US5042565A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Fiber reinforced composite leading edge heat exchanger and method for producing same
Assignee: Boeing North American Inc
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Filing: 1990-01-30
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Granted: 1991-08-27
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Expires: 2010-01-30
Abstract
Abstract A braided fiber reinforced composite, particularly a braided graphite fiber reinforced copper composite leading edge heat exchanger 18 is disclosed, formed of inlet and outlet conduits 22 and 24 and means forming a plurality of passages 26 interconnecting the conduits, as a single integral unit. The heat exchanger is formed by providing inlet and outlet manifolds 36 and 38, successively interconnecting a plurality of mandrels 40, 52 and 56 transversely between the manifolds and braiding reinforcing fibers 32 preferably having high elevated temperature strength and high thermal conductivity, e.g. graphite fibers, around each of the mandrels and the manifolds, the braiding progressing in a direction along the length of the manifolds. The resulting braided preform 58 is consolidated by introducing a matrix material of high thermal conductivity, such as copper or copper alloy, e.g. as by molten infiltration, into the braided preform 58 and removing the mandrels and manifolds from the consolidated preform, as by leaching.
Inventors
- 👤 James L. Yuen
- 👤 Beverly A. Ash
- 👤 William P. Purmort
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-23 12:24
CPC Classifications
B; B64; B64C; B64C1/00; B64C1/38; F; F28; F28F; F28F1/00; F28F1/02; F28F1/04; F28F1/045; F28F21/00; Y; Y10; Y10S; Y10S165/00; Y10S165/905; Y10T; Y10T428/00; Y10T428/12; Y10T428/12444; Y10T428/12486
Claims Analysis
Total Claims: 17
Claim 1
Independent Claim
85 words
A leading edge heat exchanger for aerothermal applications which comprises inlet and outlet conduits, each having a wall, and means forming a plurality of passages and containing lands between said passages, said passages interconnecting said conduits, said conduits and said means forming said passages being integral and formed of a composite consisting of a fiber reinforced matrix material of high thermal conductivity, the reinforcing fiber being braided in said matrix material and in the lands around said passages and in the wall around said conduits.
Claim 2
Dependent Claim
85 words
A leading edge heat exchanger for aerothermal applications which comprises inlet and outlet conduits, each having a wall, and means forming a plurality of passages and containing lands between said passages, said passages interconnecting said conduits, said conduits and said means forming said passages being integral and formed of a composite consisting of a fiber reinforced matrix material of high thermal conductivity, the reinforcing fiber being braided in said matrix material and in the lands around said passages and in the wall around said conduits.
Claim 3
Dependent Claim
16 words
The leading edge heat exchanger of claim 1, said passages being disposed transversely between said conduits.
Claim 4
Dependent Claim
21 words
The leading edge heat exchanger of claim 1, the inlet conduit being tapered from the upstream to the downstream end thereof.
Claim 5
Dependent Claim
25 words
The leading edge heat exchanger of claim 1, the reinforcing fiber having high elevated temperature strength and high thermal conductivity, and capable of being braided.
Claim 6
Dependent Claim
23 words
The leading edge heat exchanger of claim 1, said matrix material selected from the group consisting of copper and silver, and their alloys.
Claim 7
Dependent Claim
15 words
The leading edge heat exchanger of claim 2, said composite being graphite fiber reinforced copper.
Claim 8
Dependent Claim
95 words
A leading edge heat exchanger for hypersonic vehicles in the form of a fiber reinforced composite consisting of a matrix material of high thermal conductivity and a reinforcing fiber having high elevated temperature strength and high thermal conductivity, said composite comprising inlet and outlet conduits, a wall interconnecting and integral with said conduits, transverse passages in said wall and communicating with said conduits, and lands separating said passages, said reinforcing fiber being braided in said matrix in said wall and in said lands, and in the matrix material around said inlet and said outlet conduits.
Claim 9
Dependent Claim
95 words
A leading edge heat exchanger for hypersonic vehicles in the form of a fiber reinforced composite consisting of a matrix material of high thermal conductivity and a reinforcing fiber having high elevated temperature strength and high thermal conductivity, said composite comprising inlet and outlet conduits, a wall interconnecting and integral with said conduits, transverse passages in said wall and communicating with said conduits, and lands separating said passages, said reinforcing fiber being braided in said matrix in said wall and in said lands, and in the matrix material around said inlet and said outlet conduits.
Claim 10
Dependent Claim
20 words
The leading edge heat exchanger of claim 7, said matrix material being copper and said reinforcing fiber being graphite fiber.
Claim 11
Dependent Claim
142 words
A leading edge heat exchanger for hypersonic vehicles produced by the process which comprises providing an inlet manifold and an outlet manifold, successively interconnecting a plurality of mandrels transversely between said manifolds, braiding a reinforcing fiber having high elevated temperature strength and high thermal conductivity around each of said successive mandrels after installation thereof, and around the adjacent portion of said inlet and outlet manifolds, said braiding progressing in a direction substantially extending along the length of said manifolds, to form a braided preform. consolidating the braided fiber preform around said manifolds and around said mandrels by introduction of a matrix material of high thermal conductivity into said braided preform, and removing said mandrels and said manifolds from said consolidated preform to form a braided fiber reinforced matrix composite having inlet and outlet conduits and a plurality of transversely disposed interconnecting passages.
Claim 12
Dependent Claim
142 words
A leading edge heat exchanger for hypersonic vehicles produced by the process which comprises providing an inlet manifold and an outlet manifold, successively interconnecting a plurality of mandrels transversely between said manifolds, braiding a reinforcing fiber having high elevated temperature strength and high thermal conductivity around each of said successive mandrels after installation thereof, and around the adjacent portion of said inlet and outlet manifolds, said braiding progressing in a direction substantially extending along the length of said manifolds, to form a braided preform. consolidating the braided fiber preform around said manifolds and around said mandrels by introduction of a matrix material of high thermal conductivity into said braided preform, and removing said mandrels and said manifolds from said consolidated preform to form a braided fiber reinforced matrix composite having inlet and outlet conduits and a plurality of transversely disposed interconnecting passages.
Claim 13
Dependent Claim
46 words
The leading edge heat exchanger of claim 9, employing a plurality of tows of said fibers, the tows progressing through the braided preform in a diagonal direction, and at each set of braided tow crossings, a successive mandrel is inserted between the inlet and outlet manifolds.
Claim 14
Dependent Claim
23 words
The leading edge heat exchanger of claim 9, said matrix material selected from the group consisting of copper and silver, and their alloys.
Claim 15
Dependent Claim
40 words
The leading edge heat exchanger of claim 11, said fiber being graphite fiber and said matrix material being copper or copper alloy, to form a graphite fiber reinforced copper composite leading edge heat exchanger having integral inlet and outlet conduits.
Claim 16
Dependent Claim
44 words
The leading edge heat exchanger of claim 12, said consolidating being carried out by molten infiltration of copper or copper alloy into the braided preform, or by electroless deposition of copper into said braided preform, or by isostatic pressing of pre-copper-coated graphite braided preform.
Claim 17
Dependent Claim
47 words
The leading edge heat exchanger of claim 12, said inlet and outlet manifolds and said mandrels being formed of a material selected from the group consisting of strontium oxide and iron, and said removing of said mandrels and said manifolds being carried out by chemical leaching thereof.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1994-08-26 | 1995-02-25 | 1995-08-27 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1998-08-26 | 1999-02-25 | 1999-08-27 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2002-08-26 | 2003-02-25 | 2003-08-27 | $7700.00 | Window Closed / Lapsed |