TURBINE INLET SILENCER
Assignee
Filed
Apr 9, 1992
Granted
Feb 13, 1996
Location
San Diego CA (SAIC/General Dynamics)
Abstract
In order to reduce noise transmission through the air inlet duct (16) of a turbine engine (10), the air inlet duct (16) provides a non-linear path defined by a bend (24) for air from a source, and the turbine engine (10) includes a sound attenuation assembly (26) in the form of a splitter dissipative silencer disposed near the bend (24) in the air inlet duct (16). More specifically, the turbine engine (10) is such that the splitter dissipative silencer (26) can be formed as a modular assembly (42) removably securable near the bend (24) in the air inlet duct (16) upstream of a radial compressor (12) for removal and/or replacement or availability as an optional component of the turbine engine (10).
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Aug 28, 1992
Rescinded
Jan 12, 1993
Duration
4 months
Inventor
- 1JAMES C. NAPIER
Sensitive facility: San Diego CA (SAIC/General Dynamics)
Record Details
- Patent number
- US 5491308
- Application
- 07866142
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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