Modular heat exchanger for an aircraft powerplant
AssigneeRaytheon Technologies Corporation
InventorJacob C. Snyder
Life of this patent
Estimating the term…
Abstract
An apparatus is provided for an aircraft powerplant. This apparatus includes a heat exchanger. The heat exchanger includes a frame, a plurality of heat exchanger cores, a first flowpath and a second flowpath. The frame extends circumferentially about an axis. The frame includes a plurality of receptacles within an interior of the frame. Each of the heat exchanger cores is housed within a respective one of the receptacles. The first flowpath extends in a first direction across the heat exchanger and through the plurality of heat exchanger cores. The second flowpath extends in a second direction across the heat exchanger and through the plurality of heat exchanger cores.
Claims20
An apparatus for an aircraft powerplant, comprising:
- a heat exchanger including a frame, a plurality of heat exchanger cores, a first flowpath and a second flowpath;
- the frame extending circumferentially about an axis, and the frame comprising a plurality of receptacles within an interior of the frame;
- each of the plurality of heat exchanger cores housed within a respective one of the plurality of receptacles;
- the first flowpath extending in a first direction across the heat exchanger and through the plurality of heat exchanger cores;
- and
- the second flowpath extending in a second direction across the heat exchanger and through the plurality of heat exchanger cores.
An apparatus of an aircraft powerplant, comprising:
- a heat exchanger including a frame, a first heat exchanger core, a second heat exchanger core, a first flowpath and a second flowpath;
- the frame including a plurality of lattice members arranged to form a first hexahedral unit and a second hexahedral unit, the first hexahedral unit next to the second hexahedral unit, and the first hexahedral unit sharing one or more of the plurality of lattice members with the second hexahedral unit;
- the first heat exchanger core arranged within the first hexahedral unit;
- the second heat exchanger core arranged within the second hexahedral unit;
- the first flowpath extending across the first heat exchanger core and the second heat exchanger core;
- and
- the second flowpath extending across the first heat exchanger core and the second heat exchanger core.
An apparatus for an aircraft propulsion system, comprising:
- a heat exchanger including a frame, a first heat exchanger core, a second heat exchanger core, a first flowpath and a second flowpath;
- the frame extending circumferentially about an axis;
- the first heat exchanger core housed within and movably retained within the frame;
- the second heat exchanger core housed within and movably retained within the frame, and the second heat exchanger core next to and disengaged from the first heat exchanger core;
- the first flowpath extending across the first heat exchanger core and the second heat exchanger core;
- and
- the second flowpath extending across the first heat exchanger core and the second heat exchanger core.
Dependencies are inferred from the claim text.