Combustor and gas turbine including the same

1. A combustor comprising:

an inner liner forming a combustion chamber;

an outer liner surrounding the inner liner to form a cooling passage in which compressed air flows; and

a plurality of cooling guides installed around an inner circumferential surface of the outer liner to surround the combustion chamber, each of the plurality of cooling guides including an air guiding surface and protruding from the inner circumferential surface to create an impinging jet from the compressed aft flowing in the coding passage,

wherein the air guiding surface includes a concave surface that faces the flow of the compressed air to guide the compressed air toward the inner liner, and

wherein each of the plurality of cooling guides includes a downstream side surface having a square cress-section and extending perpendicularly from the inner circumferential surface of the outer liner, a top surface extending from the downstream side surface to the air guiding surface, a front surface extending perpendicularly from the inner circumferential surface of the outer liner to the air guiding surface, and two side surfaces that each has a flat surface and meets the downstream side surface, the top surface, the front surface, the inner circumferential surface of the outer liner and the air guiding surface.

2. The combustor according to claim 1 , wherein the plurality of cooling guides surrounding the combustion chamber are installed at regular intervals in a flow direction of the compressed air.

3. The combustor according to claim 2 , wherein the plurality of cooling guides installed at regular intervals in the flow direction of the compressed air are arranged in staggered axial rows.

4. The combustor according to claim 1 , wherein each coaling guide of the plurality of cooling guides has a length dimension measured from a downstream side of a corresponding cooling guide of the plurality of cooling guides to the front surface of the corresponding cooling guide, and a height dimension measured from the inner circumferential surface of the outer liner to the top surface of the corresponding cooling guide, the length dimension being greater than the height dimension.

5. The combustor according to claim 1 , wherein each cooling guide of the plurality of cooling guides has an upstream side that faces the flow of the compressed air and is disposed opposite to a downstream side, and wherein the top surface is wider than the front surface such that a corresponding cooling guide of the plurality of cooling guides is narrower on the upstream side and wider on the downstream side.

6. The combustor according to claim 1 , wherein the aft guiding surface communicates with the top surface such that the top surface has an axial length measured from the air guiding surface to a right angle junction between the top surface and the downstream side surface and communicates with the front surface such that the front surface has a radial height measured from the air guiding surface to a right angle junction between the front surface and the inner circumferential surface of the outer liner, and wherein the axial length and the radial height are substantially equal.

7. A gas turbine comprising:

a compressor to compress air, a combustor to produce combustion gas by mixing the compressed air with fuel for combustion in a combustion chamber, and a turbine rotated by the combustion gas to generate power, the combustor comprising:

an inner liner forming the combustion chamber;

an outer liner surrounding the inner liner to form a cooling passage in which the compressed air flows; and

a plurality of cooling guides installed around an inner circumferential surface of the outer liner to surround the combustion chamber, each of the plurality of cooling guides including an air guiding surface and protruding from the inner circumferential surface to create an impinging jet from the compressed air flowing in the cooling passage,

wherein the air guiding surface includes a concave surface that faces the flow of the compressed air to guide the compressed air toward the inner liner, and

wherein each of the plurality of cooling guides includes a downstream side surface having a square cross-section and extending perpendicularly from the inner circumferential surface of the outer liner, a top surface extending from the downstream side surface to the air guiding surface, a front surface extending perpendicularly from the inner circumferential surface of the outer liner to the air guiding surface, and two side surfaces that each has a flat surface and meets the downstream side surface, the top surface, the front surface, the inner circumferential surface of the outer liner and the air guiding surface.

8. The gas turbine according to claim 7 , wherein the plurality of cooling guides surrounding the combustion chamber are installed at regular intervals in a flow direction of the compressed air, and wherein the plurality of cooling guides installed at the regular intervals in the flow direction of the compressed air are arranged in staggered axial rows.

9. The gas turbine according to claim 7 , wherein the aft guiding surface communicates with the top surface such that the top surface has an axial length measured from the air guiding surface to a right angle junction between the top surface and the downstream side surface and communicates with the front surface such that the front surface has a radial height measured from the air guiding surface to a right angle junction between the front surface and the inner circumferential surface of the outer liner, and

wherein the axial length and the radial height are substantially equal.