Abstract: An impingement baffle for directing a cooling fluid onto a target surface includes a baffle body having a first end opposite a second end, and a first side opposite a second side. The second side is spaced a distance apart from the target surface, with the distance varying from the first end to the second end. The baffle body defines impingement holes that extend through the baffle body from the first side to the second side. The impingement holes are spaced apart along the baffle body to receive the cooling fluid. The impingement baffle includes tubular extensions coupled to the second side. Each tubular extension is in fluid communication with a respective one of the impingement holes to direct the cooling fluid onto the target surface. Each tubular extension extends for a length from the second side, and the length of each tubular extension is based on the distance.

Abstract: An impingement baffle for directing a cooling fluid onto a target surface includes a baffle body having a first end opposite a second end, and a first side opposite a second side. The second side is spaced a distance apart from the target surface, with the distance varying from the first end to the second end. The baffle body defines impingement holes that extend through the baffle body from the first side to the second side. The impingement holes are spaced apart along the baffle body to receive the cooling fluid. The impingement baffle includes tubular extensions coupled to the second side. Each tubular extension is in fluid communication with a respective one of the impingement holes to direct the cooling fluid onto the target surface. Each tubular extension extends for a length from the second side, and the length of each tubular extension is based on the distance.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.

Abstract: A turbine shroud assembly includes a shroud support and a shroud segment. The shroud support structure includes a forward support rail and an aft support rail. The forward support rail includes forward first engagement structures and the aft support rail includes aft first engagement structures. The shroud segment includes a forward segment rail and an aft segment rail. The forward segment rail includes forward second engagement structures positioned on a forward segment rail periphery and the aft segment rail includes second engagement structures positioned on an aft segment rail periphery. The forward first engagement structures radially and circumferentially engage with the forward second engagement structures and the aft first engagement structures radially and circumferentially engage with the aft second engagement structures to radially and circumferentially interlock the shroud segment to the shroud support structure.

Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.

Abstract: A turbine shroud assembly includes a shroud support and a shroud segment. The shroud support structure includes a forward support rail and an aft support rail. The forward support rail includes forward first engagement structures and the aft support rail includes aft first engagement structures. The shroud segment includes a forward segment rail and an aft segment rail. The forward segment rail includes forward second engagement structures positioned on a forward segment rail periphery and the aft segment rail includes second engagement structures positioned on an aft segment rail periphery. The forward first engagement structures radially and circumferentially engage with the forward second engagement structures and the aft first engagement structures radially and circumferentially engage with the aft second engagement structures to radially and circumferentially interlock the shroud segment to the shroud support structure.

Abstract: A shroud assembly for a gas turbine engine includes a shroud support and a plurality of shroud segments that are attached to the shroud support. The shroud segment includes an internal cooling passage.

Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.