Criteria of using a rotor in an integrated starter-generator

The basis for the development of the aviation industry is the continuous process of changing the designs, Type of operation and operating conditions of the applied electromechanical energy converters. An additional factor is the expansion of the trend for hybrid power plants abroad, which allows increasing the level of electrification of the aircraft and providing another step towards creating a “more electric aircraft”. One of these steps is the integration of electromechanical energy converters in the form of a starter generator into an aircraft engine, which allows providing greater compactness, unification of technologies and increasing the strength of the elements of the integrated converter.

This paper examines approaches to the development and manufacture of rotors and starter-generators for aircraft engines. The authors analyse the design of the rotor, integrated starter-generator and the materials; present calculated load data for the rotor shroud and magnets during operation and review the results of acceleration tests of rotors with permanent magnets.

The aim of the research is to evaluate the feasibility of using a composite bandage for an integrated starter-generator, as well as to analyse the potential damage to the bandage and permanent magnets used in the rotor design. The research demonstrates calculated and experimental data indicating the feasibility of using the composite bandage for rotors with rotational speeds of up to 40.000 rpm. Moreover, the authors develop an algorithm for estimating the safety margin and conduct an experimental testing. The results highlight potential defects in the bandage and magnets, identifying the underlying causes and preventing their recurrence.

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