Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Abstract: An aircraft engine has: a compressor section having a compressor rotor rotatable about a central axis; a diffuser downstream of the compressor rotor, the diffuser including a diffuser ring extending circumferentially around the central axis; a bearing housing secured to the diffuser ring, the bearing housing contained within a volume located radially inwardly of the diffuser ring; and an air manifold secured to the diffuser ring, the air manifold defining inlets in fluid flow communication with the compressor section and an outlet in fluid flow communication with the volume.

Abstract: A transfer tube assembly comprises a transfer tube slidably engaged in sealing engagement with a first component. The transfer tube has a shoulder engageable with a stopper for limiting relative axial movement between the transfer tube and the first component. The shoulder has an abutment surface facing a corresponding bore surface of the first bore of the first component. The abutment surface and the bore surface are configured to generate axially opposing reaction forces in response to the abutment surface and the bore surface contacting each other.

Abstract: A diffuser pipe includes a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a first direction from an inlet of the tubular body, a second portion extending in a second direction transverse to the first direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. A stiffening rib extends outwardly from an outer surface of the first portion of the tubular body.

Abstract: A transfer tube assembly comprises a transfer tube slidably engaged in sealing engagement with a first component. The transfer tube has a shoulder engageable with a stopper for limiting relative axial movement between the transfer tube and the first component. The shoulder has an abutment surface facing a corresponding bore surface of the first bore of the first component. The abutment surface and the bore surface are configured to generate axially opposing reaction forces in response to the abutment surface and the bore surface contacting each other.

Abstract: A diffuser pipe has a tubular body with a first portion extending from an inlet of the diffuser pipe, a second portion extending along a generally axial direction relative to a center axis, and a bend portion fluidly connecting the first and second portions. An exit segment of the second portion defines a pipe outlet. The exit segment is curved radially outwardly relative to the center axis. A compressor diffuser, a gas turbine engine, and a method of supplying air from a compressor section to a combustor of the gas turbine engine are also disclosed.

Abstract: A diffuser pipe includes a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a first direction from an inlet of the tubular body, a second portion extending in a second direction transverse to the first direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. A stiffening rib extends outwardly from an outer surface of the first portion of the tubular body.