Statistic data application for narrow-body aircraft engines combustion chambers preliminary design

Aeronautical and Space-Rocket Engineering


DOI: 10.34759/vst-2022-4-151-160

Аuthors

Orlov M. Y.*, Zrelov V. A.**, Orlova E. V.***

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

*e-mail: adler65@mail.ru
**e-mail: zrelov07@mail.ru
***e-mail: orlova_e_v@63.ru

Abstract

The article presents the results of studying parameters and geometric ratios for combustion chambers of narrow-body aircraft engines with different combustion technologies.

Due to volume reduction of passenger transportation by world aviation, the wide-fuselage aircraft employing is being decreased. Narrow-body aircraft are once again becoming the most common in civil aviation. With a view to the political situation, the development of national narrow-body aircraft and their engines is becoming an up-to-date task for Russia. It is going to be solved in the form of the concept of import substitution. In terms of time consumption, the engine design is a more durable process than the aircraft development. Thus, it is important that even at the stage of preliminary engine design its optimal structure is selected. Combustion chamber is one of the problematic ones at the preliminary design of the engine components. This fact is associated with the presence of combustion process in it. It is impossible to compute the combustion chamber workflow and characteristics without its detailed geometry. Thus, the authors propose wide employing of statistical data on the existing products at the preliminary design stage. Within the framework of this work, the data on more than fifty narrow-body aircraft engines was accumulated and analyzed. Technical data, diagrams and drawings of their combustion chambers were analyzed. The authors considered chronology of the combustion chambers development of both domestic and foreign engines of narrow-body aircraft. The ranges of the thrust changing, total pressure ratio and gas temperature prior to the turbine were determined.

Thus, it was found that the pressure ratio increased 3.5 times while transition from the third to the fifth generation engines, and the gas temperature prior to the turbine by 800K and more. This was achieved, among other things, by combustion technology improving. Analysis of the change in the ratio of the combustion chamber length to the maximum height of its profile revealed that it decreased by about 1.7 times from the mid-1960s to 2015.This is the result of the low-toxic combustion chambers creation. Evaluation of the ratio change in the combustion chamber length to the engine length has been performed for the same period. The distance from the fan blade inlet (inlet device) to the turbine outlet was used as characteristic length of the engine. This distance is of interest in terms of the engine work process implementation. The lowest achieved values correspond to the TAPS and RQL combustion technologies. The value of this ratio is 1.5 times higher for the conventional combustion scheme. The data presented in the article allows performing weight-and-size-characteristics evaluation of the engines being developed with the specified parameters (the pressure rise degree, temperature at the engine inlet) at the preliminary design stage. Evaluation of various technologies capabilities for the engines operation efficiency enhancing can be performed as well.

Keywords:

gas turbine engines of narrow-body aircraft, combustion chamber workflow, gorenje technologies DOC, TAPS, RQL

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