Aircraft Heat Exchanger Finned Plate Manufacture

Abstract

A method for forming a heat exchanger plate includes: securing a wave form metallic sheet to a heat exchanger plate substrate, the substrate comprising a first face and a second face opposite the first face, the securing of the wave form metallic sheet being to the first face; and removing peaks of the sheet.

Claims

1. (canceled)

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15. (canceled)

16. A heat exchanger plate for providing heat transfer between a first flow along a first flowpath and a second flow along a second flowpath, the heat exchanger plate comprising a substrate having: a first face and a second face opposite the first face; a leading edge along the second flowpath and a trailing edge along the second flowpath; a proximal edge having at least one inlet port along the first flowpath and at least one outlet port along the first flowpath; and at least one passageway along the first flowpath between the at least one inlet port of the plate and the at least one outlet port of the plate, the heat exchanger plate further comprising a plurality of fin structures along the first face, each fin structure comprising: a base secured to the first face; and a first fin and a second fin extending from respective first and second edges of the base to respective first and second free edges.

17. The heat exchanger plate of claim 16 wherein: the fin structures are arrayed in parallel and progressively change in height from the first face from one fin structure to the next.

18. The heat exchanger plate of claim 16 wherein: the heat exchanger plate further comprising a plurality of second fin structures along the second face, each second fin structure comprising: a base secured to the second face; and a first fin and a second fin extending from respective first and second edges of the second fin structure base to respective first and second free edges.

19. A heat exchanger for providing heat transfer between a first flow along a first flowpath and a second flow along a second flowpath, the heat exchanger comprising: at least one plate bank comprising a plurality of plates according to claim 16, wherein: for each plate, the fin structures are arrayed in parallel and progressively change in height from the first face from one fin structure to the next; and within each plate bank, the progressive change in fin height accommodates a progressive change in plate orientation from one plate to the next.

20. The heat exchanger of claim 19 further comprising: an inlet manifold having at least one inlet port and at least one outlet port; and an outlet manifold having at least one outlet port and at least one inlet port, the first flowpath passing from the at least one inlet port of the inlet manifold, through the at least one passageway of each of the plurality of plates, and through the at least one outlet port of the outlet manifold.

21. The heat exchanger of claim 19 wherein: the inlet manifold and outlet manifold are arcuate having a convex first face and a concave second face; and the at least one plate bank is mounted to the convex first faces.

22. A gas turbine engine including the heat exchanger of claim 19 wherein: the first flow is a bleed flow and the second flow is a bypass flow.

23. The heat exchanger plate of claim 16 wherein: the fin structures are along a distal portion of the substrate; and the heat exchanger further comprises one or more integrally cast fins along a proximal portion.

24. The heat exchanger plate of claim 23 wherein: the fin structures and the one or more integrally cast fins along a proximal portion have a diverging height profile from proximal to distal.

25. The heat exchanger plate of claim 23 wherein: the heat exchanger plate further comprising a plurality of second fin structures along the second face, each second fin structure comprising: a base secured to the second face; and a first fin and a second fin extending from respective first and second edges of the second fin structure base to respective first and second free edges; the second fin structures are along a distal portion of the substrate; and the heat exchanger further comprises one or more integrally cast fins along a proximal portion of the second face.

26. The heat exchanger plate of claim 23 wherein: the fin structures and the substrate are of nickel-based superalloy.

27. The heat exchanger plate of claim 16 wherein: the fin structures and the substrate are of nickel-based superalloy.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0030] FIG. 1 is a schematic view of a heat exchanger.

[0031] FIG. 2 is a view of a manifold unit of the heat exchanger of FIG. 1.

[0032] FIG. 3 is a front end view of the heat exchanger of FIG. 1.

[0033] FIG. 4 is an axial/radial sectional view of the heat exchanger of FIG. 1 taken long line 4-4 of FIG. 3.

[0034] FIG. 5 is a side view of a plate of the heat exchanger.

