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EP-4462061-B1 - MODULAR HEAT EXCHANGER FOR AN AIRCRAFT POWERPLANT

EP4462061B1EP 4462061 B1EP4462061 B1EP 4462061B1EP-4462061-B1

Inventors

  • SNYDER, JACOB C.

Dates

Publication Date
20260506
Application Date
20240312

Claims (14)

  1. An apparatus for an aircraft powerplant, comprising: a heat exchanger (20) including a frame (22), a plurality of heat exchanger cores (24), a first flowpath (96) and a second flowpath (98); the frame (22) extending circumferentially about an axis (26), and the frame (22) comprising a plurality of receptacles (48) within an interior of the frame (22); each of the plurality of heat exchanger cores (24) housed within a respective one of the plurality of receptacles (48); the first flowpath (96) extending in a first direction across the heat exchanger (20) and through the plurality of heat exchanger cores (24); and the second flowpath (98) extending in a second direction across the heat exchanger (20) and through the plurality of heat exchanger cores (24), characterized in that a first of the plurality of heat exchanger cores (24) is configured to move, while housed within a first of the plurality of receptacles (48), at least one of axially relative to the frame (22); radially relative to the frame (22); or laterally relative to the frame (22).
  2. The apparatus of claim 1, wherein the first of the plurality of heat exchanger cores (24) is moveably secured to the frame (22) while housed within a first of the plurality of receptacles (48).
  3. The apparatus of claim 1 or 2, wherein the first of the plurality of heat exchanger cores (24) extends between opposing sides (60, 62); the first of the plurality of heat exchanger cores (24) is fixedly secured to the frame (22) at a first of the opposing sides (62); and the first of the plurality of heat exchanger cores (24) is moveable relative to the frame (22) at a second of the opposing sides (60).
  4. The apparatus of any preceding claim, wherein the frame (22) forms an exoskeleton around the plurality of heat exchanger cores (24).
  5. The apparatus of any preceding claim, wherein the frame (22) is configured as a lattice framework.
  6. The apparatus of any preceding claim, wherein the frame (22) includes a plurality of elongated members (42) arranged to form edges of a hexahedral unit (46); and a first of the plurality of receptacles (48) is formed by and within the hexahedral unit (46).
  7. The apparatus of any of claims 1 to 5, wherein the frame (22) includes a plurality of lattice members (42) arranged to form a first hexahedral unit (46) and a second hexahedral unit (46), the first hexahedral unit (46) next to the second hexahedral unit (46), and the first hexahedral unit (46) sharing one or more of the plurality of lattice members (42) with the second hexahedral unit (46); the first of the plurality of heat exchanger cores (24) arranged within the first hexahedral unit (46); and a second of the plurality of heat exchanger cores (24) arranged within the second hexahedral unit (46).
  8. The apparatus of claim 7, wherein the plurality of lattice members (42) are arranged to further form a third hexahedral unit (46); the first hexahedral unit (46) is between the second hexahedral unit (46) and the third hexahedral unit (46), and the first hexahedral unit (46) shares one or more of the plurality of lattice members (42) with the third hexahedral unit (46); a third of the plurality of heat exchanger cores (24) arranged within the third hexahedral unit (46).
  9. The apparatus of any preceding claim, wherein the frame (22) is configured as an arcuate body extending partially about the axis (26), optionally wherein a or the first of the plurality of heat exchanger cores (24) is circumferentially next to a second of the plurality of heat exchanger cores (24).
  10. The apparatus of any of claims 1 to 8, wherein the frame (22) is configured as a full-hoop body around the axis (26).
  11. The apparatus of any preceding claim, wherein a second of the plurality of heat exchanger cores (24) or a third of the plurality of heat exchanger cores (24) is axially next to a or the first of the plurality of heat exchanger cores (24).
  12. The apparatus of any preceding claim, wherein the heat exchanger (20) further includes a first seal element (86) disposed at a first side (28) of the first of the plurality of heat exchanger cores (24); and the first seal element (86) seals a first gap between the frame (22) and the first heat exchanger core (24), optionally wherein the first seal element (86) is compressed between the frame (22) and the first heat exchanger core (24).
  13. The apparatus of claim 12, wherein the heat exchanger (20) further includes a second seal element (88) disposed at a second side (30) of the first heat exchanger core (24) that is opposite the first side (28) of the first heat exchanger core (24); and the second seal element (88) seals a second gap between the frame (22) and the first heat exchanger core (24).
  14. The apparatus of any preceding claim, wherein the first direction is an axial direction and the second direction is a radial direction; and/or the apparatus further comprises an engine (100) comprising an engine flowpath (132, 134) and the first flowpath (96) is fluidly coupled with or configured as part of the engine flowpath (132, 134).

