Gas turbine combustor and gas turbine

A gas turbine combustor comprising:

• a can combustor liner that includes an inner wall surface defining a combustion region through which combustion gas generated by combustion of a fuel is allowed to flow, an ejection port for the combustion gas being formed at an ejection part that is a downstream side end portion of the can combustor liner in a flow direction of the combustion gas;
• and
• a plurality of narrowing parts that are provided on the inner wall surface of the can combustor liner at intervals in a circumferential direction and that protrude radially inward, wherein a center line of the can combustor liner includes an upstream center line extending linearly through the center of an upstream region of the can combustor liner in the flow direction, and a downstream center line which extends through the center of the ejection part in a direction different from an extension direction of the upstream center line,
• in a first cross section that includes the entire center line of the can combustion liner, the can combustor liner is divided into a first region and a second region by the center line of the can combustion liner,
• in a second cross section which intersects the center line of the can combustor liner and is orthogonal to the first cross section, the can combustor liner is divided into the first region and the second region by a straight line which intersects and is orthogonal to the center line of the can combustor liner,
• a distance traced along the inner wall surface in the virtual flat plane from a position corresponding to a reference position on the upstream center line to the ejection port is shorter in the second region than in the first region,
• a total value of projected areas of the narrowing parts present in the second region when viewed from an extension direction of the center line is larger than a total value of projected areas of the narrowing parts present in the first region when viewed from the extension direction of the center line, and
• a height of at least one of the narrowing parts present in the second region in a radial direction of the can combustor liner is greater than a height of each of the narrowing parts present in the first region in the radial direction.

A gas turbine combustor comprising:

• a can combustor liner that includes an inner wall surface defining a combustion region through which combustion gas generated by combustion of a fuel is allowed to flow, an ejection port for the combustion gas being formed at an ejection part that is a downstream end portion of the can combustor liner in a flow direction of the combustion gas;
• and
• a plurality of narrowing parts that are provided on the inner wall surface of the can combustor liner at intervals in a circumferential direction and that protrude radially inward, wherein a center line of the can combustor liner includes an upstream center line extending linearly through the center of an upstream region of the can combustor liner in the flow direction, and a downstream center line which extends through the center of the ejection part in a direction different from an extension direction of the upstream center line,
• in a first cross section that includes the entire center line of the can combustion liner, the can combustor liner is divided into a first region and a second region by the center line of the can combustion liner,
• in a second cross section which intersects the center line of the can combustor liner and is orthogonal to the first cross section, the can combustor liner is divided into the first region and the second region by a straight line which intersects and is orthogonal to the center line of the can combustor liner,
• in the first cross section, a straight line obtained by extending the upstream center axis line passes through the first region in the ejection part,
• a total value of projected areas of the narrowing parts present in the second region when viewed from an extension direction of the center line is larger than a total value of projected areas of the narrowing parts present in the first region when viewed from the extension direction of the center line,
• a surface of each of the narrowing parts, on an upstream side in the flow direction, is an inclined surface that is inclined to approach the center line while moving toward the downstream side of the can combustor liner, and
• an angle at which the inclined surface for at least one of the narrowing parts present in the second region is inclined with respect to the inner wall surface is larger than an angle at which the inclined surface for each of the narrowing parts present in the first region is inclined with respect to the inner wall surface.

A gas turbine combustor comprising:

• a can combustor liner that includes an inner wall surface defining a combustion region through which combustion gas generated by combustion of a fuel is allowed to flow, an ejection port for the combustion gas being formed at an ejection part that is a downstream end portion of the can combustor liner in a flow direction of the combustion gas;
• and
• a plurality of narrowing parts that are provided on the inner wall surface of the can combustor liner at intervals in a circumferential direction and that protrude radially inward,
• wherein a center line of the can combustor liner includes an upstream center line extending linearly through the center of an upstream region of the can combustor liner in the flow direction, and a downstream center line which extends through the center of the ejection part in a direction different from an extension direction of the upstream center line,
• in a first cross section that includes the entire center line of the can combustion liner, the can combustor liner is divided into a first region and a second region by the center line of the can combustion liner,
• in a second cross section which intersects the center line of the can combustor liner and is orthogonal to the first cross section, the can combustor liner is divided into the first region and the second region by a straight line which intersects and is orthogonal to the center line of the can combustor liner,
• in the first cross section, a straight line obtained by extending the upstream center line passes through the first region in the ejection part,
• a total value of projected areas of the narrowing parts present in the second region when viewed from an extension direction of the center line is larger than a total value of projected areas of the narrowing parts present in the first region when viewed from the extension direction of the center line, and
• the narrowing parts present in the second region are provided at a first position along the center line and at a second position in which a position along the center line is different from the first position.