Combustor for a gas turbine with cooling structure

A gas turbine, comprising:

• a compressor for producing compressed air;
• a combustion structure including an inner member and an outer member in flow communication with the compressor, the combustion structure including a plurality of combustors for producing a hot gas disposed in a combustion chamber and in flow communication with the combustion chamber;
• a turbine section in flow communication with the combustors and forming a flow path for the hot gas;
• means for cooling the combustion structure including a plurality of axial cooling passages for circulating a portion of the compressed air from the compressor through the combustor structure between the inner member and the outer member in a substantially parallel, linear flow path.

A gas turbine comprising:

• a compressor section for producing compressed air;
• a combustion section in which the compressed air is heated, the combustion section including a combustor comprising:
• an inner member including a plurality of axial slots formed on the outer surface thereof;
• an outer member operatively positioned over the inner member, the combined outer and inner members having a plurality of axial cooling passages operatively positioned between the inner and the outer members;
• means, operatively connected to the compressor section and the combustion section for providing at least some compressed air from the compressor section to the cooling passages along the plurality of axial cooling passages in a substantially parallel, linear flow path, such that the inner surface of the inner member is cooled;
• and
• turbine means, operatively connected to the combustor section, for converting the hot gas from the combustor member into power.

A gas turbine comprising:

• a rotary compressor;
• a rotary turbine mounted for rotation about an axis and coupled to the compressor to drive the same;
• a nozzle adjacent the turbine for directing hot gases thereat to rotate the same;
• a combustor operatively connected to the turbine, the combustor having an inner and an outer member;
• and
• a plurality of axial cooling passages, operatively formed between the inner and outer member, for cooling the inner wall of the inner member, the plurality of axial cooling passages providing the cooling compressed air in a substantially parallel flow path in the plurality of grooves formed on the outer surface of the inner member.

A hot gas control structure for a turbine comprising:

• an inner member having a plurality of grooves formed on an outer surface thereof;
• an outer member operatively positioned over the inner member;
• and
• a plurality of axial cooling passages operatively positioned between the outer member and an inner member, for providing cooling compressed air in a substantially uneven flow path to cool the inner surface of the inner member.

A hot gas control structure for a turbine comprising:

• an inner member having a plurality of grooves formed on an outer surface thereof;
• an outer member operatively positioned over the inner member;
• and
• a plurality of axial cooling passages operatively positioned between the outer member an inner member, for providing cooling compressed air in a substantially linear flow path to cool the inner surface of the inner member.