Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

Abstract: A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A wall arrangement for the main gas path of a gas turbine engine, including: a wall segment which defines the main gas path, the wall segment having a gas path side, an outboard side and a support wall extending from the outboard side towards a supporting structure, and a channel member abutting the support wall and having one or more channels defined by the abutment of the support wall and channel member, the one or more channel having radially separated inlet and outlet.

Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.

Abstract: An air cooled component for a gas turbine engine including a first wall and a second wall having opposing inner surfaces to define a gap therebetween, and a lattice of intersecting elongate ribs extending longitudinally along the first and second walls and transversely between the inner surfaces of the first and second walls to provide a plurality of cells. One or more portions of the ribs include an aperture to provide a flow path between adjacent cells so that the cells are in fluid communication.

Abstract: The present invention provides a method of manufacturing an abradable section to be formed on the interior of the casing of a gas turbine engine. The abradable section is formed by an additive manufacturing process to be of a lower density than the surrounding portions of the casing, but integrally formed with those portions. The abradable section thus formed can result in reduced blade fin tip wear, and may also have an improved performance. It may also have lower manufacturing costs. Formation of cooling passages in the abradable section is also easier and a wider range of designs of cooling passages can be provided. A gas turbine engine included such a casing is also provided.

Abstract: There is disclosed a method of manufacturing a semi-annular component 60 for a casing arrangement of a gas turbine by additive manufacture, the component having a lattice structure 84 and extending circumferentially about a central axis 11 so that a radial direction extends towards the central axis 11. The method comprises: fusing material at successive build locations along a build direction 98 to progressively form the component 60 so that members 86 of the lattice structure 84 have an elongate direction having a circumferential component; wherein the build direction 98 lies in a plane substantially normal to the central axis; and wherein the build direction 98 is inclined with respect to the radial direction at each build location so that members 86 of the lattice structure 84 are progressively formed along their elongate direction. A semi-annular component including a seal carrier is also disclosed.

Abstract: A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.

Abstract: A method for the manufacture of a component having an internal cavity is described. The method includes; defining an external geometry of the component, defining a core geometry of the component; using an additive layer manufacturing method, building the component from a plurality of layers laid on a first plane; wherein the core geometry includes a main core passage having a first end wall and a second end wall and is divided by one or more dividing walls, the dividing walls and end walls each having a common profile and wherein the profile includes an incline to the first plane.

Abstract: A wall arrangement for the main gas path of a gas turbine engine, including: a wall segment which defines the main gas path, the wall segment having a gas path side, an outboard side and a support wall extending from the outboard side towards a supporting structure, and a channel member abutting the support wall and having one or more channels defined by the abutment of the support wall and channel member, the one or more channel having radially separated inlet and outlet.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments.

Abstract: A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Abstract: A component of a turbine is disclosed. The component includes an carrier segment having a rail, an frame segment including a hanger having a flange supported on the rail of the carrier segment, and an inner surface having a section of a track for a turbine blade defined therein. The component also includes a retainer segment secured to the carrier segment such that the hanger is secured between the retainer segment and the carrier segment.