The present disclosure concerns a preform for a curved composite stiffener for an axisymmetric part such as a shroud, including at least one web and at least one flange curved about an axis of revolution of the preform and defining a substantially T or an I shaped section. In one form, the preform includes a web and a flange, wherein the web includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns oriented radially relative to said axis, and the flange includes a plurality of warp yarns circumferentially oriented relative to the axis of revolution of the preform, and a plurality of weft yarns substantially parallel to said axis.

A transition structure between a combustor and a turbine in a gas turbine includes: a transition piece including a duct and a flange protruding from a downstream end of the duct; and a piece cover surrounding the duct. The piece cover includes a boss that is fixed to the turbine by a bolt in a state where the flange is sandwiched between the boss and the turbine.

An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

An article of manufacture includes a rotor blade configured for use with a turbomachine. The blade is configured for attachment to a rotor wheel. The blade is configured to substantially reduce the possibility of attachment with an undesired rotor wheel by modification of at least one characteristic of the blade, so that the modification of the characteristic is matched by a complementary characteristic of the rotor wheel. The characteristic of the blade is, neck width, platform length, platform angle, platform height, tang height, or circumferential width. The blade and the wheel comprise a first stage of the turbomachine. The undesired rotor wheel is in a second stage of the turbomachine, where the first stage is different from the second stage. The complementary characteristic of the wheel is, slot opening width, platform opening depth, slot neck width, slot neck angle, slot tang depth, or slot tang width.

A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

An article has a body having: a first face; and a first bevel surface extending from the first face. A plurality of first channels along the first bevel surface extending from the first face. A ceramic coating is along the inner diameter surface and the first bevel surface.

The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system includes: an overspeed protection system that activates an activation member in case a shaft failure is detected; a fuel limiting mechanism coupled with the activation member, wherein the fuel limiting mechanism is configured to limit the fuel supply to the gas turbine engine combustor if the activation member is activated; a variable stator vane mechanism which is configured to adjust variable stator vanes of a compressor of the gas turbine engine in their rotational position, the variable stator vanes having a closed position which blocks air flow through the compressor. A connecting fuel line connecting the fuel limiting mechanism and the variable stator vane mechanism is provided, wherein upon activation of the activation member the fuel limiting mechanism pressurizes the connecting fuel line, thereby activating the variable stator vane mechanism to move at least one row of the variable stator vanes into the closed position.

The invention regards a gas turbine engine control system and a method for limiting turbine overspeed in case of a shaft failure. The control system includes: an overspeed protection system that activates an activation member in case a shaft failure is detected; a fuel limiting mechanism coupled with the activation member, wherein the fuel limiting mechanism is configured to limit the fuel supply to the gas turbine engine combustor if the activation member is activated; a variable stator vane mechanism which is configured to adjust variable stator vanes of a compressor of the gas turbine engine in their rotational position, the variable stator vanes having a closed position which blocks air flow through the compressor. A connecting fuel line connecting the fuel limiting mechanism and the variable stator vane mechanism is provided, wherein upon activation of the activation member the fuel limiting mechanism pressurizes the connecting fuel line, thereby activating the variable stator vane mechanism to move at least one row of the variable stator vanes into the closed position.