Gas turbine combustor transition piece including inclined surface at downstream end portions for reducing pressure fluctuations
A gas turbine combustor and a gas turbine; wherein inclined surfaces are provided on inner surfaces of side walls neighboring in a circumferential direction at downstream end portions of transition pieces of combustors, the inclined surfaces being configured to increase a passage area of the transition pieces, a ratio (S/P) is from 0 to 0.2, where (P) is a pitch dimension of first stage vanes, and (S) is a circumferential dimension from an intermediate point between neighboring transition pieces to an upstream end of a first stage vane closest in the circumferential direction; and a ratio (L/P) is from 0.3 to 0.55, where (P) is the pitch dimension, and (L) is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.
1. A gas turbine, comprising:
a compressor configured to compress air;
a plurality of combustors disposed in an annular configuration about a rotor, each of the combustors being configured to combust a mixture of compressed air compressed by the compressor and fuel;
a turbine configured to obtain rotational power from combustion gas produced by the combustors, the turbine having first stage vanes; and
a plurality of transition pieces each arranged between a respective one of the combustors and the turbine, the transition pieces having side walls with inclined surfaces provided on inner surfaces of the side walls neighboring in a circumferential direction at downstream end portions of the transition pieces, the inclined surfaces being configured to increase a passage area of the transition pieces;
wherein the transition pieces and the turbine are configured such that a ratio S/P is in a range from 0 to 0.2, where P is a pitch dimension of the first stage vanes of the turbine, and S is a circumferential dimension from an intermediate point between neighboring transition pieces of the transition pieces to an upstream end of a first stage vane of the first stage vanes closest in the circumferential direction; and
wherein the transition pieces and the turbine are further configured such that a ratio L/P is in a range from 0.3 to 0.55, where P is the pitch dimension, and L is an axial dimension from a downstream end of the transition piece to the upstream end of the first stage vane.
2. The gas turbine according to claim 1 , wherein the transition pieces and the turbine are further configured such that the ratio S/P of the circumferential dimension S to the pitch dimension P is from 0.05 to 0.15, and the ratio L/P of the axial dimension L to the pitch dimension P is from 0.3 to 0.4.
3. The gas turbine according to claim 1 , wherein the transition pieces and the turbine are further configured such that a ratio between the number of combustors and the number of first stage vanes is 2:3 or greater.
4. The gas turbine according to claim 1 , wherein the transition pieces are further configured such that the inclined surface is provided at a downstream end portion of the transition piece on an inner surface of at least one side wall of a pair of the side walls disposed in opposition with respect to the circumferential direction of the rotor, the inclined surface inclining toward a neighboring transition piece as it extends downstream in an axial direction of the transition piece to the downstream end of the transition piece.
5. The gas turbine according to claim 1 , wherein the turbine is configured such that positions of the upstream ends of the first stage vanes are located aligned in a radial direction about the rotor.
6. The gas turbine according to claim 1 , wherein the transition pieces and the turbine are further configured such that the ratio L/P is set taking into account an amount of cooling air for a shroud which supports the first stage vanes and turbine efficiency.