An integrated bladed rotor of a gas turbine engine is provided. The integrated bladed rotor includes a hub having a rotation axis and a radially outer platform relative to the rotation axis, and a plurality of blades extending radially outwardly from the outer platform of the hub. The blades are integrally formed with the hub to define a monolithic component with the hub. Two or more of the blades each include: an airfoil including a groove formed in an outer surface of the airfoil to mitigate crack propagation, and a root fillet providing a transition between the outer platform of the hub and the airfoil.

A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

A coupling device for rotably coupling a shaft with a gearbox in a geared turbo fan aircraft engine, wherein the coupling device includes a connection to the shaft at a first end and a connection to the gearbox at a second end, the first and the second ends being axially separated and at least one curved shape between the first end and the second end extending from the gearbox radially inwards to the shaft and the at least one curved shape including at least one cross-section in the axial direction of the engine with a logarithmic profile or a power profile.

A turbo compressor comprises a rotary shaft including a rotor; a first impeller coupled to one side of the rotary shaft, a thrust bearing runner coupled between the first impeller and the rotary shaft, an impeller sleeve compressed and coupled between the first impeller and the thrust bearing runner, a second impeller coupled to the other side of the rotary shaft, and a tie rod passing through the first impeller and a thrust bearing and fastened to the rotary shaft.

An impeller for a centrifugal compressor, the impeller rotatable about a central axis, has: an outer hub body including a first material and extending around the central axis, the outer hub body defining a gaspath face extending from an inlet to an outlet, the gaspath face extending radially away from the central axis from the inlet to the outlet; blades protruding from the gaspath face and circumferentially distributed around the central axis; and an inner hub body extending around the central axis, the inner hub body secured to the outer hub body, the outer hub body axially overlapping and extending around the inner hub body, the inner hub body made of a second material being more cold dwell resistant than the first material.

An air turbine starter comprising a housing defining an inlet, an outlet, and a flow path, a turbine having a rotor with circumferentially spaced blades extending into the flow path, a drive shaft operably coupled to and rotating with the rotor, and at least one vane located within the flow path, upstream of the blades. The at least one blade being defined by an acute axial angle and an acute tangential angle.

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 gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.

A process for treating a centrifugal compressor wheel includes a combination of cold expansion of at least part of the bore of the wheel to induce residual compressive stresses in a region around the bore, and surface peening at least parts of the compressor wheel such as the back disk and portions of the blades.

An improved system, apparatus and method for estimating thrust from an engine, and more specifically, a system for estimating thrust from strain gauge and accelerometer measurements. At least one strain gauge is mounted on an engine mount to measure strain to estimate a constant velocity or steady-state portion of thrust. At least one accelerometer is mounted on the vehicle to measure acceleration to estimate a transient portion of thrust. Steady-state thrust estimation and transient thrust estimation are combined to estimate thrust from the engine. An algorithm provides steps for estimating thrust from strain gauge and accelerometer measurements.