The aircraft piston engine conjugate heat transfer model

Maintaining high aircraft’s propulsion system reliability requires a good knowledge of engine’s heat transfer conditions at each engine running time. Even though the flow around the cylinder may be steady, the heat flux from the engine is not evenly distributed. This is caused by varied engine head and fins geometry and uneven heat transfer coefficient distribution. The lack of knowledge of the local heat transfer coefficient values and time coefficients for the transient heat transfer make it unfeasible to make an analytical model for a given geometry. One transient Computational Fluid Dynamics simulation does not solve the heat transfer fully. Only a conjugate simulation allows an in-depth analysis of a transient heat transfer. The Combustion and species transport fluid simulation is coupled to the temperature field solid simulation. This work presents the methods and results of such conjugate heat transfer simulation. The change of heat flux parameters in respect to time is shown. The results are verified by the real engine measurements

Modelling of a Large Rotary Heat Exchanger

The first simulation consists of a partial cut-out of gas flow canal between the heat exchanger fins. The simulation is steady state and mainly provides the information about the heat transfer coefficient and pressure drop across the canal. The second simulation takes into account the complete system of rotary heat exchanger. It is a transient simulation with moving mesh. Then the heat transfer and air flow parameters are presented as a porous volume with a heat transfer model and rotational multi zone interface conditions. This simplification is accurate providing much better performance as the number of mesh nodes is much smaller. The methodology of the model setup is presented

The swirl ratio influence on combustion process and heat transfer in the opposed piston compression-ignition engine

In order to maximise engine heat efficiency an engines charge flow must be properly designed -especially its swirl and tumble ratio. A two-stroke compression-ignition opposed piston engine reacts to engine swirl differently compared to a standard automotive engine with axially symmetric combustion chamber. In order to facilitate direct fuel injection, high-pressure injectors must be positioned from the side of combustion chamber. Depending on the combustion chamber geometry the swirling gases impact greatly how the injection stream is formed. If the deformation is too high the high temperature combustion gases can hit the piston surface or get into gaps between the pistons. This greatly affects the heat lost to the pistons and raises their local temperature. More atomised injection stream is more prone to swirling gas flow due to its reduced droplet size and momentum. The paper presents simulation results and analyses for different intake process induced swirl ratios and different types of combustion chambers in an experimental aviation opposed piston engine

CFD numerical simulation of the indirect cooling system of an internal combustion engine

The paper presents an analysis of the fluid flow in the cooling system of an internal combustion engine with oposite pistons. The purpose of the work was to optimize the flow of fluid through the channels located in the engine block. Simulation studies and subsequent iterations were performed using Ansys Fluent software. Two-equation k-epsilon turbulence model was used in the simulation model. Boundary and initial conditions were taken from previously made simulations conducted in AVL Boost software. The average wall temperature of the cylinder and the temperature of the outer walls of the cylinder were assumed for simulations. The results of the analyzes were graphically illustrated by the speed streamline distribution of velocity fields and temperature