Ring segment surface side element for a ring segment of a gas turbine, ring segment support side element for a ring segment of a gas turbine, ring segment, gas turbine, and ring segment cooling method for a ring segment of a gas turbine

Abstract

A ring segment surface side element (104) for a ring segment (52) of a gas turbine (1), which is contained in the ring segment (52) which is arranged at a position opposite a turbine blade (33) on a stationary side of the gas turbine (1) and which serves as part of a combustion gas flow path (R1) through which combustion gas flows during operation of the gas turbine (1), wherein the ring segment surface side element (104) is formed from a composite material with a ceramic matrix, wherein the ring segment surface side element (104) comprises: a surface section (150) which, in the arranged state in the gas turbine (1), forms part of the combustion gas flow path (R1), a reversing section (152) comprising a first part (162) which, in the arranged state in the gas turbine (1), extends outwards in a radial direction of the gas turbine (1) from the surface section (150), and a second part (164) which extends from an end part of the first part (162) to a center line (159) of the surface section (150), and a projecting section (154) extending outwards from the reversing section (152) in the radial direction of the gas turbine (1), and wherein the ring segment surface side element (104) has a structure such as is formed by bending a single plate.

Claims

[1] A ring segment surface side element (104) for a ring segment (52) of a gas turbine (1), which is included in the ring segment (52) arranged at a position opposite a turbine blade (33) on a stationary side of the gas turbine (1) and which serves as a part of a combustion gas flow path (R1) through which combustion gas flows during operation of the gas turbine (1), wherein the ring segment surface side element (104) is formed from a ceramic matrix composite material, wherein the ring segment surface side element (104) comprises: a surface section (150) which, when arranged in the gas turbine (1), forms part of the combustion gas flow path (R1), a reversing section (152) comprising a first part (162) extending outwardly from the surface section (150) in a radial direction of the gas turbine (1) when arranged in the gas turbine (1), and a second part (164) extending from an end part of the first part (162) to a center line (159) of the surface section (150), and a projection portion (154) extending outward from the reversing portion (152) in the radial direction of the gas turbine (1), and wherein the ring segment surface side member (104) has a structure formed by bending a single plate. [2] A ring segment support side element (102) for a ring segment (52) of a gas turbine (1), which is included in the ring segment (52) which is arranged at a position opposite a turbine blade (33) on a stationary side of the gas turbine (1) and which carries a ring segment surface side element (104; 104a; 104b) which serves as a part of a combustion gas flow path (R1) through which combustion gas flows during operation of the gas turbine (1), wherein the ring segment support side element (102) is formed of metal, wherein the ring segment support side element (102) comprises: an engagement portion (134) to be engaged with the ring segment surface side element (104; 104a; 104b), and an opposite portion (135; 135b) which a rear surface (172) of a surface portion (150) of the ring segment surface side element (104; 104a; 104b), wherein the surface portion (150) forms part of the combustion gas flow path (R1) when installed in the gas turbine (1), and between the opposite section (135; 135b) and the rear surface (172) of the surface section (150) forms a cooling flow path (120), in which cooling air flows during operation of the gas turbine (1), wherein the opposite portion (135; 135b) comprises a flow path resistance adjusting mechanism (122) configured to adjust a flow path resistance of the cooling flow path (120), the flow path resistance adjustment mechanism (122) is configured to adjust a pressure of cooling air (CA) flowing in the cooling flow path (120) upstream in the direction (FG) of the combustion gas flow through the gas turbine (1) during operation to be higher than a pressure of cooling air (CA) flowing in the cooling flow path (120) downstream in the direction of the combustion gas flow, the ring segment support side element (102) has a plurality of through holes (136a, 136b, 136c) which connect the opposite section (135; 135b) to a cooling air supply space (80) into which the cooling air (CA) is supplied during operation and through which the cooling air (CA) flows, and the through holes (136a,136b,136c) are positioned only near the center of the ring segment support side element (102) in a direction of rotation of the gas turbine (1). [3] The ring segment support side member (102) according to claim 2, wherein the through holes (136a, 136b, 136c) have a total cross-sectional area that differs between positions in a direction (FG) of combustion gas flow through the gas turbine (1). [4] The ring segment support side member (102) according