US4759513A
Expired / Lapsed
US
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Noise reduction nacelle
Assignee: QUIET NACELLE CORP
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Filing: 1986-09-26
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Granted: 1988-07-26
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Expires: 2006-09-26
Abstract
Abstract A noise reduction nacelle for a jet engine having an inlet duct, a center body and at least one exit duct and which includes a composite sandwich panel positioned in the inlet duct, the center body and the at least one exit duct. The panel includes an inner face sheet, a honey comb core and an outer face sheet wherein the inner face sheet and the outer face sheet are connected to the inner and outer surfaces, of the core. A plurality of perforations are provided in the inner face sheet of a predetermined density and wherein each of the perforations is of a predetermined diameter. A method of forming the composite sandwich panel is also provided.
Inventors
- 👤 Fernando Birbragher
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 11:05
CPC Classifications
B; B32; B32B; B32B37/00; B32B37/14; B32B37/146; B64; B64D; B64D33/00; B64D33/02; F; F02; F02C; F02C7/00; F02C7/04; F02C7/045; F02K; F02K1/00; F02K1/78; F02K1/82; F02K1/827; B32B38/00; B32B38/04; B32B2038/047; B32B2307/00; B32B2307/10; B32B2307/102; B32B37/12; B64D2033/0206; B64D2033/0266; B64D2033/0286
Claims Analysis
Total Claims: 23
Claim 1
Independent Claim
119 words
A noise reduction nacelle for a jet engine, having an inlet duct, a center body and at least one exit duct, comprising: a composite sandwich panel positioned in said inlet duct, said center body and said at least one exit duct for absorbing high frequency harmonics produced by high speed air flow and for dampening noise generated by said engine wherein said panel consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one of said inner and outer face sheets and said honey comb core wherein said inner face sheet has a plurality of perforations formed therein and said perforations comprise an open area of 22-38%
Claim 2
Dependent Claim
119 words
A noise reduction nacelle for a jet engine, having an inlet duct, a center body and at least one exit duct, comprising: a composite sandwich panel positioned in said inlet duct, said center body and said at least one exit duct for absorbing high frequency harmonics produced by high speed air flow and for dampening noise generated by said engine wherein said panel consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one of said inner and outer face sheets and said honey comb core wherein said inner face sheet has a plurality of perforations formed therein and said perforations comprise an open area of 22-38%
Claim 3
Dependent Claim
31 words
A noise reduction nacelle as set forth in claim 1, wherein said inner face sheet comprises at least one layer of fiberglass fabric and at least one layer of graphite fabric.
Claim 4
Dependent Claim
28 words
A noise reduction nacelle as set forth in claim 2, wherein said at least one layer of graphite fabric of said inner sheet further comprises preimpregnated graphite fabric.
Claim 5
Dependent Claim
29 words
A noise reduction nacelle as set forth in claim 3, wherein said at least one outer face sheet further comprises a first, second and third layer of preimpregnated fabric.
Claim 6
Dependent Claim
22 words
A noise reduction nacelle as set forth in claim 1, wherein said inner face sheet includes a plurality of perforations formed therein.
Claim 7
Dependent Claim
20 words
A noise reduction nacelle as set forth in claim 1, wherein said honey comb has a thickness of 0.75 inches.
Claim 8
Dependent Claim
40 words
A noise reduction nacelle as set forth in claim 1, wherein said perforations of said inner sheet are of a density of 72 holes per square inch and wherein each of said perforations is of a diameter of 1/16 inch.
Claim 9
Dependent Claim
102 words
A noise reduction panel, comprising a composite sandwich panel which consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one of said inner and outer face sheets and said honey comb core wherein said inner face sheet and said outer face sheet are connected to inner and outer surfaces, respectively of said core and wherein at least one of said sheets comprises at least one layer of preimpregnated graphite fabric wherein said inner face sheet includes a plurality of perforations formed therein which comprises an open area of 22-38%.
Claim 10
Dependent Claim
102 words
A noise reduction panel, comprising a composite sandwich panel which consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one of said inner and outer face sheets and said honey comb core wherein said inner face sheet and said outer face sheet are connected to inner and outer surfaces, respectively of said core and wherein at least one of said sheets comprises at least one layer of preimpregnated graphite fabric wherein said inner face sheet includes a plurality of perforations formed therein which comprises an open area of 22-38%.
