaseous fuels.
The describes the principles of derating and the areas of such engines application. Derating is a technical modification to an engine that allows reducing its power. Derating is achieved by lowering the compression ratio. In this case, the existing engine's low-pressure turbine is employed instead of the power turbine.
A combustion chamber has been developed for a derated gas turbine gaseous fuel engine. The design features of the engine and combustion chamber are presented. The combustion processes simulation was performed. 
The gas-dynamic flow structure was modeled with an approach based on solving the Reynolds-averaged Navier–Stokes equations, closed by a two-parameter standard k–ε turbulence model, which has proven itself effective in solving a wide range of engineering problems.
A sector representing the 1/70th of its size was selected to compute the developed combustion chamber. The computational domain of the combustion chamber sector flow path was discretized by a mesh that accounted for its geometry and consisted of approximately 350,000 elements.
Numerical data on the gas-dynamic and emission characteristics, as well as the unevenness of the temperature field at the outlet of the developed combustion chamber, have been obtained. It is demonstrated that the standard k–ε turbulence model and the laminar micro-flames model (FlameLet) together provide acceptable values of harmful emissions. The fuel combustion efficiency in the designed combustion chamber has been computed.


Keywords:

derated gas turbine engine, annular combustion chamber, combustion processes modeling, hazardous pollutantы, gaseous fuel combustion efficiency

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