A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots is substantially continuous over a selected portion of a surface and perpendicular to or parallel to a centerline of the liner assembly.

A blade includes an airfoil, a stationary portion coupled to a radially inner end of the airfoil, and a leakage flow guide vane assembly coupled to the stationary portion. The leakage flow guide vane assembly includes a plurality of passages defined therein. The passages are oriented to induce a swirl velocity to a working fluid flowing through the passages.

A flow guide structure for a casing flange, and a casing and a turbomachine having the same, include a flange portion connecting an upper casing and a lower casing and a flow guide positioned at the flange portion to guide fluid to flow close to the flange portion, whereby steam flow resistance is reduced around an inner casing flange of a turbine and the steam flow is smoothed.

A guide blade for a gas turbine is disclosed. The guide blade includes a blade leaf having a receptacle in which at least one sealing element is arranged, where the sealing element is movable relative to the blade leaf between a sealing setting, in which the sealing element is at least partially moved out of the receptacle, and a storage setting, in which the sealing element is moved back into the receptacle. The guide blade further includes at least one fluid channel by which fluid under pressure can be routed into the receptacle in order to move the sealing element from the storage setting into the sealing setting. An inlet opening of the fluid channel is formed on a pressure-side surface of the blade leaf. A housing as well as a gas turbine having at least one guide blade is also disclosed.

Disclosed is a fairing element intended to be placed in a passage for flow of a fluid, in order to surround an obstacle which crosses the passage so that the fairing element guides the flow of the fluid on two opposite sides of the obstacle. The fairing element is designed such that the pressure of the flowing fluid is constant or approximately constant in an upstream part of the suction surface of the fairing element. A fairing element of this kind can be incorporated into a stator of a turbomachine, in particular of an aircraft turbomachine.

A turbine engine assembly including an air flow guide assembly, including at least one guide vane and at least one structural arm, the vane and arm extending radially about an axis. The arm includes an upstream end portion having a guide vane profile and including a leading edge aligned with that of the vane; a downstream portion; and an intermediate portion including an upper surface extending between an upstream end point and a downstream end point. The upstream end point is separated from the leading edge of the arm by an axial distance of between 0.2c and 0.5c, c being the length of the axial chord of the vane, and the angle of the tangent to the upper surface at the upstream end point is equal to that at the downstream end point 1 degree.

A gas turbine engine includes a blade having a tip, a blade outer air seal operatively connected to a case assembly, and an active clearance control system disposed on the case assembly. The active control system includes an actuator assembly. The actuator assembly includes a motor assembly and a shaft. The shaft has a shaft body that extends between a first end that is operatively connected to the motor assembly and a second end that is operatively connected to the blade outer air seal.

A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots includes a major axis oriented perpendicular to a centerline of the liner assembly.

The invention relates to a turbine engine air flow guide assembly including: a structural arm (30); and a guide vane (21) on the lower surface of the structural arm, comprising a leading edge (22), a trailing edge (23), and a camber line (24), said vane and arm extending radially about an axis (X-X) of the turbine engine and defining therebetween an air flow channel. The structural arm (30) comprises: an upstream end (31) having a guide vane profile (21) and comprising a leading edge (32) aligned with that of the vane; and a shoulder (35) located on the lower surface of the arm, defining a neck in the channel. The assembly is characterised in that the area (A.sub.neck) of the section of the channel at the neck is between 0.7 and 0.9 times the area (A.sub.inlet) of the section of the channel at the leading edges.

A method for installing a probe assembly in a case of a gas turbine engine is disclosed. The method may include installing a first portion of the probe assembly within a first section of the case, and installing a second portion of the probe assembly within a second section of the case. A case assembly within a gas turbine engine is also disclosed. The case assembly may include a case in at least one of a compressor and a turbine, and a probe assembly. The probe assembly may include a first portion positioned within a bore of the case, and a second portion positioned within an inset of the case, the bore having a smaller diameter than the inset.