Abstract: A gas turbine engine comprises an engine core, a tie bolt, and a fail-safe system. The engine core includes a compressor, a turbine, and a shaft that couples the compressor with the turbine for rotation with the turbine about an axis. The tie bolt locates axially the compressor relative to the turbine. The fail-safe system is configured to transmit torque from the turbine to the compressor through the tie bolt in response to a shaft disconnect event.

Abstract: An example article includes a body. The body defines at least one damping pocket, at least one body opening defined in an outer surface of the body, and an at least one escape channel. The at least one damping pocket is fluidically coupled to the at least one body opening by the at least one escape channel. The article includes a predetermined volume of damping material enclosed in the at least one damping pocket. An example technique includes additively manufacturing the article including the body. An example system includes an additive manufacturing tool, and a computing device configured to control the additive manufacturing tool to additively manufacture the article including the body.

Abstract: A gas turbine engine comprises an engine core, a tie bolt, and a fail-safe system. The engine core includes a compressor, a turbine, and a shaft that couples the compressor with the turbine for rotation with the turbine about an axis. The tie bolt locates axially the compressor relative to the turbine. The fail-safe system is configured to transmit torque from the turbine to the compressor through the tie bolt in response to a shaft disconnect event.

Abstract: An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.

Abstract: An improved system, apparatus and method for intercooling a turbo fan engine, and more specifically, a system for intercooling a turbo fan engine employing a secondary bypass duct that minimizes pressure losses. The secondary bypass duct is radially inwardly disposed from a fan bypass duct and receives fan bypass air through an inlet. The portion of fan bypass air flows through one or more microchannel or minichannel heat exchangers. The secondary bypass duct has an outlet in communication with the bypass air stream downstream of the throat of a fan bypass nozzle. The secondary bypass air is accelerated at the exit to create thrust.