Gas turbine engine with bleed diffuser baffles

An aircraft air supply system comprising:

• a gas turbine engine including a compressor section having a downstream most location and more upstream locations and a compressor housing surrounding compressor rotors, a combustor downstream of said compressor section and a turbine section downstream of said combustor;
• at least one bleed inlet passage for bleeding air compressed in the compressor section, and delivering the air for use on an associated aircraft;
• a baffle plate intermediate the at least one bleed inlet passage and at least one bleed exit port from the gas turbine engine, the baffle plate having a plurality of holes for allowing the air to flow from the at least one bleed inlet passage to the at least one bleed exit port, with an area of the plurality of holes increasing from a location adjacent the at least one bleed exit port and in a circumferential direction away from the at least one bleed exit port;
• and
• said at least one bleed exit port to be connected to the use on the associated aircraft.

An aircraft comprising:

• an aircraft body including a gas turbine engine including a compressor section having a downstream most location and more upstream locations and a compressor housing surrounding compressor section rotors, a combustor downstream of said compressor and a turbine section downstream of said combustor;
• at least one bleed inlet passage for bleeding air compressed in the compressor section, and delivering the air for use on an associated aircraft;
• a baffle plate intermediate the at least one bleed inlet passage and at least one bleed exit port from the gas turbine engine, the baffle plate having a plurality of holes for allowing the air to flow from the at least one bleed inlet passage to the at least one bleed exit port, with an area of the plurality of holes increasing from a location adjacent the at least one bleed exit port and in a circumferential direction away from the at least one bleed exit port;
• said at least one bleed exit port to be connected to the use;
• and
• wherein there are at least two bleed inlet passages, associated baffle plates and bleed exit ports with one of said at least two bleed inlet passages associated with a higher pressure location and one of the at least two bleed inlet passages associated with a lower pressure location in the compressor section, each of said at least two bleed exit ports to be connected to the use through a valve having an electric control to select between the at least two bleed exit ports to connect to the use, and the use is a cabin air supply system for the associated aircraft.