Internal manifold air extraction system for IGCC combustor and method

A turbine engine comprising:

• combustion section;
• an air discharge section downstream of the combustion section;
• a transition region between the combustion and air discharge sections;
• a combustor liner defining a portion of the combustion section and transition region;
• a first flow sleeve encircling said combustor liner to define a first flow annulus therebetween, said first flow sleeve having at least one cooling aperture formed about a circumference thereof for directing compressor discharge air as cooling air into said first flow annulus;
• a casing surrounding first flow sleeve with a second flow annulus therebetween, said first flow sleeve having at least one air extraction opening formed about a circumference thereof for directing at least some of said compressor discharge air that has been directed into said first flow annulus as cooling air, from said first flow annulus directly into said second flow annulus as extraction air;
• and
• an extraction port operatively coupled to said casing for extracting said extraction air from said second flow annulus.

A method of extracting air from a combustion section comprising a combustor liner, a first flow sleeve encircling said combustor liner to define a first flow annulus therebetween, and a casing surrounding said first flow sleeve, said first flow sleeve having at least one cooling aperture formed about a circumference thereof for directing compressor discharge air as cooling air into said first flow annulus, the method comprising:

• forming a second flow annulus between said casing and said first flow sleeve;
• forming at least one air extraction opening about a circumference thereof for directing at least some of said compressor discharge air that has been directed into said first flow annulus as cooling air from said first flow annulus directly into said second flow annulus as extraction air;
• operatively coupling an extraction port to said casing for extracting said extraction air from said second flow annulus;
• supplying compressor discharge air through said at least one cooling aperture into said first flow annulus as cooling air;
• flowing at least some of said cooling air directly from said first flow annulus through said at least one air extraction opening into said second flow annulus;
• and
• extracting air from said second flow annulus through said extraction port.

A combustor for a turbine comprising:

• a combustor liner;
• a first flow sleeve surrounding said combustor liner with a first flow annulus therebetween, said first flow sleeve having at least one cooling aperture formed about a circumference thereof for directing compressor discharge air as cooling air into said first flow annulus;
• a casing surrounding said first flow sleeve with a second flow annulus therebetween, said first flow sleeve having at least one air extraction opening formed about a circumference thereof for directing compressor discharge air from said first flow annulus as extraction air into said second flow annulus;
• and
• an extraction port operatively coupled to said casing for extracting said extraction air from said second flow annulus,
• wherein said first flow sleeve includes a circumferential groove to define said second flow annulus with said casing.