A gas turbine engine has a movable interface that permits rotation of the inlet portion and cone. The movable interface moves within a surface of the flow sleeve that is designed to receive the movable interface. A sealing ring and groove located at the connection between the sealing ring and groove allow axial movement.

A combustor for a gas turbine engine includes a combustor shell, a heat shield and a burner seal. The combustor shell includes metallic materials and is formed to define an interior combustion space. The heat shield includes ceramic matrix composite materials and is configured to shield a portion of the combustor shell from the interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield.

This disclosure relates to systems and methods of predicting physical parameters for a combustion fuel system. In one embodiment of the disclosure, a method of predicting physical parameters of a combustion fuel system includes causing water injection in at least one combustor. The water injection is associated with at least one time and performed during gaseous fuel operations or after liquid fuel operations. The method includes measuring exhaust spread data associated with the water injection and allows correlating the exhaust spread data to at least one physical parameter associated with a nozzle or a valve of the fuel system. The method further includes storing the exhaust spread data, the at least one physical parameter, and the at least one time to a database. The method further provides stored historical data from the database to an analytical model. The analytical model is operable to predict, based at least partially on the stored historical data, at least one future physical parameter associated with a future time.

A gas turbo machine having a combustion chamber. The combustion chamber includes a chamber bottom having an upstream wall and a downstream wall extending between inner and outer annular walls. Each upstream and downstream walls each having openings for mounting fuel injection devices for injecting fuel through said openings. The downstream wall is sectorised.

The present disclosure is directed a combustor. The combustor includes an annularly shaped liner having a downstream end that is rigidly connected to an aft frame. A flow sleeve circumferentially surrounds at least a portion of the liner and is radially spaced from the liner to form a cooling flow annulus therebetween. A plurality of fuel injector assemblies is circumferentially spaced about the flow sleeve. Each fuel injector assembly extends radially through the flow sleeve and the liner. Each fuel injector assembly is rigidly connected to the flow sleeve and to the liner. An aft portion of the flow sleeve terminates axially short of the aft frame to form an axial gap between the aft end and the aft frame to allow for unrestrained axial expansion and contraction of the aft end.

In accordance with one embodiment, a system is presented. The system includes a casing, a combustor disposed within the casing, and a sensing device located on the casing and configured to sense a plurality of acoustic emission waves and generate an electrical signal based on the sensed plurality of acoustic emission waves. The system further includes a processing subsystem operationally coupled to the sensing device and configured to determine one or more features based on the electrical signal, and determine a presence or an absence of fretting wear in the combustor based at least on the one or more features.

An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.

In a gas turbine engine, an inside turn duct portion and a nozzle guide vane are engaged together via an engagement part. An axially forward-facing load acting on a reverse flow combustor is transmitted to the vane via the engagement part. Therefore, it is possible to counteract an axially backward-facing load acting on the vane from combustion gas with the axially forward-facing load, thus reducing a bending moment acting on a support part of the vane and enhancing durability. Furthermore, part of the axially forward-facing load acting on the combustor acts on the support part via the vane. The axially forward-facing load acting on the support part of the combustor without via the vane is decreased by the above-mentioned part. Thus, it is possible to reduce bending moments acting on an outside turn duct portion and dome portion of the combustor and enhance durability, thereby preventing degradation of combustion performance.

An axial fuel staging (AFS) system for a combustor is provided. The AFS system includes a secondary fuel injector, an injector housing surrounding the secondary fuel injector, and a conduit assembly in flow communication with the secondary fuel injector. The conduit assembly includes a first conduit for conveying fuel to the secondary fuel injector, and a second conduit circumscribing the first conduit such that a channel is defined between the first conduit and the second conduit. The first conduit and the second conduit terminate within the injector housing.

A fuel conduit for a fuel injector includes a coiled tube with a longitudinal segment arranged along a flow axis and a radial segment. The radial segment extends about the flow axis and is in fluid communication with the longitudinal segment. The wall one or more of the longitudinal and radial segments increases at a thickness transition location offset from a minimum radius of curvature location along the fuel conduit to limit stress within the fuel conduit. Fuel injectors and methods of making fuel injectors are also described.