to claim 2 or 3, wherein the flow path resistance adjusting mechanism (122) is formed by forming the opposing portion (135b) to be inclined in a direction closer to the rear surface (172) of the ring segment surface side member (104b) when extending from the upstream side to the downstream side in the direction (FG) of the combustion gas flow through the gas turbine (1). [5] The ring segment support side member (102) according to any one of claims 2 to 4, wherein the flow path resistance adjusting mechanism (122) has a structure in which the opposing portion (135) has a surface roughness that varies with a position and / or a structure in which an uneven part is formed on the opposing portion (135). [6] The ring segment support side member (102) according to any one of claims 2 to 5, wherein the flow path resistance adjusting mechanism (122) includes a partition (124) that divides the cooling flow path (120) into a plurality of spaces in a cross section orthogonal to a rotation direction of the gas turbine (1). [7] The ring segment support side member (102) according to claim 6, wherein the partition (124) is provided integrally with the opposing portion (135). [8] The ring segment support side member (102) according to claim 6 or 7, wherein the partition (124) is a plate member (180) fitted into a groove (182) formed at a position facing the plate member (180). [9] The ring segment support side member (102) according to any one of claims 6 to 8, wherein a part of the partition (124) that comes into contact with the back surface (172) of the ring segment surface side member (104a) is formed of a material (186) that is different from the material of the ring segment support side member (102). [10] A ring segment (52) comprising: the ring segment surface side element (104) according to claim 1, and a ring segment support side member (102) which is arranged on an outer side of the ring segment surface side member (104) in a radial direction of a gas turbine (1), supports the ring segment surface side member (104), forms a cooling flow path (120) in which cooling air flows between the ring segment support side member (102) and the ring segment surface side member (104) during operation, and is formed of metal, wherein the ring segment surface side member (104) has a sealing mechanism (112,114) at a position upstream of the projection portion (154) arranged on an upstream side in a direction (FG) of a combustion gas flow through the gas turbine (1) and / or at a position downstream of the projection portion (154) arranged on a downstream side in the direction (FG) of the combustion gas flow. [11] A gas turbine (1) comprising: a turbine blade (33) mounted on a rotatable turbine shaft (8), a turbine guide vane (32) mounted facing the turbine blade (33) in an axial direction, the ring segment (52) according to claim 10, and a housing chamber (24) arranged on an outer circumference of the ring segment (52) and carrying the turbine guide vane (32). [12] A ring segment cooling method for a ring segment (52) of a gas turbine (1), the ring segment cooling method comprising: a step of supplying cooling air (CA) to an outside in a radial direction of a ring segment support side member (102) supporting a ring segment surface side member (104) forming part of a combustion gas flow path (R1) and formed of a ceramic matrix composite material, a step of supplying the cooling air (CA) from the ring segment support side member (102) to a cooling flow path (120) between the ring segment support side member (102) and the ring segment surface side member (104), and a step of performing convection cooling by causing the cooling air (CA) supplied to the cooling flow path (120) to flow in a rotational direction of the gas turbine (1), wherein the step of performing convection cooling comprises a step of adjusting a pressure of cooling air (CA) flowing in the cooling flow path (120) upstream in a direction (FG) of a combustion gas flow through the gas turbine (1) to be higher than a pressure of the cooling air (CA) flowing in the cooling flow path (120) downstream in the direction (FG) of the combustion gas flow, the cooling air (CA) supplied to the cooling flow path (120) flows in both directions along the direction of rotation of the gas turbine (1) from a position at which the cooling air is supplied to the cooling flow path (120), and the cooling air (CA) is supplied to the cooling flow path (120) only near the center of the ring segment support side element (102) in the direction of rotation of the gas turbine (1). [13] The ring segment cooling method according to claim 12, wherein the cooling air (CA) having passed through the cooling flow path (120) flows through a gap between the ring segment support side member (102) and an adjacent ring segment support side member (102). [14] The ring segment cooling method according to claim 12, wherein the cooling air (CA) supplied to the cooling flow path (120) also flows through a gap between a side surface of the ring segment support side member (102) in the axial direction and a side surface member of the ring segment surface side member (104).

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