[0035] FIG. 6 is a transverse sectional view of the plate of FIG. 5 taken along line 6-6 with exaggerated fin height.

[0036] FIG. 7 is a transverse sectional view of a precursor of the plate of FIG. 6.

[0037] FIG. 7A is an enlarged view of the plate precursor of FIG. 7.

[0038] FIG. 8 is a partial view of multiple plates of FIG. 6 in a circumferential array in the heat exchanger.

[0039] FIG. 9 is a view of the plate precursor during electro-discharge machining (EDM) of a fin array.

[0040] FIG. 10 is a view of an alternate plate precursor during electro-discharge machining (EDM) of a fin array.

[0041] FIG. 11 is a view of a second alternate plate precursor during electro-discharge machining (EDM) of a fin array.

[0042] FIG. 12 is a schematic axial half section view of a gas turbine engine including the heat exchanger of FIG. 1.

[0043] Like reference numbers and designations in the various drawings indicate like elements.

DETAILED DESCRIPTION

[0044] FIG. 1 shows a gas turbine engine heat exchanger 20 providing heat exchange between a first flowpath 900 and a second flowpath 902 and thus between their respective first and second fluid flows 910 and 912. In the exemplary embodiment, the flowpaths 900, 902 are gas flowpaths passing respective gas flows 910, 912. In the illustrated example, the first flow 910 enters and exits the heat exchanger 20 as a single piped flow and exits as a single piped flow 910; whereas the flow 912 is sector portion of an axial annular flow surrounding a central longitudinal axis (centerline) 10 of the heat exchanger and associated engine. For purposes of schematic illustration, the exemplary heat exchanger 20 is shown shaped to occupy approximately 20° of a 360° annulus. There may be multiple such heat exchangers occupying the full annulus or one or more such heat exchangers occupying only a portion of the annulus.

[0045] Other connections are also possible. For example, a configuration with a single first flow inlet and branched first flow outlets is shown in copending U.S. Patent Application No. 62/957,091 (the '091 application), filed Jan. 3, 2020, and entitled “Aircraft Heat Exchanger Assembly”, the disclosure of which is incorporated by reference herein in its entirety as if set forth at length.

[0046] The heat exchanger 20 has an inlet 22 and outlet 24 for the first flow. The exemplary inlet and outlet are, respectively, ports of an inlet manifold 26 (FIG. 2) and an outlet manifold 28 (discussed below) shown formed as portions of a combined manifold structure/unit 29. The manifold 29 has a first face 100 (outer diameter (OD) in the example), an opposite second face 102 (inner diameter (ID) in the example), a leading end 104, a trailing end 106, and lateral (circumferential (circumferentially facing) in the example) ends/edges 108, 110. In the particular arcuate manifold example, the OD face is convex and the ID face concave. Thus the respective manifold OD and ID surfaces/faces are portions of the faces 100 and 102

[0047] Exemplary manifolds are metallic (e.g., nickel-based superalloy). The inlet manifold and outlet manifold may each have a respective fitting 30, 32 providing the associated port 22, 24. As is discussed further below, the inlet manifold and outlet manifold are coupled to heat exchanger plates (panels) of one or more exemplary plate banks 40 (FIG. 3). FIG. 2 also shows exemplary inlet manifold outlet ports 34 and outlet manifold inlet ports 36 for such coupling.

[0048] Each plate bank 40 comprises a circumferential array 42 (FIG. 3) of plates 44 (discussed further below). In the exemplary banks, the plates extend axially and radially relative to the axis 10. Thus, the plates diverge from each other in the outward radial direction. Each plate has an inlet port 46 (FIG. 4) mated to an associated inlet manifold outlet port 34 and an outlet port 48 mated to an associated outlet manifold inlet port 36 (e.g., plugs of the plate mated to sockets in an outer diameter wall of the respective manifold). Each plate has internal passageways 49 (example in FIG. 4 based on that of the '091 application) between the ports 46 and 48.

