A ducting arrangement (12) for a combustion turbine engine is provided. The arrangement includes a ceramic liner (22) defining a hot gas path throughout a length of the ducting arrangement. A cooling sleeve (24) is disposed circumferentially outwardly onto the ceramic liner along the length. A metallic support frame (26) is disposed circumferentially outwardly onto the cooling sleeve along the length. The cooling sleeve may be structured with structural features along the length for biasing against the ceramic liner and the metallic support frame to resiliently accept mechanical and thermal growth induced loading that develops between the ceramic liner and the metallic support frame during operating conditions of the combustion turbine engine.

An aft heat shield for a fuel nozzle tip includes: an annular shield wall; an annular shield flange extending radially outward from an aft end of the shield wall; an annular baffle flange surrounding the conical section, and disposed such that an axial gap is defined between the shield flange and the baffle flange, the baffle flange including a radially outer rim extending axially forward therefrom; and a plurality of impingement cooling holes passing through the baffle flange and oriented to as to direct air flow towards the shield wall.

A fuel nozzle configured to channel fluid towards a combustion chamber is provided. The fuel nozzle includes a stem having a central passageway and at least one fuel tube disposed within the passageway. The fuel tube includes an outlet end portion having inner and outer walls separated by a cavity defined by a fixed aft face. The inner wall defines a central bore for delivering fuel to the combustion chamber. Further, the fuel nozzle includes an outer heat shield tube concentrically aligned with the outlet end portion of the fuel tube. The heat shield tube includes a circumferential outer wall having an aft face that stops upstream of the fixed aft face of the fuel tube. Thus, during operation, the heat shield tube is configured to thermally expand by sliding against the outer wall of the fuel tube.

An aircraft component is used for an aircraft gas-turbine engine. The aircraft component includes an annular part, a flange, and a boss. The annular part has an outer circumferential surface. The flange is formed at one end portion of the annular part in an axial direction. The boss projects from the outer circumferential surface of the annular part to the radial direction. On a section cut along an axial direction of the annular part, the outer circumferential surface of the annular part between the flange and the boss has a taper part that is formed into a tapered shape in which plate thickness becomes thicker from the flange toward the boss.

A combustion chamber comprises an upstream end wall, at least one fuel injector and at least one seal. Each fuel injector is arranged in a corresponding aperture in the wall. Each seal is arranged in a one of the apertures in the wall and around one of the fuel injectors. Each seal has a first portion, a second portion and a third portion. The second portion abuts the corresponding fuel injector. Each seal has a plurality of circumferentially spaced coolant passages extending longitudinally there-through from the upstream end to the downstream end of the seal to provide internal convective cooling of the seal to improve the working life of the seal.

A nozzle assembly includes a fuel distributor for issuing a spray of fuel. A fuel conduit is in fluid communication with the fuel distributor and has a first end and a second end. The first end and/or the second end of the fuel conduit is operatively connected to the fuel distributor. The fuel conduit is configured to allow relative movement between the first end and the second end to accommodate dimensional variations of at least one of the nozzle assembly or a combustor. A nozzle system includes the nozzle assembly and a combustor wall having a nozzle inlet. The nozzle assembly is positioned adjacent to the nozzle inlet.

A gas turbine includes a compressor, a turbine, and a combustor disposed downstream from the compressor and upstream from the turbine. The combustor includes an end cover. The combustor also includes a flange. The flange includes an internal fluid passage defined within the flange and the flange is coupled to an internal face of the end cover. A fuel port is integrally joined with the flange. The fuel port extends through the end cover between the flange and an inlet positioned outside of the end cover. The inlet of the fuel port is in fluid communication with the internal fluid passage of the flange.

The gas turbine engine including, in serial flow communication, a compressor, a combustor, a turbine, and a fluid system fluidly connecting at least two components of the gas turbine engine, also includes a tunable resonator in fluid flow communication with the fluid system, the tunable resonator. The tunable resonator has a resonating volume that varies as a function of a volume of an inflatable member located inside the tunable resonator. The inflatable member having a means for varying the volume of the inflatable member, to thereby tune the resonating volume to a selected frequency of pressure fluctuations or acoustic waves within the fluid system.

A turbine component assembly is disclosed, including a first component, a second component, and a circumferentially oriented flat spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The circumferentially oriented flat spring is disposed on and directly contacting the second component and directly contacting and supporting the first component as a compliant contact interface between the first component and the second component. The circumferentially oriented flat spring provides a radial spring compliance between the first component and the second component.

A turbine component assembly is disclosed, including a first component, a second component, and a cantilever spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The cantilever spring is attached directly to the second component as a compliant contact interface between the first component and the second component. The cantilever spring provides a radial spring compliance between the first component and the second component. During operation, the cantilever spring directly contacts and supports the first component.