Estimated and analytical study of the possibility to develop a bypass turboprop with afterburning chamber based on baseline gas generator

Aeronautical and Space-Rocket Engineering

Thermal engines, electric propulsion and power plants for flying vehicles


DOI: 10.34759/vst-2020-1-152-163

Аuthors

Ezrokhi Y. A.*, Morzeeva T. A.**

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

*e-mail: yaezrokhi@ciam.ru
**e-mail: 30105@ciam.ru

Abstract

Analysis of development of engines for any type of aircraft, including those with high maneuverability, reveals that all engine-building enterprises of a world level both domestic and foreign permanently perform intensive development of their engines modifications directed to improving their thrust and economic characteristics, as well as service life and reliability. The exigency for such modifications development is dictated by the necessity to support the aircraft efficiency during its life span. The main tendency for the BTAC family development is associated with employing on the basic gas generator new fans of higher productivity and pressure rate. As practice shows, such an approach may allow drastic thrust increase (more than 20%) of the upgraded engine with concurrent reduction of its specific weight. To perform evaluation, a bypass turbofan with afterburning chamber, which basic parameters are typical to multimode engine of a fourth generation maneuverable aircraft. It was believed that the upgraded engine was developed based on the basic gas generator by installing a new fan with the specified values of air consumption Ga and pressure ratio n*a .

The dependencies of the takeoff thrust, gas temperature level in front of the turbine, bypass ratio, as well as total value of pressure ratio in compressors and HPC on the new fan parameters were obtained by the results generalization of parametric computational studies. They allowed evaluate probable characteristics of the upgraded engine, being developed based on basic gas generator and a fan of higher pressure rate and productivity. Representation of the obtained dependencies in the form of nomograms allow elucidate the most probable data while analyzing information available in the open press on parameters and characteristics of foreign engines, discarding erroneous values.

The results obtained in article allow also solving the problem often occurring while the engine modernization, i.e. define parameters of the new fan, which should be installed on the original basic gas generator to obtain a preset value of takeoff thrust of the upgraded engine, as well as temperature level increase at the turbine inlet necessary for its operation ensuring.

It was demonstrated in particular that for the thrust increase by 10% under impossibility to increase air consumption through the engine (for example due to the restriction from the air intake side) the pressure rate growth in the fan should be about 30%. The required temperature rise herewith should be no less than 120-130 K. However, if the throughput margin of the air intake, which can be employed, will be at least 5%, the similar engine thrust value can be obtained at significantly lower fan pressure ratio (of about 14%) and gas turbine inlet temperature (of no more than 85 K).

The capabilities of the obtained nomograms allowing revealing a set of data discrepancies on engines available in publicly-accessible information are demonstrated on the example of the afterburning turbofan parameters and characteristics analysis of General Electric engines family, developed on the basis of the F-404-GE-400 core

.

Keywords:

bypass turboprop with afterburning chamber (BTAC), baseline gas generator, engine modification, engine thrust, fan pressure ratio, air consumption, bypass ratio

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