Dual air source bearing assembly housing for an aircraft propulsion system

An engine for an aircraft propulsion system, the engine comprising:

• a compressor section including a first air source and a second air source;
• a turbine section;
• a rotational assembly including a bladed compressor rotor for the compressor section, a bladed turbine rotor for the turbine section, and a shaft interconnecting the bladed compressor rotor and the bladed turbine rotor, and the rotational assembly is rotatable about a rotational axis;
• and
• a bearing assembly including a bearing compartment housing and at least one bearing, the bearing compartment housing surrounds and forms a bearing compartment, the bearing compartment housing includes a housing body, the housing body extends circumferentially about the rotational axis, the housing body extends axially between and to a first axial housing end and a second axial housing end, the housing body forms a first air flow path and a second air flow path through the bearing compartment housing,
• the first air flow path extending through the housing body from a first inlet plenum of the first air flow path to a first outlet plenum of the first air flow path, and the first air flow path is connected in fluid communication with and between the first air source and the turbine section, and
• the second air flow path extending through the housing body from a second inlet plenum of the second air flow path to a second outlet plenum of the second air flow path, the second air flow path is connected in fluid communication with and between the second air source and the bearing compartment, and the first air flow path is independent of the second air flow path through the bearing compartment housing, and
• the at least one bearing is mounted to the housing body and disposed within the bearing compartment, and the at least one bearing is rotationally engaged with the shaft;
• wherein the first air flow path is connected in fluid communication with the first air source at a first position of the compressor section to receive a first compressed bleed air, and the second air flow path is connected in fluid communication with the second air source at a second position of the compressor section, upstream of the first position, to receive a second compressed bleed air;
• and
• wherein the first compressed bleed air has a greater pressure than the second compressed bleed air.

An engine for an aircraft propulsion system, the engine comprising:

• a rotational assembly including a shaft, and the shaft is rotatable about a rotational axis;
• and
• a bearing assembly including a bearing compartment housing, at least one bearing, a first bearing seal, and a second bearing seal,
• the bearing compartment housing surrounds and forms a bearing compartment, the bearing compartment housing includes a housing body, the housing body extends circumferentially about the rotational axis, the housing body extends axially between and to a first axial housing end and a second axial housing end, the housing body extends radially between and to an inner radial end and an outer radial end, the housing body includes a plurality of first feed holes forming a first air flow path through the bearing compartment housing and a plurality of second feed holes forming a second air flow path through the bearing compartment housing,
• the first air flow path extending through the housing body from a first inlet plenum of the first air flow path to a first outlet plenum of the first air flow path, the plurality of first feed holes being axially between the first inlet plenum and the first outlet plenum, and the first air flow path connected in fluid communication with a first air source, and
• the second air flow path extending through the housing body from a second inlet plenum of the second air flow path to a second outlet plenum of the second air flow path, the second air flow path is disposed radially between the first air flow path and the bearing compartment from the second inlet plenum to the second outlet plenum, the plurality of second feed holes being axially between the second inlet plenum and the second outlet plenum, and the second air flow path connected in fluid communication with a second air source,
• the at least one bearing is mounted to the housing body and disposed within the bearing compartment, and the at least one bearing is rotationally engaged with the shaft,
• the first bearing seal is disposed at the first axial housing end, and the first bearing seal further forms the second air flow path and the bearing compartment,
• the second bearing seal is disposed at the second axial housing end, and the first bearing seal further forms the second air flow path and the bearing compartment, and
• the plurality of first feed holes and the plurality of second feed holes are parallel to each other, and the first outlet plenum and the second outlet plenum are parallel to each other.