System and method for cooling turbine shroud trailing edge

A gas turbine engine comprising:

• a compressor;
• a combustion system;
• and
• a turbine section comprising:
• an outer casing;
• an outer shroud segment coupled to the outer casing;
• an inner shroud segment coupled to the outer shroud segment to form a cavity between the outer shroud segment and the inner shroud segment, the cavity being configured to receive a cooling fluid from the compressor, wherein the inner shroud segment comprises:
• a body including a leading edge, a trailing edge opposite the leading edge, a first side edge, a second side edge opposite the first side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges, wherein a first lateral side of the pair of opposed lateral sides is configured to interface with the cavity, and a second lateral side of the pair of opposed lateral sides is oriented toward a hot gas flow path;
• a plurality of channels disposed within the body, wherein each channel comprises a first flow passage extending radially inward from an inlet in the first lateral side, a second flow passage in fluid communication with the first flow passage, a fourth flow passage parallel to and laterally offset from the second flow passage and defining an outlet, and a third flow passage defining a single linear portion disposed between the second flow passage and the fourth flow passage;
• wherein the second flow passage, the third flow passage, and the fourth flow passage are disposed on the second lateral side adjacent the trailing edge;
• wherein the second flow passage and the fourth flow passage define cooling flow paths in a first direction, and the third flow passage defines a cooling flow path in a second direction different from the first direction;
• and
• wherein the plurality of channels is configured to convey the cooling fluid from the cavity to the trailing edge to cool the trailing edge.

A shroud segment for use in a turbine section of a gas turbine engine, the shroud segment comprising:

• a body including a leading edge, a trailing edge, a first side edge, a second side edge, and a pair of opposed lateral sides between the leading and trailing edges and the first and second side edges, wherein a first lateral side of the pair of opposed lateral sides is configured to interface with a cavity having a cooling fluid, and a second lateral side of the pair of opposed lateral sides is oriented toward a hot gas flow path;
• a plurality of channels disposed within the body, wherein each channel comprises a first flow passage extending radially inward from an inlet in the first lateral side, a second flow passage in fluid communication with the first flow passage, a fourth flow passage parallel to and laterally spaced from second flow passage and defining an outlet, and a third flow passage defining a single linear portion disposed between the second flow passage and the fourth flow passage;
• and wherein the second flow passage and the fourth flow passage define cooling flow paths in a first direction, and the third flow passage defines a cooling flow path in a second direction different from the first direction;
• wherein the second flow passage, the third flow passage, and the fourth flow passage are disposed on the second lateral side adjacent the trailing edge;
• and
• wherein the plurality of channels is configured to convey the cooling fluid from the cavity to the trailing edge to cool the trailing edge.