Communicating structure between adjacent combustors and turbine portion and gas turbine

1. A communicating structure between a plurality of combustors and a turbine portion,

wherein the plurality of combustors generate combustion gas by combusting compressed air supplied from a compressor and fuel supplied from fuel nozzles, which are mixed inside a plurality of pipe pieces each of which are provided for each of the combustors and which are disposed next to each other around a rotating shaft,

a turbine portion generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of a plurality of turbine stator vanes including first-stage turbine stator vanes and turbine rotor blades disposed around the rotating shaft,

wherein at least some of first-stage turbine stator vanes closest to the pipe pieces of the combustors among the turbine stator vanes are disposed downstream of a gap between a sidewall of a first pipe piece of the plurality of pipe pieces and a sidewall of a second pipe piece of the plurality of pipe pieces which is adjacent to the first pipe piece, wherein the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the gap between the sidewalls of the first and second pipe pieces to end portions of the sidewalls closer to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the first pipe piece and an internal surface of the sidewall of the second pipe piece in order to prevent the combustion gas from flowing in a gap between the leading edges of the first-stage turbine stator vanes disposed downstream of the gap and the end portions of the side walls closer to the turbine portion, and

wherein the internal surfaces of the sidewalls have shapes that are smoothly continuous with combustor-side external surfaces of the first-stage turbine stator vanes disposed downstream of the sidewalls such that the extending directions of the internal surfaces of the sidewalls being the same as the extending directions of the combustor-side external surfaces, the combustor-side external surfaces of the first-stage turbine stator vanes being surfaces which are closest to the internal surfaces of the sidewalls.

2. The communicating structure between combustors and a turbine portion according to claim 1 , wherein

the first-stage turbine stator vanes having cooling holes, the first-stage turbine stator vanes disposed downstream of the sidewalls has fewer cooling holes than the first-stage turbine stator vanes disposed at locations other than downstream of the sidewalls, the cooling holes are holes from which a cooling fluid to cool the first-stage turbine stator vanes is made to flow out to the peripheries of the first-stage turbine stator vanes.

3. The communicating structure between combustors and a turbine portion according to claim 1 , wherein

a cooling fluid for cooling the sidewalls is made to flow through a gap between the sidewall of the first pipe piece and the sidewall of the second pipe piece; and

the cooling fluid that has cooled the sidewalls subsequently flows along the peripheries of the first-stage turbine stator vanes disposed downstream of the sidewalls from downstream-side end portions of the sidewalls.

4. The communicating structure between a plurality of combustors and a turbine portion,

wherein the plurality of combustors generate combustion gas by combusting compressed air supplied from a compressor and fuel supplied from fuel nozzles, which are mixed inside a plurality of pipe pieces each of which are provided for each of the combustors and which are disposed next to each other around a rotating shaft,

the turbine portion that generates a rotational driving force by making the combustion gas sequentially pass through a turbine stage formed of a plurality of turbine stator vanes including first-stage turbine stator vanes and turbine rotor blades disposed around the rotating shaft,

wherein at least some of the first-stage turbine stator vanes closest to the pipe pieces of the combustors among the turbine stator vanes are disposed downstream of a gap between a sidewall of a first pipe piece of the plurality of pipe pieces and a sidewall of a second pipe piece of the plurality of pipe pieces which is adjacent to the first pipe piece,

wherein the distance from leading edges of the first-stage turbine stator vanes disposed downstream of the gap between the sidewalls of the first and second pipe pieces to end portions of the sidewalls closed to the turbine portion is equal to or less than a spacing between an internal surface of the sidewall of the first pipe piece and an internal surface of the sidewall of the second pipe piece in order to prevent the combustion gas from flowing in a gap between the leading edges of the first-stage turbine stator vanes disposed downstream of the gap and the end portions of the side walls closer to the turbine portion,

wherein the downstream-side end portions of the sidewalls are tilted in the direction in which the combustion gas is deflected by the first-stage turbine stator vanes, and

wherein the internal surfaces of the sidewalls have shapes that are smoothly continuous with combustor-side external surfaces of the first-stage turbine stator vanes disposed downstream of the sidewalls such that the extending directions of the internal surfaces of the sidewalls being the same as the extending directions of the combustor-side external surfaces, the combustor-side external surfaces of the first-stage turbine stator vanes being surfaces which are closest to the internal surfaces of the sidewalls.

5. The communicating structure between combustors and a turbine portion according claim 4 , wherein said sidewalls which are tilted, in cross-sectional view, form airfoil shapes together with the first-stage turbine stator vanes disposed downstream of the sidewalls.

6. A gas turbine comprising:

a compressor that compresses air;

a combustor that generates combustion gas by combusting compressed air supplied from the compressor and fuel supplied from a fuel nozzle, which are mixed therein;

a turbine portion that converts part of energy possessed by the combustion gas into a rotational driving force;

a rotating shaft that transmits the rotational driving force from the turbine portion to the compressor; and

the communicating structure between the combustors and the turbine portion according to claim 1 .