[0049] The schematic illustrations of the heat exchanger have environmental and other details such as shrouds, mounting hardware, deflectors/blockers, and structural brace hardware (if any) removed for purposes of illustration.

[0050] Each plate 44 (FIG. 5) comprises a body or substrate 52 (e.g., cast or additively manufactured alloy such as nickel-based superalloy) having a leading edge 54, a trailing edge 56, an inboard or inner diameter (ID) edge 58, an outboard or outer diameter (OD) edge 60, a first circumferential (generally circumferentially facing) face 62 (FIG. 3) and a second circumferential face 64.

[0051] As is discussed below, one or both faces 62, 64 may bear fin arrays 70 (FIG. 6—shown for purposes of illustration with exaggerated progressive change in fin height relative to FIG. 3). The fins are separately formed (e.g., of folded sheetmetal—e.g., nickel-based superalloy) and secured (e.g., brazing, welding, diffusion bonding, and the like) to adjacent substrate(s) (generally see the '740 patent). As is discussed further below, exemplary fins are initially formed as square wave corrugations 72 (FIG. 7) of even height/amplitude whose troughs 73 (FIG. 7A) are secured to the associated face 62, 64. The corrugation has legs 74, 75 and peaks 76 and extends from a first sectional end 77 (an inner diameter (ID) end in the example) to a second section end 78 (an outer diameter (OD) end in the example). Along the direction of the individual corrugations (streamwise of the ultimate second flow 912) the corrugation has a first end near the plate substrate upstream edge and a second end near the plate substrate downstream edge. In general, the term “plate” or “panel” may be applied at any of several levels of detail. It may identify a body or substrate of an assembly or the greater assembly or subassembly (e.g., a cast substrate plus one or more separately-attached fin arrays).

[0052] After the wave corrugation(s) are secured, the peaks 76 and portions of the legs 74, 75 are cut off to create discrete pairs of fins 80, 82 (FIG. 6). Each fin extends to a free distal end/edge 84 and each pair are joined by the intact trough 73. At the ends (ID and OD in the example) of the fin arrays, there may be boundary conditions whereby a single isolated fin exists secured by an isolated trough remnant.

[0053] The exemplary trimming or cutting provides a progressive change in fin height from the associated substrate surface 62, 64. This allows a progressive proximal-to-distal change in spacing between adjacent plates. For example, FIG. 8 shows two adjacent plates extending exactly radially and diverging from each other by an angle θ. Exemplary θ is 0.5°-10.0°, more particularly, 0.5°-3.0°. The fins are thus trimmed at an angle θ/2 so that spacing between fin tips of adjacent plates is uniform. Thus, in the illustrated example, from the ID end of the fin array to the OD end, the fins progressively increase in height. Such fin divergence may be particularly advantageous for plates extending from an OD surface of an ID manifold; whereas a proximal-to-distal convergence would be advantageous for plates mounted to the ID surface of an OD manifold. Nevertheless, non-uniform spacing may be useful such as to allow greater clearance where there may be plate movement or differential thermal expansion.

[0054] FIG. 9 shows a wire electro-discharge machining (EDM) system 700 for removing all peaks of a given wave corrugation 72 in a single traversal. The system 700 includes an EDM power supply 702 having leads 704A, 704B respectively electrically connected to an EDM wire 706 (e.g., directly or to a spool) and the plate precursor (e.g., by a clip or other electrical contact 710 engaging the fin precursor or the substrate). The exemplary wire is held at the angle θ/2 and traversed parallel to the corrugations (e.g., axially relative to the ultimate position of the exemplary plate in the exemplary heat exchanger). Other conventional EDM components such as the wire holder, spools, and manipulator and the conductive fluid in which all may be immersed are not shown.

