Abstract:
A turbine engine system includes a gutter and a gear train with an axial centerline. The gutter is disposed radially outside of the axial centerline. The gutter at least partially circumscribes the gear train, and includes an inner surface and a channel. The channel receives fluid directed out of the gear train. The channel extends radially into the gutter from the inner surface to a channel end, and circumferentially to a channel outlet. At least a portion of the channel has a cross-sectional channel geometry that tapers axially as the channel extends radially towards the channel end.
Abstract:
A gear reduction for a gas turbine engine comprises a carrier driven to rotate gears. The gears are supported by journal bearings. The carrier extends through a transfer bearing, which provides oil to passages within the carrier to supply oil to the gears and to the journal bearings. A device limits leakage oil from the transfer bearing to axial ends of the transfer bearing to a controlled amount. A gas turbine engine is also disclosed.
Abstract:
A journal support pin to support intermediate gears for use in gas turbine engine comprises a titanium body, and an outer surface outside of the titanium body having a surface hardness that is harder than the body. A gas turbine engine and a method of forming a journal support pin to support intermediate gears for use in gas turbine engine are also disclosed.
Abstract:
A debris monitor sensor system according to one disclosed non-limiting embodiment of the present disclosure includes a first passage disposed substantially linearly along a flow path, the first passage includes a sensor passage section. A second passage splits from the first passage and is offset from the flow path. An oil debris monitor is in communication with the sensor passage section.
Abstract:
A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
Abstract:
A high-bypass ratio geared turbomachine comprises a compressor section (24) of a high-bypass ratio geared turbomachine. The compressor section (24) provides at least a low-pressure compressor (44) and a high-pressure compressor (52), wherein a rotor of the low-pressure compressor (44) rotates together with a rotor of a fan (42).
Abstract:
An exemplary system for delivering a turbomachine fluid to a supplied area is a pump configured to draw fluid from both a first container and a second container when operating in both a positive g-force environment and a negative g-force environment. The fluid from the first container in a positive g-force environment is a mixture of air and oil, and the fluid from the first container in a negative g-force environment is primarily oil.