Patent ID: 9163717
Filing Date: 2015-10-20
Classification: F01D,F02C,F02K,F16H,Y10T

Abstract:
1. A gas turbine engine comprising: a first shaft that interconnects a fan, a low pressure compressor, and a low pressure turbine; a second shaft that interconnects a high pressure compressor and a high pressure turbine, the second shaft configured to rotate at a faster speed than the first shaft; a geared architecture that interconnects the first shaft to drive the fan, the geared architecture comprising a gear assembly enclosed within a gear housing; a manifold assembly comprising a mounting plate having a mount interface attached to the gear housing and a flow plate attached to the mounting plate to provide a plurality of flow passages between the mounting plate and flow plate, the manifold assembly including at least one fluid inlet configured to receive fluid from a supply and at least one fluid outlet to direct the fluid into the gear housing; wherein the flow plate comprises a ring-shaped structure with a center opening defining a center axis and a first ring portion defined by a first inner peripheral surface extending circumferentially about the axis and a first outer peripheral surface spaced radially outwardly relative to the first inner peripheral surface; wherein the mounting plate comprises a ring-shaped structure with a center opening concentric with the center axis and a second ring portion defined by a second inner peripheral surface extending circumferentially about the axis and a second outer peripheral surface spaced radially outwardly relative to the second inner peripheral surface; and wherein the plurality of flow passages comprises at least a first flow passage formed adjacent to the first and second inner peripheral surfaces and a second flow passage formed adjacent to the first and second outer peripheral surfaces, the first and second flow passages extending circumferentially around the first and second ring portions to at least partially surround the central axis.