Turbofan blade blocking apparatus are disclosed. An example turbofan engine includes a containment casing, a fan, at least one of a trench filler or an abradable layer at least partially aligned with the fan in an axial direction defined by the turbofan engine, at least one of the trench filler or the abradable layer fixed to an inner radial surface of the containment casing, and a metal blocker coupled to the containment casing forward of the fan, an aft end of the metal blocker interfacing with at least one of the trench filler or the abradable layer.

A cooling fan has a fan shroud with a fan wheel recess surrounded by a shroud ring and a fan wheel rotatably mounted in the fan wheel recess for conveying the air flow along a conveying direction from a shroud upper side to a shroud underside. The fan wheel has a central hub cup with radially orientated blades and an outer ring connecting the blades at the blade tip ends. A circumferential ring gap is formed between the outer ring and the shroud ring. A rib structure in the ring gap reduces swirl in a gap flow orientated against the conveying direction. A shroud ring section of the shroud ring extends axially beyond the outer ring on the shroud underside. The shroud ring section is orientated parallel or at an angle of inclination and radially inwards relative to the conveying direction.

A compressor for an aircraft engine. A rotor includes blades rotatable about an axis. Blade tips extend between leading and trailing edges. A shroud surrounds the rotor, with an inner surface surrounding the tips. Grooves are defined in the shroud inner surface adjacent the tips. The grooves extend circumferentially about the shroud and radially from inlet openings to closed end surfaces. Groove sidewalls extend circumferentially about the axis. The grooves are axially spaced-apart, the most upstream inlet opening having an upstream end disposed upstream of the leading edges of the blades. The grooves have a swept angle from the inner surface, with a center of the inlet openings is axially offset of a center of the closed-end surfaces. The grooves span an overall axial distance corresponding to 30% or more of the blades’ chord length. The grooves have circumferential interruptions defined by baffles, and extend non-continuously around a shroud circumference.

A fan includes an air cylinder and an air outlet hood. An interior of the air cylinder is hollow to form a hollow cavity. The air cylinder has an air inlet and an air outlet. The air outlet hood is detachably disposed on the air outlet. The air outlet hood is provided with an annular air outlet for air outlet. An outer ring and/or an inner ring of the annular air outlet is formed with an annular guide rib extending toward the air inlet. The annular guide rib is configured to make an airflow cross section adjacent to the annular air outlet gradually decrease, so as to make an airflow in the air outlet hood cohesive, thereby increasing an air outlet speed of the annular air outlet. A hair dryer having the fan is also disclosed.

Structures, such as compressor casings, for reducing a thermal gradient are provided. For example, a compressor case is split such that it includes first and second case segments. The first case segment extends over a first portion of the compressor case circumference and comprises a first inner structure, a first outer structure, and a first porous structure integrally formed as a monolithic component. The first porous structure is defined between the first inner structure and the first outer structure. The second case segment extends over a second portion of the compressor case circumference and comprises a second inner structure, a second outer structure, and a second porous structure integrally formed as a monolithic component. The second porous structure is defined between the second inner structure and the second outer structure. Methods of cooling structures such as compressor casings also are provided.

Turbine and compressor casing abradable components for turbine engines include abradable surfaces with a zonal system of forward (zone A) and rear or aft sections (zone B) surface features. The zone A surface profile comprises an array pattern of non-directional depression dimples, or upwardly projecting dimples, or both, in the abradable surface. The dimpled forward zone A surface features reduce surface solidity in a controlled manner, to help increase abradability during blade tip rubbing incidents, yet they provide sufficient material to resist incoming hot working fluid erosion of the abradable surface. In addition, the dimples provide generic forward section aerodynamic profiling to the abradable surface, compatible with different blade airfoil-camber profiles. The aft zone B surface features comprise an array pattern of ridges and grooves.

A fan includes an annular frame, a rail assembly, a driving member and blades. The blades are connected to the driving member. The driving member is electromagnetically movable along the maglev assembly that extends along an edge of the annular frame. The driving member does not contact the annular frame or the maglev assembly so that when the fan is used, the maglev assembly is energized to generate an electromagnetic force between the maglev assembly and the driving member to move the driving member along the edge of the annular frame to drive the blades to rotate. Therefore, the blades can be rotated without having to use any motor behind the annular frame, thereby reducing the volume of the fan.

A ventilation device has a holder, in particular a ventilation frame, with a substantially circular continuous opening for receiving a ventilation wheel rotating about the central axis, thereof. The opening is bordered by an edge face running substantially cylinder-symmetrically about the central axis. As the edge face in two separate, diametrically opposed peripheral sections the radius is at least partly enlarged in comparison to the cylinder-symmetrical form in the remaining peripheral sections, and/or a circular projection of she edge face, which projection projects radially inwards, is axially offset away from a space provided for the ventilation wheel. Because of she corresponding shaping of the edge face of the opening, contact and/or development of noise between the ventilation wheel and the edge of the opening is prevented in the ventilation frame in the event of a yawing of the ventilation wheel.

A gas turbine compressor has a flow duct wall disposed radially opposite to an airfoil tip and has a circumferential groove having an upstream groove edge and a downstream groove edge, the circumferential groove having a web having a radial cutback. In at least one meridional section through an airfoil-tip-side end face of the web, an axial distance between an upstream beginning of the cutback and the upstream leading edge of the airfoil tip is at least 1% and/or no more than 40% of a chord length and/or an axial distance between the upstream leading edge of the airfoil tip and the downstream groove edge is at least 5% and/or no more than 40% of the chord and/or an axial distance between the upstream leading edge of the airfoil tip and a kink in an airfoil-tip-side upper edge of the web in the cutback is no more than 10% of the chord length and/or a radial distance between the airfoil tip and an airfoil-tip-side upper edge of the web in the cutback is at least 50% and/or no more than 1500% of a radial distance between the airfoil tip and the downstream groove edge radially opposite thereto.

A fan assembly is provided. The fan assembly includes a fan, a fan casing circumscribing the fan, and a fan casing heating system in thermal communication with the fan casing. The fan includes a hub, and a plurality of fan blades extending from the hub. Each fan blade of the plurality of fan blades terminates at a respective blade tip. A clearance gap is defined between the fan casing and the blade tips. The fan casing heating system is configured to apply heat to the fan casing when the fan is operating in a first operational mode, and remove the applied heat when the fan transitions into a second operational mode.