[0055] Relative to the '740 patent, the progressive height increase post-cutting may have one of more of several advantages. In heat exchangers with progressive change in plate orientation (e.g., radial plates), the uniform amplitude of source stock may be less expensive than forming source stock of progressive amplitude change. Assembly may also be eased because a relatively precise registry may be required for the progressive amplitude wave to contact both adjacent plates. By having separate fins on each adjacent plate face, slight variations in gaps between facing fins of the two plates or other artifacts of inconsistency in fin position are of trivial consequence.

[0056] Although the illustrated example involves removing peaks from the entire span S (FIG. 7), smaller fractions are possible (e.g., along a radially inboard portion of the corrugation 72, leaving radially outboard peaks 76 intact. Thus an exemplary range is 50% to 100% of the span S or 75% to 100%.

[0057] FIG. 10 schematically shows an alternative plate 200 initially formed as a unitary piece (e.g., via casting) including a main body 202 and integral fins 204 extending from opposite faces of the main body. General details of the main body may be similar to those of the substrates 52 of the plates 44. The fins 204 initially extend to distal ends/tips 206. In an example of an initial plate precursor, this may effectively involve a uniform fin height. However, as with the plate 44, the fins on one or both sides may be cut to provide a progressive change in height along at least a portion of the area/footprint covered by the fins. FIG. 8 specifically shows fins on one side cut down leaving final cut fin tips 208 while the fins on the other side are in the process of being cut.

[0058] Additionally, combinations of cast fins and foil fins are possible and may be simultaneously cut. FIG. 11 show a plate 250 with one or more integrally cast fins 204 along each side of a proximal portion 252 of a body and foil-formed fins 70 along each side of a distal portion 254. Fins on the drawing left side are cut away for illustration and fins on the right side are in the process of being cut by wire EDM.

[0059] Although a reverse taper of final fin height is shown (height diverging from proximal to distal), other height profiles are possible including converging.

[0060] FIG. 12 schematically shows a gas turbine engine 800 as a turbofan engine having a centerline or central longitudinal axis 10 and extending from an upstream end at an inlet 802 to a downstream end at an outlet 804. The exemplary engine schematically includes a core flowpath 950 passing a core flow 952 and a bypass flowpath 954 passing a bypass flow 956. The core flow and bypass flow are initially formed by respective portions of a combined inlet airflow 958 divided at a splitter 870.

[0061] A core case or other structure 820 divides the core flowpath from the bypass flowpath. The bypass flowpath is, in turn, surrounded by an outer case 822 which, depending upon implementation, may be a fan case. From upstream to downstream, the engine includes a fan section 830 having one or more fan blade stages, a compressor 832 having one or more sections each having one or more blade stages, a combustor 834 (e.g., annular, can-type, or reverse flow), and a turbine 836 again having one or more sections each having one or more blade stages. For example, many so-called two-spool engines have two compressor sections and two turbine sections with each turbine section driving a respective associated compressor section and a lower pressure downstream turbine section also driving the fan (optionally via a gear reduction). Yet other arrangements are possible.

[0062] FIG. 12 shows the heat exchanger 20 positioned in the bypass flowpath so that a portion of the bypass flowpath 954 becomes the second flowpath 902 and a portion of the bypass flow 956 becomes the second airflow 912.

[0063] The exemplary first airflow 910 is drawn as a compressed bleed flow from a diffuser case 850 between the compressor 832 and combustor 834 and returned radially inwardly back through the core flowpath 950 via struts 860. Thus, the flowpath 900 is a bleed flowpath branching from the core flowpath.

[0064] The use of “first”, “second”, and the like in the following claims is for differentiation within the claim only and does not necessarily indicate relative or absolute importance or temporal order. Similarly, the identification in a claim of one element as “first” (or the like) does not preclude such “first” element from identifying an element that is referred to as “second” (or the like) in another claim or in the description.

[0065] One or more embodiments have been described. Nevertheless, it will be understood that various modifications may be made. For example, when applied to an existing baseline configuration, details of such baseline may influence details of particular implementations. Accordingly, other embodiments are within the scope of the following claims.