Improving parametric model of aircraft turboprop engine mass

DOI: 10.34759/vst-2020-2-81-89

Аuthors

Grigor'ev V. A.^*, Ryzyvanov I. P.^**, Zagrebel'nyi A. O.^***

Samara National Research University named after Academician S.P. Korolev, 34, Moskovskoye shosse, Samara, 443086, Russia

*e-mail: grigva47@gmail.com
**e-mail: iryzyvanov@gmail.com
***e-mail: zao_sam156@mail.ru

Abstract

The modern approach to the aircraft engine analysis as a part of an aircraft requires the presence of a perfect technique for the thermo-gas dynamic calculation (and such techniques do exist) and a mathematical model of GTE mass (based on the parametrical dependences, based on statistics of the already created GTEs). Considering the last circumstance, the assertion that such models need periodic updating is possible.

It is expedient for the turboprop engine mass models to present the equation of mass in the form of the sum of the gas turbine engine and the gearbox masses. The gas turbine engine mass should be expressed in the form dependency on the working process parameters (G_air,π_c,T_g).

This is explained by the fact that the gearbox mass does not depend on the working process parameters, and it is better to consider it by separate dependencies.

For the MGTE dependency actualization, the basic specification data on twenty three turboprops, such as G_air,π_c ,T_g, and a certification year were used.

Coefficients B, m₁ and m₂ were refined and corrected with the algorithm, proposed in the article.

Linear dependencies of m₁ on the airflow rate, and m₂ on the of pressure increase degree were obtained. To refine the k_Tg coefficient, which accounts for the temperature T_g impact on the engine mass, turbine models were developed, in which the structure being changed with temperature T_g. The corresponding elements of the turbine cooling system were being added, and the mass changed accordingly. This change was expressed by an approximating expression for kT_g.                                                                             

By approximation of integral quantitative values of  and assuming 1999 as a basic year, the expression for k_imp was obtained. This coefficient characterizes the of engine mass improving by the structural and technological solutions introduction.

The performed improvement of the parametric model equation of the turboprop mass allowed reducing its calculation error by 10%.

Keywords:

conceptual design of turboprop engine, mass model of turboprop engine, aircraft power plant weight, flying vehicle

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