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.

A turbo compressor may include a motor casing having a motor space; a drive motor provided in the motor space; a rotary shaft coupled to the drive motor and configured to transmit a rotational force; an impeller coupled to a first side of the rotary shaft and configured to rotate together with a rotation of the rotary shaft; a thrust bearing runner coupled to a second side of the rotary shaft opposite to the first side and configured to rotate together with the rotation of the rotary shaft; a bearing casing to support the thrust bearing runner; an inlet flow path configured to guide fluid introduced into the impeller; a discharge flow path configured to guide fluid discharged from the impeller; and a cooling flow path branched from the discharge flow path and configured to guide the fluid to the bearing casing.

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.

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.

A electric motor assembly includes an electric motor and a fan assembly coupled to the electric motor and configured to rotate therewith about an axis. The fan assembly includes a hub including a core ring, a first inner ring circumscribing the core ring, and a first plurality of circumferentially-spaced ribs extending between the core ring and the first inner ring. The hub also includes a second inner ring circumscribing the first inner ring and a second plurality of circumferentially-spaced ribs extending between the first inner ring and the second inner ring, and a plurality of circumferentially-spaced blades coupled to an outer periphery of the hub.

A cooler fan module, having: a fan frame, a fan wheel recess formed in the fan frame, wherein the fan wheel recess is bounded by a frame ring, a motor mount, which is arranged within the fan wheel recess and is mechanically connected to the fan frame by means of struts, a motor, more particularly an electric motor, which is held at least partially in the motor mount, and a fan wheel, which is arranged in the fan wheel recess and is rotationally driven by the motor, wherein the cooler fan module further has a separately formed, annular structure element, which is arranged on the frame ring.

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 tunable compliant mount structure for an engine such as a turbine engine can include a fluid conduit coupled to a fan casing by a connector. At a junction between the connector and the fluid conduit, a compliant mount structure can provide compliance and can be tuned to operate under variable stresses at the junction. The compliant mount structure can include a set of nested convolutions to provide compliance. The geometry of the convolutions can be used to tune the compliance, stiffness, or directionality. The tunable compliant attachment structure provides for additive in-situ manufacturing at the fluid conduit.

A data processing method is proposed, including: sensing, via at least one sensing portion, target information of a target device; receiving and processing, via an electronic device, the target information of the sensing portion to form feature information; processing, via the electronic device, the feature information into a label matrix, and establishing, via an artificial intelligence training method, a target model based on the label matrix; and after the electronic device captures real-time information of the target device, predicting, via the target model, a life limit of the target device, wherein a content of the target information is corresponding to a content of the real-time information. Thus, a good target model is constituted and is advantageous in training artificial intelligence by processing the feature information into the label matrix.

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.