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 first opening, which passes through the blade surface part from a negative pressure side toward a positive pressure side, is provided between the first blade element and the second blade element on the blade surface part. A space between an outer edge of the first blade element extended from the side surface toward an outer edge side of the blade, and an outer edge of the second blade element extended from the side surface toward the outer edge side of the blade on the positive pressure surface side, is opened from the side surface in a radial direction of the blade surface part, so that an air current coming from the negative pressure side toward the positive pressure side through the first opening, flows from the first opening toward the outer edge side of the blade along the positive pressure surface.

A propeller fan includes a hub and a plurality of blades, wherein the blade has a plurality of blade elements branching on a way from an outer peripheral portion to an inner peripheral portion, the plurality of blade elements form a hole which is a flow path for airflow, between the adjacent blade elements, have a first blade element on an upstream side and a second blade element on a downstream side to be adjacent to the first blade element which branch at a branch point, and include an extension portion as a part of the first blade element, on a trailing edge of the first blade element from the branch point to a side surface of the hub, and at least a part of a leading edge of the second blade element overlaps with a rotation orbit of the extension portion with a central axis as a rotation center.

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.

A first opening, which passes through the blade surface part from a negative pressure side toward a positive pressure side, is provided between the first blade element and the second blade element on the blade surface part. A space between an outer edge of the first blade element extended from the side surface toward an outer edge side of the blade, and an outer edge of the second blade element extended from the side surface toward the outer edge side of the blade on the positive pressure surface side, is opened from the side surface in a radial direction of the blade surface part, so that an air current coming from the negative pressure side toward the positive pressure side through the first opening, flows from the first opening toward the outer edge side of the blade along the positive pressure surface.

On the blade surface part, a first opening passing through the blade surface part from a negative pressure side toward a positive pressure side is provided between the first blade element and the second blade element. A chord length of the first blade element along a direction connecting the apex A with the point B, is equal to or larger than a chord length of the second blade element along a direction connecting an apex C with a point D.

An inner peripheral blade projects from the positive pressure surface of the blade surface part toward a positive pressure side, includes a front edge in a rotation direction of the inner peripheral blade that is formed in a curved shape to be separated from a reference line toward the front edge side in the rotation direction of the blade, the reference line connecting a lower end positioned on the positive pressure surface at a base end of the inner peripheral blade connected to the side surface of the hub with an outer edge of the inner peripheral blade that is extended from the side surface toward an outer edge side of the blade and positioned on the positive pressure surface, and satisfies H/L≥0.1, where L is a length of the reference line and H is a maximum value of a distance between the reference line and the front edge of the inner peripheral blade.

On the blade surface part, a first opening passing through the blade surface part from a negative pressure side toward a positive pressure side is provided between the first blade element and the second blade element. A chord length of the first blade element along a direction connecting the apex A with the point B, is equal to or larger than a chord length of the second blade element along a direction connecting an apex C with a point D.

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 (10), in particular of a radial compressor or diagonal compressor, having an annular stabilizer chamber (12) which encloses a main flow channel (13) in the intake region of a compressor wheel (21) and is delimited from the main flow channel (13) by an annular bridge (14). The annular stabilizer channel (12) is connected to the main flow channel (13) via a downstream flow inlet (15) and an upstream flow outlet (16). At least one separating element (T) is arranged in at least one of the flow inlet (15) and the flow outlet (16), with the result that an inflow into the annular stabilizer chamber (12) and/or an outflow out of the annular stabilizer chamber (12) are/is split transversely with respect to the main flow direction (1) of the main flow channel (13). Furthermore, at least one flow guiding element (17) is arranged in at least one of the flow inlet (15) and the flow outlet (16). 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 turbomachine, in particular a turbocharger, comprising the compressor.