Abstract: A method for synchronizing multiple generators includes positioning a pilot feature of a shaft of a first generator positioned at a first angular position that is substantially aligned with a first predetermined reference point located at a predetermined angular position relative to an axis, locking the shaft of the first generator at the first angular position, aligning a pilot feature of a first shaft of a second generator with a second angular position that is substantially aligned with a second predetermined reference point located at a position relative to the axis that is substantially equal to the predetermined angular position, calculating an angular difference between the two angular positions, and rotating a second shaft splined with the first shaft of the second generator about the axis in another direction, based on the calculated angular difference.

Abstract: An adjustable flange is provided by the present invention for the synchronization of multiple generators driven by a gas turbine engine. The adjustable flange of the present invention may comprise a clocking pin and a plurality of alignment holes which may allow for the precise synchronization of the generators so that they may be driven in a precisely parallel manner. The adjustable flange may be used, for example, in combination with any gas turbine engine having multiple gearbox-mounted generators, such as the engines used in gas turbine-driven land vehicles, or with any other source of rotating-shaft power suitable to drive the gearbox. A method for using the adjustable flange to synchronize multiple generators of an engine is also provided.

Abstract: An adjustable gear arrangement for synchronization of multiple generators in a gas turbine engine is provided. The adjustable gear arrangement comprises a two-piece splined shaft that allows for the precise adjustment of the gears in synchronizing the generators. A method for synchronizing multiple generators using the adjustable gear arrangement of the present invention is also provided.

Abstract: A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.