A flex seal assembly includes a plurality of duct segments configured to be disposed about a joint between a turbine of a turbine system and a diffuser of the turbine system. The plurality of duct segments includes a groove configured to extend circumferentially around the joint. Additionally, the plurality of duct segments includes a first duct segment of the plurality of duct segments and a second duct segment of the plurality of duct segments. The second duct segment includes a drain. Furthermore, the plurality of duct segments include insulation disposed within the groove of the plurality of duct segments.

A flex seal assembly includes a plurality of duct segments configured to be disposed about a joint between a turbine of a turbine system and a diffuser of the turbine system. The plurality of duct segments includes a groove configured to extend circumferentially around the joint. Additionally, the plurality of duct segments includes a first duct segment of the plurality of duct segments and a second duct segment of the plurality of duct segments. The second duct segment includes a drain. Furthermore, the plurality of duct segments include insulation disposed within the groove of the plurality of duct segments.

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.

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 for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.

A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.

An acoustic liner that may be for a turbofan engine may comprise a first sidewall, a second sidewall, wherein the first sidewall and the second sidewall define a plurality of cells disposed therebetween, and a pre-cut septum ribbon comprising a plurality of permeable septum coupled together via a plurality of connecting members, with each one of the plurality of permeable septum being generally in a respective one of the plurality of cells.

A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.

A method for a position determination of a turbine blade of a high-pressure turbine stage of a gas turbine that is connected to a high-pressure compressor via a shaft, wherein each turbine blade of the high-pressure turbine is recorded on a record card with a relative position. The method includes: determining a position of a blade lock of a stage of the high-pressure compressor, where the stage is selected such that, when the gas turbine is mounted, the blade lock is brought into view of a boroscope, which is guided through a boroscope opening on the gas turbine by rotating the shaft, and so that the blade lock can be identified; and marking that turbine blade on the record card that is in view of a second boroscope, which is guided through a second boroscope opening on the gas turbine when the blade lock is in view of the boroscope.