The invention relates to a nubomachine with a longitudinal axis, comprising two, respectively upstream (122) and downstream, coaxial outer propellers (122), characterised in that at least some of the blades (148) of the upstream propeller (122) comprise at least one internal air circulation chimney (150) that communicates with air-bleeding openings (152) in tire boundary layers of the blades (148), and communicates with air outflow openings (158) on the radially outer end thereof, the air-bleeding openings (152) leading to opening inlets (152a) on tire passive surfaces (156) of the blades (148), the inlets (152a) of the air-bleeding openings being radially arranged in an area (H1) contained between 10% and 45% of the radial dimension (H2) of the blades (148), measured above turd from the radial height of the blades for which the tangent of the leading edge (138) of the blades is orthogonal to the longitudinal axis, and the inlets (152a) of the air bleeding openings being arranged in an area contained between 0% and 30% of the local chord of the blades (148), measured at the level of said inlets (152a) and from the leading edges (138) of tire blades (148).

A propeller fan includes a hub that has a side surface around a central axis, and blades that are provided on the side surface, wherein a blade of the blades includes an inner peripheral portion located on a side of a base, and an outer peripheral portion located on a side of an outer edge, the outer peripheral portion is formed as one blade, the inner peripheral portion includes blade elements arranged at a predetermined interval, a ratio r/R of a radius r which is a distance from the central axis to the outer peripheral portion and a radius R which is a distance from the central axis to the outer edge is 0.4 or less, and when a wind speed at the outer peripheral portion is V1 and a wind speed at the inner peripheral portion is V2, a relational formula of V1≤V2×2.0 is established.

A ceiling fan may include a shaft coupled to a ceiling, a cover to surround the shaft, a main blade having a blade hole which is a space open inward, and a sub-blade positioned in the blade hole. The sub-blade is disposed to have an angle of attack different from an angle of attack of the main blade. The ceiling fan may resolve a red zone of the air flow and may improve air volume and the flow rate due to the dual blades.

In a turbocharged internal combustion engine (ICE) system, a catalytic treatment device receives exhaust gases from the ICE after they have passed through the turbocharger turbine. The system includes a secondary air pump (SAP) for injecting pressurized air into the exhaust gases ahead of the catalytic treatment device. The SAP is a single-stage centrifugal compressor that includes an air recirculation passage for causing a first portion of the air pressurized by the SAP to be continuously recirculated back to the inlet of the SAP, which is effective for heating the air in the volute of the SAP. A second portion of the pressurized air, having thereby been heated, is injected into the exhaust gases proceeding toward the catalytic treatment device.

There is disclosed a fan assembly including a fan rotor including a hub and fan blades. The fan blades have a leading edge and a trailing edge. A fan stator downstream of the fan rotor relative to a direction of an airflow through the fan assembly. The fan stator includes vanes extending between radially inner ends and radially outer ends. A flow recirculation circuit has an inlet downstream of the vanes of the fan stator and an outlet upstream of the vanes. A recirculation rotor has a plurality of airfoils circumferentially distributed around the axis and located in the flow recirculation circuit. The recirculation rotor is rotatable about the axis within the recirculation circuit. A method of operating the fan assembly is also disclosed.

A compressor bleed port apparatus includes: a compressor shroud which defines a boundary between a primary flowpath and a plenum; a bleed port including one or more apertures passing through the compressor shroud, each of the one or more apertures having an inlet communicating with the primary flowpath and an outlet communicating with the plenum, and extending along a respective centerline. Each of the one or more apertures is bounded by sidewalls, and includes a diffuser section in which the sidewalls diverge from each other in a downstream direction; A diffusing angle between the sidewalls varies over the length of the diffuser section.

A compressor section for a gas turbine engine according to an example of the present disclosure includes, among other things, a low pressure compressor including a plurality of rotor blades arranged about an axis, a high pressure compressor, and a core flowpath passing through the low pressure compressor. The core flowpath at the low pressure compressor defines an inner diameter and an outer diameter relative to the axis. The outer diameter has a slope angle relative to the axis.

A bleed plenum for a compressor section associated with a gas turbine engine includes a plenum chamber having a first wall spaced apart from a second wall to define a plenum slot configured to receive a flow of fluid from the compressor section. A slot angle of the plenum slot is defined between a centerline of the plenum slot and a longitudinal axis of the gas turbine engine and varies about a circumference of the bleed plenum. The second wall includes a bullnose having a wedge angle defined between the second wall and a surface associated with the compressor section. The bullnose faces into the flow of fluid through the plenum slot, and the wedge angle of the bullnose varies about the circumference of the bleed plenum.

The invention relates to a stabilizer channel, in particular of a radial compressor or diagonal compressor, having an annular stabilizer chamber which encloses a main flow channel in the intake region of a compressor wheel and is delimited from the main flow channel by an annular bridge. The annular stabilizer chamber is bladeless and is connected to the main flow channel via a downstream inlet channel and an upstream outlet channel. A plurality of flow directing elements are arranged in the downstream inlet channel. The downstream inlet channel is arranged between an upstream part of the annular bridge and a downstream part of the annular bridge. The invention furthermore relates to a compressor, in particular a radial compressor or diagonal compressor, comprising the stabilizer channel according to the invention and to a turbocharger comprising the compressor.

When an apex of a first blade element projecting from the positive pressure surface is A, a distance from the center axis to the apex A is r, and a point having the distance r from the center axis on a front edge in the rotation direction of the first blade element is B, the first blade element among the blade elements that is arranged on a front edge side in the rotation direction of the blade, is formed to have a blade angle equal to or larger than a predetermined first angle and equal to or smaller than a second angle that is larger than the first angle, the blade angle being formed by a direction along a chord of the first blade element along a direction that connects the apex A with the point B, and a plane orthogonal to the center axis.