Combustor for gas turbine

Abstract

Provided is a backflow combustor for a gas turbine provided with a rotary shaft having an axis extending in the axial direction, said backflow combustor comprising: an outer liner and an inner liner that both extend about the axis and that both have a ring shape; an end liner that is disposed on one side of both the liners in the axial direction, that connects the outer liner to the inner liner, and that has a ring shape; a combustion chamber that is defined by these liners; and an evaporation tube that is connected to the outer liner, that is disposed in the combustion chamber, and that evaporates fuel in an internal flow path communicating with an opening of the outer liner into which a fuel injector is inserted. A tip end part of the evaporation tube positioned on the opposite side from the opening side of the outer liner in the internal flow path is connected to a specific liner.

Claims

1. A backflow combustor for a gas turbine having a rotating shaft having an axis extending in the axial direction, comprising: an outer liner having an annular shape extending around the axis and including an opening into which a fuel injector is inserted; an inner liner having an annular shape extending around the axis and facing the outer liner from the radially inward side of the axis; an end liner having an annular shape, positioned on one side in the axial direction with respect to the outer liner and the inner liner, connecting the outer liner to the inner liner; a combustion chamber defined by the outer liner, the inner liner and the end liner; and an evaporator tube connected to the outer liner and positioned in the combustion chamber, including an internal passage communicating with the opening of the outer liner, and evaporating fuel in the internal passage, wherein the tip of the evaporator tube, located on the side of the internal passage opposite to the opening of the outer liner, is connected to a specific liner which is at least one of the outer liner, the inner liner and the end liner.

2. The combustion device according to claim 1, wherein the specific liner includes the inner liner.

3. The combustor according to claim 1, wherein the evaporator tube includes an expanded tube portion in which the flow path cross-sectional area of ​​the outer liner expands from the opening to the tip.

4. The combustor according to any one of claims 1 to 3, wherein the tip of the evaporator tube includes an open end having an opening periphery that widens towards the end liner in the circumferential direction of the inner liner.

5. The combustor according to any one of claims 1 to 3, wherein the tip of the evaporator tube includes an open end whose opening edge is inclined such that it slopes downward towards the inner liner as it approaches the end liner.

6. The combustor according to any one of claims 1 to 3, wherein at least the outer liner, the inner liner, the end liner, and the evaporator tube are integrally continuous with respect to each other.

7. A backflow combustor for a gas turbine having a rotating shaft having an axis extending in the axial direction, comprising: an outer liner having an annular shape extending around the axis and including an opening into which a fuel injector is inserted; an inner liner having an annular shape extending around the axis and facing the outer liner from the radially inward side of the axis; an end liner having an annular shape, positioned on one side in the axial direction with respect to the outer liner and the inner liner, connecting the outer liner to the inner liner; a combustion chamber defined by the outer liner, the inner liner and the end liner; and an evaporator tube connected to the outer liner and positioned in the combustion chamber, including an internal flow path communicating with the opening of the outer liner, and evaporating fuel in the internal flow path, wherein the evaporator tube includes an expanding tube section in which the flow path cross-sectional area expands from the opening of the outer liner toward the tip of the evaporator tube located opposite the opening side of the internal flow path to the side of the outer liner where the opening is located.

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