Abstract: In the case of saddle-type rotor blades of axial-flow turbomachines, the locking blade (6a), without its root part engaging in the fir trees (2) on the radially outer part of the rotor disk (1), is located under a large prestress between its neighboring blades (6b, 6c). It is fastened in the root part by means of axial pins (7). The blade root (4') of the locking blade (6a) is dimensioned more narrowly in the region of its fir trees (2') in its axial extension than that (4) of the neighboring blades (6b, 6c). By this means, a removal recess (10) is produced on both the inlet and outlet sides, in each of which a compression jack (11) can be introduced for pressing apart the neighboring blades (6b, 6c). The locking blade, relieved of loads in this manner, can be removed without being destroyed.

Abstract: An axial flow rotor disc apparatus of the radial blade entry type wherein bifurcated roots of the blades engage opposite sides of a circumferential rib member of the disc has shims or root liners between at least some of the blades for adjusting the blade spacing to match the circumference of the disc. The root liners are split into pairs for separate insertion from opposite sides of the rib member at convenient locations around the periphery of the disc, without requiring insertion at an entry slot for the blades. In one version of the apparatus, the liners are retained against the rib member by deforming corners of the roots circumferentially over the liners. In another version, the liners have dogs that engage cavities in the adjacent root. The liners can also be joined along an interlocking split line for holding each pair together.

Abstract: A fan apparatus including a fan spider having a hub portion and a plurality of outwardly extending arms, a plurality of fan blade assemblies, each fan blade assembly having a molded plastic blade with an attachment insert partially embedded within, the exposed portion of each attachment insert being rigidly attached to a corresponding one of the arms of the spider.

Abstract: In an axial flow compressor rotor stage having a blade mount rail about the eriphery thereof, a seal is positioned below the blade platforms to provide improved compressor gas path efficiency. Each blade platform has a seal bonded to the underside thereof, said seals extending toward adjacent blade platforms and providing sealing means in the interstices between said platforms as well as between said platforms and said blade mount rail.

Abstract: A multiple number of rotatable, axial flow turbine blades having a common platform and shroud portion from which two arcuately separated, axially extending, side entry roots protrude radially inwardly toward the axis of rotation of a rotatable shaft.

Abstract: A gas turbine engine has a turbine vane case, an outer combustion case and inner vane case along with an air seal located in circumferential surrounding relationship to a circumferential row of stator vanes defining a turbine nozzle assembly upstream of a high pressure turbine stage. Individual stator vanes can be replaced without removing the high pressure turbine stage by configuring an index vane to be removably secured to an inner support band by means of a spring loaded pin and configuring each of the remaining vanes in the vane row to have a side slotted base secured to the inner band and removable therefrom by rotation of each of the individual vanes in a direction opposite to the tangential gas load thereon.

Abstract: The disclosure of this invention pertains to a bladed rotor for gas turbine engines wherein each blade has a root portion connected to a blade support element spaced radially outwardly from the rim of a single disc and being of greater axial extent than the rim. The element is connected to the rim by a web extending in part radially outside the rim and in part at the sides of the rim.