Sound absorbing apparatus for a supersonic jet propelling engine

• US 5,655,361 A
• Filed: 09/11/1995
• Issued: 08/12/1997
• Est. Priority Date: 09/14/1994
• Status: Expired due to Fees

• Current Assignee: Mitsubishi Jukogyo Kabushiki Kaisha
• Original Assignee: Mitsubishi Jukogyo Kabushiki Kaisha
• Inventors: Kishi, Kimihiro
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US08/526,235
• Time in Patent Office: 701 Days
• Field of Search: 60/266, 60/271, 239/127.3, 181/213, 181/220, 181/222
• US Class Current: 60/266
• CPC Class Codes: F02K 1/827 Sound absorbing structures or liners
• CPC Class Codes: F05D 2260/96 Preventing, counteracting or reducing vibration or noise
• CPC Class Codes: G10K 11/161 in systems with fluid flow G10K11/162 takes precedence; gas flow silencers or exhaust apparatus for machines or engines in general or for internal combustion engine F01N, noise absorbers in pipes or pipe systems F16L55/02; noise absorption in air conditioning and ventilation F24F13/24; silencing exhaust or propulsion jets in aircraft B64D33/06
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

To reduce a noise and to cool a nozzle in a supersonic jet propelling engine, a sound absorbing member made of a porous plate (4) and a honeycomb structure (2) or a porous plate (4) and a torus core (3) is provided between a nozzle plate (5) and a liner (1), a cooling air (7) is caused to flow along an inner surface of the nozzle plate (5) and to impinge against the liner (1) through holes (10) of the porous plate (4). Furthermore, a number of holes (11) which are slanted on a rear side are formed in the liner (1) so that the cooling air (9) are injected through the holes (11).

Claims

1. A cooling and noise reducing wall assembly for an exhaust gas nozzle of a supersonic jet engine, said wall assembly comprising:

a nozzle plate;

a liner spaced from said nozzle plate, said liner having a first surface, a second surface exposed to hot combustion gases, and a plurality of holes extending between said first surface and said second surface;

a honeycomb structure spaced from said nozzle plate and having a first side opposing said nozzle plate and a second side positioned directly on said first surface of said liner; and

a porous plate attached to said first side of said honeycomb structure, wherein said porous plate and said nozzle plate define a cooling air flow passage such that cooling air can flow from said cooling air flow passage through said porous plate into said honeycomb structure and impinge against said first liner surface.

2. The cooling and noise reducing wall assembly as claimed in claim 1, wherein said plurality of holes in said liner are angled in the direction of flow of the hot combustion gas so that a film of cooling air forms along said second surface of said liner.