The present invention is a turbine blade (1) having a hollow blade body (2). This turbine blade (1) is provided with: cooling air holes (5) that penetrate the blade body (2) from an internal wall surface (2e) to an external wall surface (2f) thereof, and are provided with a straight tube portion (5a) that is located on the internal wall surface (2e) side of the blade body (2), and an expanded diameter portion (5b) that is located on the external wall surface (2f) side of the blade body (2); and with a guide groove (6) that is located on an internal wall of the expanded diameter portion (5b) and that guides cooling air (Y) in the expanded diameter portion (5).

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.

Described is 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, in which the seal member further includes a plurality of flow passages extending from an outboard side to an inboard side.

A turbine vane of a turbine engine is described. The turbine vane includes a blade and a root. The root includes a stilt having lateral flanks with a curvilinear profile. The stilt includes a frangible zone suitable for undergoing a breakage of the stilt if radial forces higher than a threshold are exerted on the vane, in particular centrifugal forces during an overspeed state of the turbine. The frangible zone includes at least one oblong frangibility recess formed on at least one of the lateral flanks of the stilt, the oblong recess extending in an axial direction of the stilt along a longitudinal axis parallel to or included in a minimum cross-sectional plane which contains a minimum cross-section of the stilt.

A support system for an airfoil piece in a gas turbine engine includes first and second support platforms for supporting the airfoil piece there between. Each of the support platforms defines a forward support platform side, an aft support platform side, a first support platform circumferential side, a second support platform circumferential side, an airfoil side, and a non-airfoil side. The airfoil side of at least one of the support platforms has a radial channel therein for receiving a complementary radial flange of the airfoil piece. Each radial channel includes a radial channel first leg portion extending adjacent the aft support platform side, a radial channel second leg portion that extends from the radial channel first leg portion and that curves toward the forward support platform side, and a radial channel third leg portion that extends from the second leg portion toward the forward support platform side.

A turbine of a turbomachine includes a ceramic matrix composite sector of a stator includes an outer platform and an inner platform connected via at least one vane. The outer platform has means for attaching to a sector of a metallic support, the attachment means having at least one central rim and two lateral rims. The central rim is radially offset with respect to said lateral rims along a directrix line such that the central rim is radially on one side of said directrix line and the lateral rims on the other. The central rim and said central hook bear radially against one another and are located radially on either side of said directrix line. The lateral rim and said corresponding lateral hook bear radially against one another and are located radially on either side of said directrix line.

A turbine ring assembly includes ring segments forming a turbine ring and a ring support structure, each segment having a part forming an annular base with, in the radial direction, an inner face and an outer face from which project a first and a second hooking tab, the structure including a shroud from which project a first and a second radial flange between which are retained the first and second tabs, a first annular flange made of one part and a second annular flange disposed upstream of the ring. The first flange includes an annular shoulder and the second flange includes an annular recess forming an axial stop cooperating with the shoulder.

Disclosed are a centrifugal fan blade assembly and a centrifugal fan, comprising a plurality of blades, a blade leading edge of at least some of the blades being provided with an interference groove, the interference groove extending in a width direction of the blade. By providing the interference groove extending in the width direction of the blade on the blade leading edge, when the fan blade assembly is running, the interference groove changes noise frequency, thereby preventing the blade leading edge from producing a relatively large broadband noise after being impacted by a high speed air flow, thus effectively reducing noise.

An airfoil including a spar and a cover sheet that are configured for cooling. The spar includes standoffs and a leading edge wall. The standoffs are disposed along a pressure and/or suction side. A pressure-side panel and a suction-side panel are coupled to the standoffs and/or the leading edge wall. Leading ends of the pressure-side panel and the suction-side panel are disposed adjacent to one another proximate to the leading edge. The standoffs extend beyond the pressure-side leading end toward the leading edge wall. At least one of the leading ends of the pressure-side and suction-side panels defines a notch to form an outlet port at the leading edge. Standoffs may be disposed to define grooves in between in communication with the outlet port.

A seal assembly for a turbomachine. The turbomachine includes a rotating shaft extending along a centerline and a fixed housing positioned exterior to the rotating shaft in a radial direction relative to the centerline. The seal assembly includes a sump housing at least partially defining a bearing compartment for holding a cooling lubricant. The seal assembly further includes a bearing supporting the rotating shaft. In addition, the seal assembly also includes a sump seal at least partially defining the bearing compartment. A pressurized housing of the seal assembly is positioned exterior to the sump housing and defines a pressurized compartment to at least partially enclose the sump housing. Further, a non-contacting carbon seal is positioned between the rotating shaft and the fixed housing to at least partially define the pressurized compartment to enclose the sump housing.