Abstract: This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N1 of the low-pressure compressor spools of the gas-turbine engines are determined and a difference value N1 is calculated and subsequently on the basis of this difference value at least one trim value is calculated, on the basis of which, at least on one gas-turbine engine, a change of the setting is made, with subsequently the respective speeds N2 of the high-pressure compressor spools of the gas-turbine engines being determined and a difference value N2 being calculated and subsequently on the basis of this difference value, at least on one gas-turbine engine, the inlet temperature value T20, which is fed to the engine controller, being changed for synchronization.

Abstract: This invention relates to an engine synchronization method for aircraft equipped with at least two gas-turbine engines, where the respective speeds N1 of the low-pressure compressor spools of the gas-turbine engines are determined and a difference value N1 is calculated and subsequently on the basis of this difference value at least one trim value is calculated, on the basis of which, at least on one gas-turbine engine, a change of the setting is made, with subsequently the respective speeds N2 of the high-pressure compressor spools of the gas-turbine engines being determined and a difference value N2 being calculated and subsequently on the basis of this difference value, at least on one gas-turbine engine, the inlet temperature value T20, which is fed to the engine controller, being changed for synchronization.

Abstract: A protective coating is applied to a eutectic or near-eutectic alloy which contains at least one continuously multi-ply connected crystalline phase and at least one other phase which may be continuous or non-continuous, by removing from the surface of said alloy, one or more of the phases, such that at least one continuous phase will remain unaffected, so as to roughen said alloy surface, and thereafter coatng said surface with a protective coating.

Abstract: A protective coating is applied to a eutectic or near-eutectic alloy which contains at least one continuously multi-ply connected crystalline phase and at least one other phase which may be continuous or non-continuous, by removing from the surface of said alloy, one or more of the phases, such that at least one continuous phase will remain unaffected, so as to roughen said alloy surface, and thereafter coating said surface with a protective coating.

Abstract: In a cast anisotropic body comprising an at least partially monovariant ternary eutectic alloy of Co, Cr and C, the eutectic part of the alloy comprising a matrix phase consisting substantially of Co containing at least Cr in a solid solution and a dispersed phase consisting substantially of a carbide of the formula Cr.sub.7.sub.-x.sub.-y Co.sub.x Me.sub.y C.sub.3 wherein x is a number capable of values from 0 to 2 and y is a number capable of values from 0 to 4, and wherein Me is an additional element contained in the matrix and/or dispersed phase, the dispersed phase consisting essentially of a plurality of high strength carbide fibers oriented in substantial alignment, and embedded in the matrix phase, the improvement which comprises the additional element Me being selected from the group consisting of manganese, aluminum, yttrium, boron, one or more rare earths and mixtures thereof, wherein said additional element Me is present in an amount of from 0.