Geared turbofan with over-speed protection
AssigneeRaytheon Technologies Corporation
InventorsMarc J. Muldoon, Michael E. McCune, Andrew J. Murphy
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AssigneeRaytheon Technologies Corporation
InventorsMarc J. Muldoon, Michael E. McCune, Andrew J. Murphy
Estimating the term…
A gas turbine engine includes a fan shaft rotatable about an axis, a fan connected to the fan shaft, and an outer housing surrounding the fan to define a bypass passage. A compressor section has both a low pressure compressor that is fixed to rotate with the fan shaft and a high pressure compressor. A turbine section has a low pressure turbine driving a low speed spool and a high pressure turbine driving the high pressure compressor. The low pressure turbine includes rotating blades and a static structure aft of the rotating blades. A fan drivetrain includes a geared architecture connecting the low speed spool to the fan shaft such that the fan and low pressure compressor rotate at a lower speed than the low pressure turbine. A thrust bearing is axially aft of the geared architecture and axially forward of the high pressure compressor. A tower shaft is rotatably driven by the low speed spool.
A gas turbine engine comprising:
A gas turbine engine comprising:
A gas turbine engine comprising:
Dependencies are inferred from the claim text.