Abstract:
An exemplary method of lubricating a turbomachine interface includes, among other things, securing a carrier relative to a torque frame using a flexure pin, and lubricating an interface of the flexure pin using a lubricant that has moved through a lubricant passage in the carrier and a lubricant passage in the flexure pin.
Abstract:
A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between about 430 and 645.
Abstract:
A turbofan engine (20) has a fan shaft (120) coupling a fan drive gear system (60) to the fan (28). A low spool comprises a low pressure turbine (50) and a low shaft (56) coupling the low pressure turbine to the fan drive gear system. A core spool comprises a high pressure turbine (46), a compressor (44), and a core shaft (52) coupling the high pressure turbine to the core spool compressor. A first bearing (150) engages the fan shaft, the first bearing being a thrust bearing. A second bearing (160) engages the fan shaft on an opposite side of the fan drive gear system from the first bearing, the second bearing being a roller bearing. A third bearing (180) engages the low spool shaft and the fan shaft.
Abstract:
A scavenge filter system according to an exemplary aspect of the present disclosure includes, among other things, a first scavenge pump stage positioned in a first flow path downstream of a first bearing compartment of a spool and a second scavenge pump stage positioned in a second flow path downstream of a second bearing compartment. The second bearing compartment houses a geared architecture mechanically coupled to the spool. A first scavenge filter fluidly couples the first scavenge pump stage to at least one oil reservoir. A second scavenge filter fluidly couples the second scavenge pump stage to the at least one oil reservoir. The first and second scavenge filters are separate and distinct. A method of filtering debris is also disclosed.
Abstract:
A gas turbine engine has a fan section including a fan rotatable about an axis. A speed reduction device is connected to the fan. The speed reduction device includes a planetary fan drive gear system with a planet gear ratio of at least 2.6. A bypass ratio is greater than about 11.0. A method of improving performance of a gas turbine engine, a fan drive gear module for a gas turbine engine, and a method of designing a gas turbine engine are also disclosed.
Abstract:
A disclosed fan drive gear system includes a sun gear rotatable about an axis of rotation, a plurality of intermediate gears rotatable about an intermediate gear rotation axis in meshing engagement with the sun gear and a ring gear circumscribing the intermediate gears. A bearing assembly supports at least one of the plurality of intermediate gears and includes a first beam extending in a first direction and a second beam extending from an end of the first beam in a second direction. The bearing surface supported on the second beam such that first and second beams are configured to maintain the bearing surface substantially parallel to the intermediate gear rotation axis during operation.
Abstract:
A geared architecture for a gas turbine engine includes a central gear supported for rotation about the axis, a plurality of intermediate gears engaged with the central gear and a ring gear circumscribing the intermediate gears. A first flexible coupling is provided between an input shaft driven by a turbine section and the sun gear. The geared architecture provides a power density comprising a power measured in horsepower (HP) related to a weight of the geared architecture within a defined range that benefits overall engine weight and efficiency.
Abstract:
A gas turbine engine includes a fan section including a fan rotatable about an axis of rotation of the gas turbine engine. A speed reduction device is in communication with the fan. The speed reduction device includes a star drive gear system with a star gear ratio of at least 1.5. A fan blade tip speed of the fan is less than 1400 fps. A bypass ratio is between about 11.0 and about 22.0.
Abstract:
A fan gear drive system includes a fan shaft, a turbine shaft, a fixed structure, and a gear train which includes a torque frame that comprises a base with integrated gear shafts that are circumferentially spaced relative to one another. Each shaft provides a shaft axis. Intermediate gears are supported on each bearing assembly for rotation about the bearing axis. A central gear is located radially inward from and intermeshes with the intermediate gears. A ring gear is arranged about and intermeshes with the intermediate gears. One of the torque frame, central gear and ring gear is connected to the fan shaft. Another of the torque frame, central gear and ring gear is connected to the turbine shaft. The remaining of the torque frame, central gear and ring gear is connected to the fixed structure. A bearing assembly is mounted on each of the gear shafts and provides a bearing axis. Each bearing assembly supports the respective intermediate gear.
Abstract:
A three-spool turbofan engine (20) has a variable fan nozzle (35). The fan blades have a peak tip radius RT and an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.