Cast slot-cooled single nozzle combustion liner cap

A liner cap assembly for a combustion liner in a turbine comprising:

• an outer tubular sleeve having upstream and downstream ends;
• an inner annular cowl concentric with said sleeve and having a central opening adapted to receive a forward end of a nozzle;
• and
• an annular cone portion extending between said outer sleeve and said inner cowl, said cone extending rearwardly and radially inwardly from said downstream end of said outer sleeve to said inner cowl, said cone portion provided with a plurality of cooling apertures and three directional vanes on a downstream side of said cone portion adapted to divert air passing through said cooling apertures in predetermined directions;
• wherein each of said directional vanes comprises a ring having a first portion extending from said cone portion and a second portion extending parallel to said cone portion;
• and
• wherein said three annular vanes are located at radially spaced locations along said cone portion.

A one-piece, liner cap assembly for a combustion liner in a turbine comprising:

• an outer tubular sleeve having upstream and downstream ends;
• an inner annular cowl concentric with said sleeve and having a central opening adapted to receive a forward end of a nozzle;
• and
• an annular cone portion extending between said outer sleeve and said inner cowl, said cone extending rearwardly and radially inwardly from said downstream end of said outer sleeve to said inner cowl, said cone portion provided with a plurality of cooling apertures and at least one annular directional vanes on a downstream surface of said cone portion adapted to divert air passing through said cooling apertures in predetermined directions, wherein said outer tubular sleeve, said inner cowl and said annular cone portion are of unitary cast construction;
• wherein said at least one directional vane comprises a ring having a first portion extending from said cone portion and a second portion extending parallel to said cone portion;
• and
• wherein at least one of said directional vanes includes a second portion which extends radially inwardly and outwardly of said first portion.

A liner cap assembly for a combustion liner comprising:

• an outer tubular sleeve;
• an inner annular cowl adapted to receive a forward end of a nozzle, said outer sleeve and said inner cowl being in concentric relationship with each other;
• an annular cone portion extending between said outer sleeve and said inner cowl, said cone portion having a plurality of cooling apertures formed therein, and three directional vanes adapted to divert air passing through at least some of the cooling apertures in predetermined directions;
• wherein each of said vanes comprises an annular ring having a first portion extending from the cone portion and a second portion extending parallel to said cone portion;
• and
• wherein said three annular vanes are located at radially spaced locations along the cone portion.

A one-piece, liner cap assembly for a combustion liner comprising:

• an outer tubular sleeve;
• an inner annular cowl adapted to receive a forward end of a nozzle, said outer sleeve and said inner cowl being in concentric relationship with each other;
• an annular cone portion extending between said outer sleeve and said inner cowl, said cone portion having a plurality of cooling apertures formed therein, and at least one annular directional vanes adapted to divert air passing through at least some of the cooling apertures in predetermined directions, wherein said outer tubular sleeve, said inner cowl and said annular cone portion are of unitary cast construction;
• wherein said at lest one directional vane comprises an annular ring having a first portion extending from the cone portion and a second portion extending parallel to said cone portion;
• and
• wherein said second portion extends radially inwardly and outwardly of said first portion.