An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.

Gas turbine unit having an axis parallel to the main gas flow, the gas turbine unit comprising: a blade having a tip; a stator heat shield having an inner surface facing the blade tip; wherein the inner surface of the stator heat shield and the blade tip define a variable clearance depending on the applied thermal condition; wherein the blade tip is configured to have a cylindrical shape along the axial direction in a hot running condition starting from a conical shape along the axial direction in a cold starting condition.

A method for large-scale, real-time simultaneous additive and subtractive manufacturing is described. The apparatus used in the method includes a build unit and a machining mechanism that are attached to a positioning mechanism, a rotating platform, and a rotary encoder attached to the rotating platform. The method involves rotating the build platform; determining the rotational speed; growing the object and the build wall through repetitive cycles of moving the build unit(s) over and substantially parallel to multiple build areas within the build platform to deposit a layer of powder at each build area, leveling the powder, and irradiating the powder to form a fused additive layer at each build area; machining the object being manufactured; and cutting and removing the build wall. The irradiation parameters are calibrated based on the determined rotational speed.

Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.

An assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a gas turbine engine component that has a first interface portion, and a support that has a mounting portion and a second interface portion, the mounting portion attachable to an engine static structure, a first retention feature that releasably secures the first interface portion to the support in a first installed position of the gas turbine engine component, and a second retention feature dimensioned to secure the first interface portion to the second interface portion in a second installed position of the gas turbine engine component. The first installed position differs from the second installed position, and one of first and second retention features is dimensioned to carry the gas turbine engine component in response to release of another one of the first and second retention features. A method of sealing for a gas turbine engine is also disclosed.

An airfoil for a turbomachine such as a gas turbine engine includes a pressure side and a suction side, a flow-distributing forward wall and an inner cooling wall. A switchbacked passage extends through the airfoil, and the flow-distributing forward wall has a plurality of jetting orifices formed therein and connecting the switchbacked passage to a forward cavity. The jetting orifices are oriented to produce wall jets of cooling fluid directed in an upstream direction toward a back side of the leading edge. A second passage extends between the forward cavity and outlets of the airfoil, so as to convey cooling fluid in a downstream direction toward the outlets.

A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.

A profiled element used is disclosed for generating a force, the profiled element comprising a material having an active surface; a plurality of cavities located on the active surface of the material, the plurality of cavities comprising pin holes, each pin hole having an opening of a micrometric size on the active surface and a depth of a micrometric size greater than its diameter; wherein each pin hole is hermetically sealed on the opposite side of the cavity; and further wherein an airflow circulation against the active surface of the material causes a pressure change on the active surface and inside each of the plurality of cavities thereby generating a force.

A staged injector in a combustor of a gas turbine. The staged injector may include an injector tube comprising a lateral wall enclosing an injection passageway that extends between an outlet and inlet. An outboard segment of the injector tube may include an exterior face. A cover may be formed about the outboard segment so form a surrounding plenum. The cover may include a side wall that radially overlaps the outboard segment and forms a first portion of the surrounding plenum therebetween. A ceiling wall of the cover may form a second portion of the surrounding plenum. A directional cover port may connect the first portion of the surrounding plenum to a feed cavity. The staged injector may include lateral vanes on the exterior face of the outboard segment that are configured to radially deflect a flow entering the surrounding plenum toward the inlet of the injector tube.

A ceramic matrix composite article, method for forming the article, and perforated ply which may be incorporated therein are disclosed. The article includes at least one shell ply forming an exterior wall having first and second portions and defining a plenum. An annular brace formed of at least one structural support ply is disposed within the plenum, including a first integral portion integral with and part of the first portion of the exterior wall, a first curved portion extending from the first integral portion and curving across the article plenum to the second portion of the exterior wall, a second integral portion integral with and part of the second portion of the exterior wall, a second curved portion extending from the second integral portion and curving across the article plenum to the first curved portion, and an overlap in which the first and second curved portions are integral.