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A combustor of a turbine engine includes a portion where the aft end of a combustor liner is sealed to a forward end of a transition piece. A cover sleeve surrounds the aft end portion of the combustor liner to form an annular airflow passage between the exterior of the combustor liner and the inner

A combustor of a turbine engine includes a portion where the aft end of a combustor liner is sealed to a forward end of a transition piece. A cover sleeve surrounds the aft end portion of the combustor liner to form an annular airflow passage between the exterior of the combustor liner and the inner side of the cover sleeve. A plurality of turbulators project radially outward from the combustor liner. One or more circumferential rows of supports also extend radially outward from the combustor liner to support the cover sleeve.

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1. 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 a first plurality of cooling apertures formed about a circumference thereof for directing compressor discharge air as

1. 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 a first plurality of cooling apertures formed about a circumference thereof for directing compressor discharge air as cooling air into said first flow annulus;a transition piece body connected to said combustor liner, said transition piece body being adapted to carry hot combustion gases to the turbine;a second flow sleeve surrounding said transition piece body, said second flow sleeve having a second plurality of cooling apertures for directing compressor discharge air as cooling air into a second flow annulus between the second flow sleeve and the transition piece body, said first flow annulus connecting to said second flow annulus;an arch shaped resilient seal structure disposed radially between an aft end portion of said combustor liner and a forward end portion of said transition piece body, wherein a center portion of the arch shaped resilient seal structure faces the combustor liner, and ends of the arch shaped resilient seal structure bear against an inner surface of the transition piece body; anda cover sleeve disposed between said aft end portion of said combustor liner and said resilient seal structure, an air flow passage being defined between said cover sleeve and said aft end portion of said combustor liner, said cover sleeve having at a forward end thereof a plurality of air inlet apertures for directing cooling air from said first or second flow annulus into said air flow passage, a radially outer surface of said combustor liner aft end portion defining said air flow passage including a plurality of turbulators projecting towards but spaced from said cover sleeve and a plurality of circumferentially extending rows of supports extending to and engaging said cover sleeve to space said cover sleeve from said turbulators to define said air flow passage, wherein said plurality of circumferentially extending rows of supports are disposed at a position substantially aligned with the center portion of the arch shaped resilient seal structure. 2. The combustor of claim 1, wherein an aperture is provided between each adjacent pair of the supports such that cooling air flowing along the air flow passage can pass through the apertures to flow past a circumferentially extending row of the supports. 3. The combustor of claim 1, wherein the turbulators comprise raised portions of the combustor liner that extend around the circumference of the combustor liner. 4. The combustor of claim 1, wherein the turbulators comprise raised circumferential rings of material that extend from the combustor liner toward the cover sleeve. 5. The combustor of claim 1, wherein said resilient seal structure is a Hula seal. 6. The combustor of claim 1, wherein said first plurality of cooling apertures are configured with an effective area to distribute about 40-60% of the compressor discharge air to said first flow annulus. 7. A turbine engine comprising the combustor of claim 1. 8. A method of cooling a transition region of a turbine engine located between a combustion section having a combustor liner and a transition piece body, said transition region including an arch shaped resilient seal structure disposed radially between an aft end portion of said combustor liner and a forward end portion of said transition piece body, the center of the arch shaped resilient seal structure facing the combustor liner, the method comprising: configuring said aft end portion of said combustor liner so that a radially outer surface thereof includes a plurality of radially outwardly projecting turbulators and a plurality of circumferentially extending rows of radially outwardly projecting supports having a radial height greater than that of said turbulators, wherein said plurality of circumferentially extending rows of supports is aligned with the center of the arch shaped resilient seal structure;disposing a cover sleeve between said aft end portion of said combustor liner and said arch shaped resilient seal structure to define an air flow passage between said cover sleeve and said aft end portion of said combustor liner, said cover sleeve having at a forward end thereof a plurality of air inlet apertures for directing cooling air into said cooling air passage, said turbulators projecting towards but being spaced from said cover sleeve and said supports extending to and spacing said cover sleeve from said turbulators to define said air flow passage; andsupplying compressor discharge air to and through said air inlet apertures and through said air flow passage to reduce a temperature in a vicinity of said resilient seal. 9. A method as in claim 8, wherein the center portion of the arch shaped resilient seal structure bears against the cover sleeve, and wherein ends of the arch shaped resilient seal structure bear against the transition piece body. 10. A method as in claim 8, wherein said resilient seal structure is a Hula seal. 11. The method as in claim 8, wherein the plurality of radially outwardly projecting turbulators are arranged in circumferential rings on the combustor liner. 12. The combustor of claim 1, wherein the plurality of circumferentially extending rows of supports comprise raised portions of the combustor liner that extend around the circumference of the combustor liner. 13. The combustor of claim 1, wherein each of the circumferentially extending row of supports comprises raised portions of the material forming the combustor liner, the raised portions extending radially outward toward the cover sleeve, wherein an aperture is provided between each adjacent pair of raised portions, and wherein the raised portions form a circumferential ring around the exterior of the combustor liner. 14. The method as in claim 8, wherein the configuring step comprises configuring the aft end portion of said combustor liner so that the plurality of circumferentially extending rows of supports comprise raised portions of the combustor liner that extend around the circumference of the combustor liner. 15. The method as in claim 8, wherein the configuring step comprises configuring the aft end portion of said combustor liner so that each of the plurality of circumferentially extending rows of supports comprises raised portions of the material forming the combustor liner, the raised portions extending radially outward toward the cover sleeve, wherein an aperture is provided between each adjacent pair of raised portions, and wherein the raised portions form a circumferential ring around the exterior of the combustor liner.