Developing a Mathematical Modelling Code for Keeping the Power of Multi Turbocharged Engines at Flight Altitudes

Abstract

In this paper, a code is developed in C++ programming language aiming to select and introduce a well-chosen propulsion system for appropriate operation in an aircraft. By using a suitable turbocharged engine, the inlet pressure of the engine manifold will increase to a level equal to the pressure at sea level. Therefore, the aircraft engine will not notice the drop of pressure caused by the increase in altitude. Consequently, the engine power will not be reduced. On the other hand, at high altitude, using only one turbocharger is not adequate to supply engine inlet pressure and flow rate equivalent to sea level conditions, requiring the use of more turbochargers. The code developed in this study will be able to introduce the appropriate turbocharged engine based on the flight altitude and the required power engine of an air vehicle. The altitude defined in this code ranges from 5 to 30 kilometers, which leads to a selection of one to three turbochargers plus a number of intercoolers, according to user input parameters. The objective function of this optimization problem is defined as a function of turbochargers efficiency. However, this objective function can be modified according to the user requests and requirements.

Study of super/turbocharger system for helicopter diesel engine

“…Thus, when it rises off the ground to an altitude about 6,000 m above mean sea level, the atmospheric density is halved. Such a significant atmospheric density reduction at altitude (h) has a great impact on the efficient engine running, its reliability and resources [4]. This is due to the fact that during the ascent of an aircraft with internal combustion engine (ICE), the air mass entering its cylinders decreases.…”