Angled vanes in combustor flow sleeve

A turbine combustor liner assembly comprising:

• a combustor liner having upstream and downstream ends;
• a transition duct attached to the downstream end of the liner;
• a first flow sleeve surrounding said combustor liner with a first radial flow passage therebetween;
• a first annular inlet to said first radial flow passage at an aft end of said flow sleeve, provided with a plurality of circumferentially spaced, angled flow vanes arranged to swirl air entering said first radial flow passage via said first annular inlet;
• an impingement sleeve surrounding said transition duct establishing a second annular flow passage radially between said transition duct and said impingement sleeve and communicating with said first annular flow passage;
• a second annular inlet to said first annular flow passage upstream of said first annular inlet relative to said direction of flow;
• said second annular inlet provided with a second plurality of flow vanes arranged circumferentially about said combustor liner to swirl air entering said first annular flow passage through said second annular inlet, said second plurality of flow vanes extending radially between said combustor liner and said impingement sleeve.

A turbine combustor liner assembly comprising:

• a combustor liner having upstream and downstream ends;
• a transition duct attached to the downstream end of the liner;
• a first flow sleeve surrounding said combustor liner with a first radial flow passage therebetween;
• a first annular inlet to said first radial flow passage at an aft end of said flow sleeve, provided with a plurality of circumferentially spaced, angled flow vanes arranged to swirl air entering said first radial flow passage via said first annular inlet;
• an impingement sleeve surrounding said transition duct establishing a second annular flow passage radially between said transition duct and said impingement sleeve and communicating with said first annular flow passage;
• a second annular inlet to said first annular flow passage upstream of said first annular inlet relative to said direction of flow;
• said second annular inlet provided with a second plurality of flow vanes arranged circumferentially about said first annular flow passage to swirl air entering said first annular flow passage through said second annular inlet;
• wherein said first plurality of flow vanes extend radially between and are engaged with said flow sleeve and an annular coupling attaching said flow sleeve to an impingement sleeve surrounding said transition duct;
• wherein said second plurality of flow vanes extend radially between said combustor liner and said impingement sleeve;
• and
• wherein each of said first and second pluralities of flow vanes comprises a leading end portion and a trailing end portion, said leading end portion located upstream of said trailing end portion relative to a direction of flow into said first annular flow passage.