Effectiveness estimation of turbo-compound scheme application on purpose of indicators increasing of aircraft piston diesel engine of 300 H.P.

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles

DOI: 10.34759/vst-2019-4-98-107


Baryshnikov S. I.*, Kostyuchenkov A. N., Zelentsov A. A., Lukovnikov A. V.**

Central Institute of Aviation Motors named after P.I. Baranov, CIAM, 2, Aviamotornaya str., Moscow, 111116, Russia

*e-mail: stanislawish@ya.ru
**e-mail: Lukovnikof@mail.ru


The goal of the presented work consisted in improvement of the engine basic indicators — specific power and effective specific fuel consumption (ESFC). This goal achieving is possible though three methods, based on a heat balance equation, namely, effective power increasing, as well as heat emission decreasing into cooling system and exhaust energy utilization. Effective power increase seems to be a conservative method that ensures relatively low performance increase, and is the main research trendHeat removal limitation to the cooling system was actively studied in 90-s, and currently considered unworkable. Thus, the best way to increase the engine indicators radically is the exhaust gases energy utilization.

There are many ways realization, including mechanical and electric compounding, the Renkin cycle application, thermoelectrical generators. However, the most efficient way from the niewpoint of specific parameters is mechanical compound.

Historically, turbo-compounding is a logical continuation of turbocharging. Turbo-compound engines are the pinnacle of aviation piston engines. VD-4K and Napier Nomad engines represent the examples of such engines, demonstrating at that time the unsurpassed fuel efficiency levels.

A six-cylinder boxer four-stroke turbocharged CI water-cooled engine was selected for the purpose of this study. The key factor for the diesel engine selection was the high air to fuel ratio, which was about two times higher than this for the gasoline engine. Owing to this, other things being equal the compound turbine will ensure twice as much power.

In this work, identification of the basic engine was being performed with the AVL BOOST software. The Patton, Nitschke, Heywood friction model, allowing determine friction losses based on the engine arrangement; Vibe combustion model, and Woschni 1978 heat exchange model were employed. Based on the obtained model a turbo-compound modification was developed. Optimization of basic parameters, such as charge pressure, pressure drop on both power and compressor turbines, gas distribution phases and ignition advance angle.

Based on the obtained results, a comparison of three variants of the engine, such as basic one; with the Garret turbine, which roughly corresponds to domestic prospective turbines; and the one with reference turbine was performed.

As a whole, the achieved results fit theoretical estimations with high degree of precision, with the exception of the exhaust gases temperature: contrary to the initial expectations, the temperature decreased. However, this result fits the pattern, established in other authors’ works.

The results of the comparison revealed that the power increment in the turbo-compound engine could achieve 10%, and ESFC reduction could achieve 11%.


turbocharging, turbo-compound, diesel engines, four-stroke engines, aviation engines


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