Description

TECHNICAL FIELD This disclosure relates generally to an aircraft powerplant and, more particularly, to a heat exchanger for the aircraft powerplant. BACKGROUND An aircraft powerplant such as a gas turbine engine may include one or more heat exchangers to transfer heat energy between fluids. As fluid cooling and/or heating needs increase, sizes of the heat exchangers also increase. Incorporating large heat exchangers within a gas turbine engine, however, can be challenging both for assembly / disassembly as well as for withstanding thermally induced stresses. Manufacturing large heat exchangers may also be challenging. There is a need in the art therefore for an improved heat exchanger. US 2009/031695 A1 discloses prior art methods and apparatus for mixing fluid in turbine engines. US 2,792,200 A discloses a prior art toroidal type heat exchanger. US 2022/282670 A1 discloses a prior art three-stream engine having a heat exchanger. SUMMARY OF THE DISCLOSURE According to an aspect of the present disclosure, there is provided an apparatus for an aircraft powerplant as set forth in claim 1. Further embodiments are provided as set forth in claims 2 to 14. The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a perspective illustration of a modular heat exchanger.FIG. 2 is a schematic illustration of the heat exchanger with a full-hoop body.FIG. 3 is a perspective illustration of a frame for the heat exchanger.FIG. 4 is a perspective illustration of a heat exchanger core for the heat exchanger.FIG. 5 is a schematic illustration of an axial side of the heat exchanger core.FIG. 6 is a schematic illustration of a lateral side of the heat exchanger core.FIG. 7 is a partial schematic illustration of the heat exchanger core housed within the frame.FIG. 8 is a schematic illustration of an axial side of the heat exchanger core housed within the frame.FIG. 9 is a partial schematic illustration of the heat exchanger core housed within the frame and retained by one or more retainers.FIG. 10 is a partial schematic illustration of the heat exchanger core housed within the frame and retained by a mount.FIG. 11 is a perspective illustration of the heat exchanger with one or more axial arrays of the heat exchanger cores.FIG. 12 is a partial schematic illustration of a gas turbine engine. DETAILED DESCRIPTION FIG. 1 illustrates a modular heat exchanger 20 for a powerplant of an aircraft. The aircraft may be an airplane, a drone (e.g., an unmanned aerial vehicle (UAV)) or any other manned or unmanned aerial vehicle or system. The aircraft powerplant may be configured as, or otherwise included as part of, a propulsion system for the aircraft. The aircraft powerplant may also or alternatively be configured as, or otherwise included as part of, an electrical power system for the aircraft. The heat exchanger 20 of FIG. 1 includes a heat exchanger (HX) frame 22 and one or more heat exchanger (HX) cores 24. The heat exchanger 20 and its HX frame 22 extend axially along an axis 26 from an axial first side 28 of the heat exchanger 20 to an axial second side 30 of the heat exchanger 20. The axis 26 may be a centerline axis of the aircraft powerplant and/or a rotational axis of one or more rotors included in the aircraft powerplant. The heat exchanger 20 and its HX frame 22 extend radially (in an outward direction away from the axis 26) from a radial inner side 32 of the heat exchanger 20 to a radial outer side 34 of the heat exchanger 20. The heat exchanger 20 of FIG. 1 and its HX frame 22 extend a number of degrees circumferentially about the axis 26 between and to opposing circumferential sides 36 and 38 of the heat exchanger 20, defining an angle 40 between the HX circumferential sides relative to the axis 26. This angle 40 is between one-hundred degrees (100°) and one-hundred and forty degrees (140°); e.g., one-hundred and twenty degrees (120°). However, in other embodiments, the angle may be less than one-hundred degrees (e.g., between 30° and 90°) or greater than one-hundred and forty degrees (e.g., between 160° and 180°). With such an arrangement, the heat exchanger 20 and its HX frame 22 may each have an arcuate geometry. Examples of this arcuate geometry include, but are not limited to, a partial frustoconical geometry or a partial cylindrical geometry. The present disclosure, however, is not limited to such exemplary arcuate geometries. Moreover, referring to FIG. 2, the heat exchanger 20 and its HX frame 22 (schematically shown) may alternatively extend circumferentially completely around the axis 26 providing the heat exchanger 20 and its HX frame 22 with a full-hoop (e.g., annular) geometry. The HX frame 22 may be configured to form an exoskeleton (e.g., a rigid, exterior framework) around the HX cores 24 collectively. The HX frame 22 may also be configured to form an exoskeleton around