High cycle fatigue (HCF) in a turbine wheel of a sector-divided dual volute turbocharger, particularly a turbocharger where the tongue-to-blade gap is as small as from 1-3% of the wheel diameter, is reduced, and energy extraction is optimized, using a turbine wheel with (blade stiffness/backwall stiffness×100) between 41 and 44.

A rotating machine system can include a rotating machine. The rotating machine system can include a housing. The housing can include an inner surface. The housing can surround at least a portion of the rotating machine. The inner surface of the housing can be spaced from the rotating machine such that a space is defined therebetween. The rotating machine system can include one or more super elastic wires. The one or more super elastic wires can be positioned in the space and can be operatively connected to the rotating machine and the inner surface of the housing. The one or more super elastic wires can reduce vibration within the rotating machine system.

A gas turbine engine, has: an annular gaspath extending around a central axis, the annular gaspath defined between a first casing and a second casing, the first casing defining pockets; and a variable guide vane assembly having: variable guide vanes circumferentially distributed around the central axis, the variable guide vanes having airfoils extending into the annular gaspath and extending between first and second pivot members at respective first and second ends of the airfoils, the variable guide vanes rotatable about respective spanwise axes, bushings received within the pockets of the first casing, the first pivot members of the variable guide vanes rollingly engaged to the bushings, and resilient members disposed radially between surfaces of the first casing and the bushings relative to the spanwise axes, the resilient members in abutment against both of the surfaces of the first casing and the bushings.

Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.

An engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades; and a gearbox. The gearbox is an epicyclic gearbox and comprises a sun gear, a plurality of planet gears, a ring gear, and a planet carrier on which the planet gears are mounted. The radial bending stiffness of the planet carrier is equal to or greater than 1.20×10.sup.9 N/m, and/or the tilt stiffness of the planet carrier is greater than or equal to 6.00×10.sup.8 Nm/rad. A method of operation of such an engine is also disclosed.

A compressor rotor for turbomachinery, such as a compressor, is provided. Disclosed embodiments can benefit from seal elements that may be arranged to inhibit passage onto respective hirth couplings of process fluid being processed by the compressor. A seal element may be affixed to adjacent rotor components (e.g., adjacent impeller bodies) by way of a slip or interference fit connection to one of the adjacent components and may be affixed to the other adjacent rotor component by way of a elastically flexible frustoconical inner surface of the seal element that permits the seal element to be placed in a spring-loaded condition, which generates a biasing force to circumferentially clamp onto a frustoconical outer surface of the other adjacent rotor component. This arrangement is conducive to user-friendly assembly/disassembly of the seal elements with respect to the adjacent rotor components.

Auxetic structures, effusion-cooling auxetic sheets, systems and devices with auxetic structures, and methods of using and methods of making auxetic structures are disclosed. An auxetic structure is disclosed which includes an elastically rigid body with opposing top and bottom surfaces. First and second pluralities of elongated apertures extend through the elastically rigid body from the top surface to the bottom surface. The first plurality of elongated apertures extends transversely with respect to the second plurality of elongated apertures. The first and/or second pluralities of elongated apertures have distorted shapes projected through the elastically rigid body at an oblique angle. The elongated apertures are cooperatively configured to provide a desired stress performance while exhibiting negative Poisson's Ratio (NPR) behavior under macroscopic planar loading conditions. By way of example, the auxetic structure may exhibit a reduction in stress concentration proximate the elongated apertures and a Poisson's Ratio of approximately −0.0001 to −0.9%.

A bladed disc for a rotating machine comprising a central disc that rotates about a central axis, the central disc having a series of blades arranged around its periphery; the blades have dovetail roots which engage with slots on the central disc; the bladed disc being configured so that there is a pre-loading force between the blades and the central disc such that each blade is forced away from the central axis of the bladed disc; and wherein the pre-loading force is equal or greater than 40% of the maximum centrifugal force applied to the blade during a flight cycle.

Provided is a vibration reduction device for stator vanes (30) positioned behind rotor blades (28) in a turbo machine, comprising an annular base member (80) having a cylindrical shape concentric around a central axis of the casing and supporting base ends of the stator vanes which extend radially inward from an inner circumferential surface of the base member, an elastomeric damping member (100) surrounding and in slidable contact with an outer circumferential surface of the base member, and a preloading member (102) surrounding an outer circumferential surface of the elastomeric damping member and configured to apply a preload directed radially inward to the elastomeric damping member.

The invention relates to a fluid pump, in particular to a liquid pump having a rotor with at last one rotor blade for conveying the fluid, the rotor being variable with respect to its diameter between a first, compressed state and a second expanded state. In order to produce a simple compressibility and expandability of the rotor of the pump, it is provided according to the invention that at least one rotor blade is deformable between a first state which it assumes in the compressed state of the rotor and a second state which it assumes in the expanded state of the rotor by means of a fluid counterpressure during a rotation of the rotor during pump operation.