Part load performance improvement using deformable bore plugs

A gas turbine engine, comprising:

• a compressor for compressing air;
• a combustor for combusting fuel with compressed air;
• a turbine for generating power;
• the compressor further including
• a discharge channel for directing compressed air from the compressor downstream for combustor and cooling;
• a cooling channel to provide cooing for cooling flow to turbine buckets;
• a compressor discharge case forming a boundary between the cooling channel and the discharge channel;
• at least one aperture in the compressor discharge case providing communication between the flow of air through the discharge channel and the first cooling channel;
• and
• a restrictor device positioned in the at least one aperture that regulates the flow of air between the discharge channel and the cooling channel through the at least one aperture in response to a physical condition of the gas turbine engine;
• and
• wherein the restrictor device deforms in response to at least one of a temperature of the air flowing through the discharge channel and a power output of the gas turbine engine, thereby regulating the opening for air flow through the at least one aperture.