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A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow sleeve

A combustor has a flow sleeve and a flow liner defining a generally axial flow direction of compressor discharge air toward combustor burners. A casing is secured to the forward end of the flow sleeve defining an annular plenum along the interior of the flow sleeve. Openings through the flow sleeve supply compressor discharge air into the plenum where the air changes direction for flow through apertures into and generally coaxially with the free air stream. The axial injection minimizes or eliminates energy losses due to cross flow injection within the axial air stream while continuing to cool the liner.

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What is claimed is: 1. A combustor for a gas turbine comprising: a combustor housing including a flow liner extending in a generally axial direction and a flow sleeve surrounding and spaced from said flow liner, arranged to define a flow path for flowing air in a generally axial flow direction betw

What is claimed is: 1. A combustor for a gas turbine comprising: a combustor housing including a flow liner extending in a generally axial direction and a flow sleeve surrounding and spaced from said flow liner, arranged to define a flow path for flowing air in a generally axial flow direction between said liner and said flow sleeve to at least one burner at an aft end of the combustor; and an inlet to said flow sleeve for introducing additional air into the flow path in substantially the same axial direction as the direction of air flow along the flow path wherein said inlet is formed by an annular casing member attached to an inner wall of said flow sleeve within a radially outer portion of said flow path, thereby creating an annular plenum within said flow sleeve, said flow sleeve having at least one radially-oriented hole for flowing the additional air into the plenum in a radial direction substantially perpendicular to said axial flow direction, said casing provided with at least one axially-oriented exit aperture in communication with said plenum wherein said plenum and said axially oriented exit aperture are configured to turn the additional air in said annular plenum from said radial direction to said axial flow direction thereby enabling the additional air to be introduced into the flow path substantially in said axial flow direction and thus preventing radial cross flow of the additional air with the air flowing in said flow path. 2. A combustor according to claim 1 wherein said at least one radially-oriented hole comprises a plurality of holes circumferentially-spaced about said flow sleeve, and further wherein said at least one axially-oriented aperture comprises a plurality of apertures facing in a generally downstream direction of the air flow along the flow path. 3. A combustor according to claim 2 wherein said plenum is also defined in part by a portion of said flow sleeve. 4. A combustor according to claim 2 including an impingement sleeve surrounding a transition piece and defining a passage therebetween for flowing air into a forward end of said flow path, said plenum being spaced outwardly of the air flowing into the flow path. 5. A combustor for a gas turbine comprising: a combustor housing including a flow liner and a flow sleeve surrounding and spaced from said flow liner defining a flow path therebetween and arranged for flowing compressor discharge air generally in a first axial upstream direction, opposite a flow of combustion gases from the combustor, between said liner and said flow sleeve to at least one burner at an aft end of the combustor; and an inlet device within said flow sleeve for introducing additional air into the flow path, said inlet device configured to turn the additional air flowing into said inlet device in a radial flow direction to a parallel axial upstream direction and to introduce the additional air to the flow path in said first axial upstream direction to thereby eliminate cross flow between the additional air introduced through the inlet and air flowing along the flow path. 6. A combustor according to claim 5 wherein said inlet device includes an annular plenum within said flow sleeve, said flow sleeve having at least one radially-oriented hole for flowing the additional air into the plenum, said plenum including at least one axially-oriented exit aperture in communication with said plenum for directing the additional air from said plenum into the flow path substantially in said first axial direction. 7. A combustor according to claim 6 wherein said plenum is formed in part by a casing within the flow sleeve, and wherein said at least one radially-oriented hole comprises a plurality of radially-oriented holes circumferentially spaced about said flow sleeve, and further wherein said at least one axially-oriented aperture comprises a plurality of apertures facing in a generally downstream direction of the air flow along the flow path. 8. A combustor according to claim 7 wherein said plenum is bounded in part by a portion of said flow sleeve. 9. A combustor according to claim 7 including an impingement sleeve surrounding a transition piece and defining a passage therebetween for flowing air into a forward end of said flow path, said plenum being spaced radially outwardly of the air flowing into the flow path. 10. In a combustor for a gas turbine having a flow liner, a fuel burner adjacent an aft end of the liner and a flow sleeve surrounding and spaced from the liner defining a flow path for flowing air in a first axial upstream direction, opposite a flow of combustion gases from the combustor, to said burner at said aft end, a method of introducing additional air into the air flowing along the flow path comprising step of introducing the additional air in a radial direction into an inlet device, turning the radially-introduced additional air so as to flow in a second parallel axial upstream direction, and injecting the additional air directly into the flow path to join with the air flowing in said first axial upstream direction toward said fuel burner at said aft end to thereby prevent cross flow between said additional air and air flowing in said flow path. 11. A method according to claim 10 including providing a casing defining a plenum within the flow sleeve, supplying the additional air to the plenum, and directing the additional air from said plenum through apertures facing in the generally downstream and generally parallel to said first axial flow direction. 12. A method according to claim 11 including supplying the additional air to the plenum through the flow sleeve.