COMPRESSOR BLEED COOLING SYSTEM FOR MID-FRAME TORQUE DISCS DOWNSTREAM FROM A COMPRESSOR ASSEMBLY IN A GAS TURBINE ENGINE

A cooling system (10) configured to cool aspects of the turbine engine (12) between a compressor (14) and a turbine assembly (16) is disclosed. In at least one embodiment, the cooling system (10) mayinclude one or more mid-frame cooling channels (18) extending from an inlet (20) through one or more mid-frame torque discs (22) positioned downstream of the compressor (14) and upstream of the turbine assembly (16). The inlet (20) may be positioned to receive compressor bleed air. The mid-frame cooling channel (18) may be positioned in a radially outer portion of the mid-frame torque disc (22) toprovide cooling to outer aspects of the mid-frame torque disc (22) such that conventional, low cost materials may be used to form the mid-frame torque disc (22) rather than high cost materials with capacity to withstand higher temperatures. The cooling fluid routed through the mid-frame cooling channel (18) in the mid-frame torque disc (22) may be exhausted into a cooling system (10) for the downstream turbine assembly (1