Patent · US5655361A · A · US
Sound absorbing apparatus for a supersonic jet propelling engine
- (11) Publication number
- US5655361A
- (21) Application number
- US-52623595-A
- (22) Filing date
- 1995-09-11
- (30) Priority date
- 1994-09-14
- (43) Publication date
- 1997-08-12
- (45) Date of grant
- 1997-08-12
- (52) CPC
- G10K Sound-producing devices; methods or devices for protecting against, or for damping, noise or other acoustic waves in general; acoustics not otherwise provided for: 11/161
- F02K Jet-propulsion plants: 1/827
- F05D Indexing scheme for aspects relating to non-positive-displacement machines or engines, gas-turbines or jet-propulsion plants: 2260/96
- Y02T Climate change mitigation technologies related to transportation: 50/60
- (73) Assignee
- MITSUBISHI HEAVY IND LTD
- (54) Title
- Sound absorbing apparatus for a supersonic jet propelling engine
- (57) 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).
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Claims (2)
- 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.
- 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.
Citations (3)
- US4747543A
- US5080284A
- US5388765A
Record as JSON
{
"publication_number": "US5655361A",
"country": "US",
"kind": "A",
"title": "Sound absorbing apparatus for a supersonic jet propelling engine",
"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."
],
"cpc": [
"G10K 11/161",
"F02K 1/827",
"F05D 2260/96",
"Y02T 50/60"
],
"assignees": [
"MITSUBISHI HEAVY IND LTD"
],
"filing_date": "1995-09-11",
"publication_date": "1997-08-12",
"grant_date": "1997-08-12",
"priority_date": "1994-09-14",
"application_number": "US-52623595-A",
"family_id": "16745430",
"citations": [
"US4747543A",
"US5080284A",
"US5388765A"
]
}
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