Engine nacelle acoustic panel with integral wedge fairings and an integral forward ring

(19)

(11)

EP 0 895 223 A3

(12)	EUROPEAN PATENT APPLICATION

(88)	Date of publication A3:
	17.11.1999 Bulletin 1999/46

(43)	Date of publication A2:
	03.02.1999 Bulletin 1999/05

(21)	Application number: 98202574.4

(22)	Date of filing: 30.07.1998

(51)	International Patent Classification (IPC)⁶: G10K 11/172, F16L 55/02

(84)	Designated Contracting States:
	AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE
	Designated Extension States:
	AL LT LV MK RO SI

(30)

Priority:

30.07.1997 US 54196 P
13.04.1998 US 59797

(71)	Applicant: THE BOEING COMPANY
	Seattle, Washington 98124-2207 (US)

(72)	Inventors:
	Welch, John M. Wichita, Kansas 67207 (US) Wikstrom, Robert F. Derby, Kansas 67037 (US) Stratton, Terry W. Rose Hill, Kansas 67133 (US) Popp, Thomas D. Wichita, Kansas 67206 (US) Kitt, Brian R. Wichita, Kansas 67212 (US)

(74)	Representative: Land, Addick Adrianus Gosling
	Arnold & Siedsma, Advocaten en Octrooigemachtigden, Sweelinckplein 1 2517 GK Den Haag 2517 GK Den Haag (NL)

(54)	Engine nacelle acoustic panel with integral wedge fairings and an integral forward ring

(57) An acoustic panel (26) for the nacelle (20) of a high bypass jet engine. The acoustic panel (26) has a perforated composite inner sheet (54), an outer composite sheet (96, 98), and a honeycomb-core material (74) sandwiched therebetween. The acoustic panel (26) includes an integral forward ring (36) and integral wedge fairings (44).

Search report