A method for processing speech, comprising semantically parsing a received natural language speech input with respect to a plurality of predetermined command grammars in an automated speech processing system; determining if the parsed speech input unambiguously corresponds to a command and is sufficiently complete for reliable processing, then processing the command; if the speech input ambiguously corresponds to a single command or is not sufficiently complete for reliable processing, then prompting a user for further speech input to reduce ambiguity or increase completeness, in dependence on a relationship of previously received speech input and at least one command grammar of the plurality of predetermined command grammars, reparsing the further speech input in conjunction with previously parsed speech input, and iterating as necessary. The system also monitors abort, fail or cancel conditions in the speech input.

A blade retainer adapted for use in a gas turbine engine is configured to block axial movement of a blade. The blade retainer includes a first brace, a second brace, and a web that extends between the first brace and the second brace. The blade retainer is configured to block axial movement of a root of the blade out of a blade receiver slot.

A rotor of a gas turbine, having two adjacent rotor disks having a plurality of blade-holding grooves for receiving rotor blades, distributed around the periphery thereof, and having an axially extending peripheral ring projection radially beneath the blade-holding grooves. A peripheral rotor component is fixed to the ring projections, between the rotor disks. In order to protect the periphery, the rotor disk or the rotor component includes at least two recesses arranged on the periphery in a distributed manner, in each of which engaging shoulders of the rotor component or the rotor disk engage.

A rotor arrangement for a rotor of a gas turbine includes at least one rotor disk with attachment slots for carrying rotor blades and an annular groove having an annular opening towards the outward direction; and rotor blades having an airfoil and a blade root and assembled in an attachment slot. Each of the assembled blade roots have a root extension with a root groove. The root groove faces the annular groove when the rotor blade is assembled in the attachment slot. For each assembled rotor blade a locking element is provided, the locking element engaging the annular groove of the rotor disk and the root groove of the respective rotor blade. Preferably all locking elements are embodied as a locking sheet metal strip, which has two bended tongues embracing the respective root extension.

A structure for assembling turbine blade seals, which includes a turbine blade including an airfoil, a platform, and a root, a turbine rotor disk to which the root of the turbine blade is mounted, a seal plate mounted between the platform and one side of the turbine rotor disk to seal a cooling channel defined within the root and the platform, and an insertion pin inserted through the turbine rotor disk to fix the seal plate to the turbine rotor disk by supporting the seal plate, wherein the turbine rotor disk has a mounting groove into which a radially inner end of the seal plate is inserted, and the seal plate has a jaw portion radially supported by a stepped portion of the mounting groove.

A sealing element and a rotor of a gas turbine having at least one rotor disc and having an annular rotor component arranged adjacently to the rotor disc and having a plurality of sealing elements arranged distributed around the circumference. The sealing elements are fastened to the rotor disc at least in the axial direction. An inner edge portion of each of the sealing elements is adjacent to a sealing portion of the rotor component. In order to provide a seal between the sealing element and rotor component whilst at the same time enabling a relative axial displacement, a ring seal is arranged in a receiving space formed by the sealing element and rotor component.

A rotor for a gas turbine having a rotor disk on which there are a plurality of rotor components distributed around the circumference. The rotor disk has a circumferential securing shoulder with a contact face. Retaining faces come to bear against the contact face, each of the retaining faces have a retaining shoulder of the respective rotor component and are designed with a form that complements the contact face. In order to optimize the bearing stresses between the retaining shoulder and the securing shoulder, the retaining face has a smaller radius than the contact face, namely the retaining radius is at least 0.99 times and at most 0.995 times the contact radius. Also provided is an axially extending aperture in the rotor component, the width of which in the circumferential direction is 25% to 75% of the rotor component width in the circumferential direction.

A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.

A rotating machine includes a plurality of rotors. Each of the rotors includes a rotor bore protruding radially inward from a platform. A ring shaped cover plate is interfaced with each rotor bore via at least one snap. The at least one snap includes a first arm extending from the cover plate and having a convex facing contact surface, and multiple second arms extending axially from each rotor bore and having contact surfaces facing the convex surface.

A platform seal and damper assembly for turbomachinery (100), such as fluidized catalytic cracking (FCC) expanders or gas turbine engines; and methodologies for forming such assembly are provided. An axially-extending groove (160) is arranged on a side (162) of a respective platform. Groove (160) is defined by a radially-outward surface (168) at an underside of the platform and a surface (170) extending with a tangential component (T) toward radially-outward surface (168). A seal and damper member (152) is disposed in groove (160), where the body of seal and damper member has adjoining surfaces (190, 188) configured to respectively engage, in response to a camming action, with the surfaces (168, 170) that define the axially-extending groove. The camming action being effective to produce an interference fit of the seal and damper member (152) with the side of the respective platform (162) and an opposed side (163) of an adjacent platform.