This disclosure describes a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts the either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes axially compressible segments which allow the seal member to bend longitudinally.

A scroll structure of a centrifugal compressor according to an embodiment is a scroll structure of a centrifugal compressor having a scroll passage formed in spiral shape, comprising: a tongue portion separating the scroll passage from an outlet passage connected to the downstream side of the scroll passage at the most downstream position of the scroll passage in a passage connecting portion where a winding start portion and a winding end portion of the scroll passage intersect; and a ridge portion protruding from an inner peripheral surface of the scroll passage on the axially downstream side of the centrifugal compressor toward the axially upstream side of the centrifugal compressor, with a protruding height toward the axially upstream side gradually increasing toward the tongue portion from a starting position that is located upstream from the tongue portion in the scroll passage. The starting position is a position at an angle of 8 degrees or less in the circumferential direction of the centrifugal compressor from the tongue portion toward the upstream side of the scroll passage.

A fan having a housing including a front piece that is separable but connectable to a back piece is disclosed. The front piece has a first connecting edge and a downstream edge, and the back piece has a second connecting edge and an upstream edge. The second connecting edge is configured to be connected to the first connecting edge. The fan may include a handle, the handle having a first portion integral with the front piece and a second portion integral with the back piece, the first portion configured to be connected to the second portion. The fan may further include air guide ribs provided on an interior surface of the housing and/or a ramp that starts at a location downstream of the upstream edge of the housing and ends at the downstream edge of the housing.

A blower includes a propeller fan, and an enclosure. The propeller fan is configured to rotate around a rotation axis. The propeller fan includes a plurality of blades at unequal pitches. The enclosure houses the propeller fan. The enclosure includes a bell mouth. The enclosure has a depth L. The bell mouth includes a cylindrical part parallel to the rotation axis.

[00001]$0.14\le \frac{H2}{H0}\le 0.22\#$

A length of the blades is H0 in a rotation axis direction, and a length of the cylindrical part is H2 in the rotation axis direction.

A ring assembly has a housing made of woven composite material carrying on its radially inner face an acoustic panel with a cellular structure covered with a composite material. The housing includes at least one radial recess in which is engaged at least one radially outwardly projecting part of the radially outer face of the acoustic panel.

A process for additively controlled surface features of a gas turbine engine casing. The process comprises forming the casing having an inner surface and an outer surface opposite the inner surface; forming a surface feature on the casing proximate the inner surface, wherein the surface feature comprises a structure on the inner surface configured to align or misalign with respect to a flow direction of a working fluid in a flow path of the casing.

A pump features a liquid sensing device (LSD) in combination with a housing. The LSD senses the level of a liquid collecting outside the pump and turns the pump on/off for pumping the liquid. The housing includes a housing wall to contain the LSD. The housing wall has an outside wall surface with an outside sensing surface. The housing includes an inside mounting structure to mount the LSD inside the housing in relation to the outside sensing surface. The outside sensing surface has ribs extending or projecting outwardly away from the outside wall surface in order to prevent an object from being stuck on the outside sensing surface, and allow the LSD to sense the level of the liquid collecting outside the pump and touching the outside sensing surface, reducing a malfunction of the pump due to the object contacting the outside sensing surface.

A blower including a housing at least partially defining a chamber, a motor including a drive shaft defining a rotational axis, and an impeller drive by the motor to generate an air flow in the chamber. The blower also includes a coupler operably connected between the drive shaft and the impeller to transmit torque therebetween, the coupler being connected to one of the drive shaft and the impeller and including a plurality of ribs configured to engage the other of the drive shaft and the impeller, each rib defining a rib axis transverse to the rotational axis, each rib axis being arranged tangent to a circle centered on the rotational axis.

A coated component, along with methods of its formation and use, is provided. The coated component may include a substrate having a surface with a plurality of cavities defined therein, a bond coating (e.g., including a silicon material) on the surface of the substrate within the cavities, and an environmental barrier coating over the surface of the substrate and encasing the bond coating within the cavities such that the bond coating, when melted, is contained within the cavities. Such a coated component may be, in one embodiment, a turbine component, such as a CMC component for use in a hot gas path of a gas turbine engine.

Provided is a method for sealing an annular gap in a turbine with a housing and a rotor, in which method a) an annular recess, which is arranged coaxially with respect to the rotor and opposite the tips of the rotor blades of a stage, is provided in the housing or in at least one element attached to the housing, b) a subdivided insert ring, which is formed such that it can be inserted into the recess in a form-fitting manner with play, is provided, c) the insert ring is inserted into the recess, more particularly in that the insert ring is pushed into the recess at least substantially in the axial direction, and d) the insert ring is fixed using securing elements in such a way that an at least substantially axially directed clamping force is applied by means of the securing elements. A turbine is also provided.