Claim 11
Dependent Claim
29 words
A noise reduction panel as set forth in claim 8, further comprising a film adhesive for bonding said inner face and outer face sheets to said honey comb core.
Claim 12
Dependent Claim
31 words
A noise reduction panel as set forth in claim 9, wherein said inner face sheet comprises at least one layer of fiberglass fabric and at least one layer of graphite fabric.
Claim 13
Dependent Claim
29 words
A noise reduction panel as set forth in claim 10, wherein said at least one layer of graphite fabric of said inner face sheet further comprises preimpregnated graphite fabric.
Claim 14
Dependent Claim
26 words
A noise reduction panel as set forth in claim 11, wherein said at least one sheet further comprises first, second and third layers of preimpregnated fabric.
Claim 15
Dependent Claim
40 words
A noise reduction panel as set forth in claim 8, wherein said perforations in said inner sheet are of a density of 72 holes per square inch and wherein each of said perforations is of a diameter of 1/16 inch.
Claim 16
Dependent Claim
37 words
A noise reduction panel as set forth in claim 8 wherein said upper sheet comprises a fiberglass fabric sheet and at least one graphite fabric sheet and said outer sheet comprises at least one graphite fabric sheet.
Claim 17
Dependent Claim
29 words
A noise reduction panel as set forth in claim 8, wherein said inner sheet comprises a metal sheet and said outer sheet comprises at least one graphite fabric sheet.
Claim 18
Independent Claim
167 words
A method of forming a noise reduction nacelle for a jet engine having an inlet duct, a center body and at least one exit duct, which comprises: forming a composite panel consisting of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one said inner and outer face sheets and said honey comb core wherein the inner face sheet and the outer face sheets are connected to inner and outer surfaces, respectively of the core; positioning said composite panel in said inlet duct, said center body and said at least one exit duct; forming a plurality of perforations in said inner sheet after positioning of said composite panel in said inlet duct, said center body and said at least one exit duct so as to form perforations of a density of 72 holes per square inch wherein each of said perforations of a diameter 1/16 inch and wherein said perforations comprise an open area of 22-38%
Claim 19
Independent Claim
167 words
A method of forming a noise reduction nacelle for a jet engine having an inlet duct, a center body and at least one exit duct, which comprises: forming a composite panel consisting of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one said inner and outer face sheets and said honey comb core wherein the inner face sheet and the outer face sheets are connected to inner and outer surfaces, respectively of the core; positioning said composite panel in said inlet duct, said center body and said at least one exit duct; forming a plurality of perforations in said inner sheet after positioning of said composite panel in said inlet duct, said center body and said at least one exit duct so as to form perforations of a density of 72 holes per square inch wherein each of said perforations of a diameter 1/16 inch and wherein said perforations comprise an open area of 22-38%
Claim 20
Dependent Claim
44 words
A method of forming a noise reduction nacelle as set forth in claim 16, which further comprises adhering said inner face and outer face sheet via an adhesive to said core and curing said adhesive at a temperature of 350° F. to 450° F.
Claim 21
Independent Claim
84 words
A method of forming a noise reduction panel which consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one said inner and outer face sheets and said honey comb core, which comprises: adhering said inner face and outer face sheets to opposite sides of said honey comb core via said adhesive sheet; and forming a plurality of perforations in said inner sheets so as to have an open area of 28-38%.
Claim 22
Independent Claim
84 words
A method of forming a noise reduction panel which consists of an inner face sheet, a honey comb core, an outer face sheet and an adhesive sheet positioned between at least one said inner and outer face sheets and said honey comb core, which comprises: adhering said inner face and outer face sheets to opposite sides of said honey comb core via said adhesive sheet; and forming a plurality of perforations in said inner sheets so as to have an open area of 28-38%.
Claim 23
Dependent Claim
54 words
A method of forming a noise reduction panel as set forth in claim 18, wherein said step of forming said plurality of perforations further comprises forming perforations in said inner face sheet of a density of 72 holes per square inch and wherein each of said perforations are of a diameter of 1/16 inch.
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) | 1991-07-26 | 1992-01-25 | 1992-07-26 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1995-07-26 | 1996-01-25 | 1996-07-26 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1999-07-26 | 2000-01-25 | 2000-07-26 | $7700.00 | Window Closed / Lapsed |