Appeal 2007-1434
Application 10/610,718
The claimed invention is a system for reducing jet engine noise including the
synergistic operation of fluidic vortex generators (fluidic chevrons) and a
configurable thermal acoustic shield to reduce the exhaust jet noise. Claims 1 and
13, reproduced below, are further illustrative of the claimed subject matter.
1. A system for jet engine noise control of a jet engine having a main jet
stream exiting a nozzle exit and flowing along a jet axis, the system comprising:
a thermal acoustic shield directed at a non-zero angle relative to the jet axis.
13. A system for jet engine noise control of a jet engine having a main jet
stream exiting a nozzle exit and flowing along a jet axis, the system comprising:
a fluidic chevron injected at a location relative to the nozzle exit for creating
a non-circular jet stream; and
a thermal acoustic shield directed at a non-zero angle to the jet axis for
selective noise reduction.
The references of record relied upon by the Examiner as evidence of
anticipation are:
Hoch US 3,721,314 Mar. 20, 1973
Braga Da Costa Campos US 6,705,547 B2 Mar. 16, 2004
Claims 1-25 stand rejected under 35 U.S.C. § 102 as anticipated by Costa
Campos.
Claims 1-25 stand rejected under 35 U.S.C. § 102 as anticipated by Hoch.
Appellants group the claims on appeal into two groups (Br. 6). Claims
1-12 stand or fall with claim 1 and claims 13-25 stand or fall with claim 13.
2
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