Gas turbine engine systems involving cooling of combustion section liners
Gas turbine engine systems involving cooling of combustion section liners are provided. A representative liner includes: an outer side, an inner side, an upstream end, and a downstream end, the outer side being configured to face away from a combustion reaction, the inner side being configured to face the combustion reaction; a cooling air channel, a portion of the cooling air channel being located proximate the downstream end; and cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed through the cooling holes and to the inner side of the liner such that at least a portion of the inner side of the liner receives cooling air despite a corresponding portion located on the outer side of the liner being obstructed from receiving cooling air.
1. A gas turbine engine comprising:
a compressor;
a turbine operative to rotate the compressor; and
a combustion section operative to provide thermal energy for rotating the turbine;
the combustion section comprising:
a transition piece having an open, upstream end;
a liner having an outer side, an inner side, an upstream end and a downstream end, the outer side being configured to face away from a combustion reaction of the combustion section, the inner side being configured to face the combustion reaction, and the downstream end being received within the open, upstream end of the transition piece such that gas associated with the combustion reaction is directed from the liner, through the transition piece and to the turbine; and
a cooling air channel located at the outer side of the liner, the cooling air channel being operative to direct cooling air from the outer side of the liner to the inner side of the liner to cool a portion of the downstream end of the liner obstructed by the transition piece;
a barrier wall attached to the outer side of the liner; and
a cooling slot formed in the outer side of the liner and in fluid communication with the cooling air channel, the cooling slot extending between at least a portion of the barrier wall and the inner side of the liner.
2. The gas turbine engine of claim 1 , wherein the barrier wall has an aperture formed therein such that cooling air directed toward the barrier wall is provided to the cooling air channel via the aperture of the barrier wall.
3. A combustion section of a gas turbine engine comprising:
a transition piece having an upstream end;
a liner having an outer side, an inner side and a downstream end, the outer side being configured to face away from a combustion reaction of the combustion section, the inner side being configured to face the combustion reaction, and the downstream end being sized and shaped to be received within the upstream end of the transition piece;
a cooling air channel, at least a portion of the cooling air channel being located in a vicinity of the downstream end of the liner such that, when the downstream end is inserted into the transition piece, a first portion of the cooling air channel is located within the transition piece and a second portion of the cooling air channel is located outside the transition piece; and
cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed into the transition piece, through the cooling holes and to the inner side of the liner such that at least a portion of the liner obstructed by the transition piece receives cooling air;
a barrier wall contacting the outer side of the liner, at least a portion of the barrier wall being located in a vicinity of the downstream end of the liner such that, when the downstream end is inserted into the transition piece, a first portion of the barrier wall is located within the transition piece and a second portion of the barrier wall is located outside the transition piece; and
a cooling slot formed in the outer side of the liner and in fluid communication with the cooling air channel, the cooling slot extending between at least a portion of the barrier wall and the outer side of the liner.
4. The combustion section of claim 3 , wherein the barrier wall has an aperture formed therein such that cooling air directed toward the barrier wall is provided to the cooling air channel via the aperture of the barrier wall.
5. A combustion liner for a combustion section of a gas turbine engine, the liner comprising:
an outer side, an inner side, an upstream end and a downstream end for being received within a transition piece, the outer side being configured to face away from a combustion reaction, the inner side being configured to face the combustion reaction;
a cooling air channel formed in the outer side between the liner and a barrier wall, at least a portion of the cooling air channel being located in a vicinity of the downstream end;
cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed through the cooling holes and to the inner side of the liner such that at least a portion of the inner side of the liner receives cooling air despite a corresponding portion located on the outer side of the liner being obstructed from directly receiving cooling air; and
a cooling slot formed in the outer side of the liner, the cooling slot being in fluid communication with the cooling air channel.