GB1498193A - Silencing of jet engines - Google Patents
Silencing of jet enginesInfo
- Publication number
- GB1498193A GB1498193A GB4079774A GB4079774A GB1498193A GB 1498193 A GB1498193 A GB 1498193A GB 4079774 A GB4079774 A GB 4079774A GB 4079774 A GB4079774 A GB 4079774A GB 1498193 A GB1498193 A GB 1498193A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- main
- indicated
- auxiliary
- jet
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
- 230000030279 gene silencing Effects 0.000 title abstract 3
- 238000007599 discharging Methods 0.000 abstract 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/40—Nozzles having means for dividing the jet into a plurality of partial jets or having an elongated cross-section outlet
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Supercharger (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1498193 Jet propulsion nozzles - silencing ROLLS-ROYCE Ltd 11 Sept 1975 [19 Sept 1974] 40797/74 Heading F1J The invention relates to a means for directionally silencing a main propulsion jet discharging from the main propulsion nozzle of a jet engine. In Figs. 3a, 3b, 3c and 4 the main nozzle of a gas turbine jet engine is indicated at 16 and one auxiliary nozzle 20 is disposed below the main nozzle in the vertical plane of the aircraft, the auxiliary nozzle being of rectangular form and the outlet being bevelled as indicated of 21 so that gas flow discharges from the nozzle as indicated of 22 at an angle α to the line of discharge 23 of the main jet, the auxiliary jet nozzle discharge being of rectangular form. The noise level contour from the main nozzle without the auxiliary nozzle in operation is indicated by the line 26 and that with the auxiliary nozzle in operation is indicated by line 27 so that the noise level is effectively reduced in the zone indicated angle Y 1 vertically beneath the nozzle; the noise level in the regions indicated by angle Y 2 at either side of the silenced region Y 1 is however increased. Further auxiliary nozzles such as 18, Fig. 2, (not shown) may be disposed laterally of the main nozzle so that gas may be discharged therefrom to silence these regions in the event of the aircraft banking whereby the increased noise level would be directly beneath the aircraft. Various other arrangements are described in which the auxiliary nozzle may be of isosceles triangle form with the apex disposed inwardly or outwardly with respect to the main nozzle; also with the inclination angle of the auxiliary nozzle to the main nozzle at 25 degrees and 55 degrees.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4079774A GB1498193A (en) | 1974-09-19 | 1974-09-19 | Silencing of jet engines |
| IT2733775A IT1042626B (en) | 1974-09-19 | 1975-09-17 | REFINEMENTS IN THE DESIGN OF INDIBDI GAS TURBINE |
| FR7528568A FR2285521A1 (en) | 1974-09-19 | 1975-09-18 | IMPROVEMENTS TO REDUCE TURBOMOTOR NOISE |
| DE19752541962 DE2541962A1 (en) | 1974-09-19 | 1975-09-19 | METHOD OF REDUCING JET NOISE FROM JET ENGINES AND NOZZLE ARRANGEMENT FOR IMPLEMENTING THESE |
| JP11354975A JPS5177712A (en) | 1974-09-19 | 1975-09-19 | Jetsutoenjinno shusuishinjetsutono shoonhohooyobi sochi |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4079774A GB1498193A (en) | 1974-09-19 | 1974-09-19 | Silencing of jet engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1498193A true GB1498193A (en) | 1978-01-18 |
Family
ID=10416659
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4079774A Expired GB1498193A (en) | 1974-09-19 | 1974-09-19 | Silencing of jet engines |
Country Status (5)
| Country | Link |
|---|---|
| JP (1) | JPS5177712A (en) |
| DE (1) | DE2541962A1 (en) |
| FR (1) | FR2285521A1 (en) |
| GB (1) | GB1498193A (en) |
| IT (1) | IT1042626B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2720242A1 (en) * | 1976-05-13 | 1977-11-24 | United Technologies Corp | METHOD AND DEVICE FOR REDUCING THE NOISE LEVEL OF A TWO-FLOW TURBOL AIRJET ENGINE |
| US20100006697A1 (en) * | 2007-01-30 | 2010-01-14 | Japan Aerospace Exploration Agency | Low noise aircraft |
| CN115853677B (en) * | 2023-01-10 | 2025-07-08 | 航天科工火箭技术有限公司 | Turbine exhaust structure of liquid rocket engine |
-
1974
- 1974-09-19 GB GB4079774A patent/GB1498193A/en not_active Expired
-
1975
- 1975-09-17 IT IT2733775A patent/IT1042626B/en active
- 1975-09-18 FR FR7528568A patent/FR2285521A1/en active Granted
- 1975-09-19 JP JP11354975A patent/JPS5177712A/en active Pending
- 1975-09-19 DE DE19752541962 patent/DE2541962A1/en active Pending
Also Published As
| Publication number | Publication date |
|---|---|
| FR2285521B3 (en) | 1978-05-05 |
| DE2541962A1 (en) | 1976-04-01 |
| IT1042626B (en) | 1980-01-30 |
| FR2285521A1 (en) | 1976-04-16 |
| JPS5177712A (en) | 1976-07-06 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| CSNS | Application of which complete specification have been accepted and published, but patent is not sealed |