GB885713A - Improvements relating to exhaust silencers for jet-propulsion engines - Google Patents
Improvements relating to exhaust silencers for jet-propulsion enginesInfo
- Publication number
- GB885713A GB885713A GB19336/57A GB1933657A GB885713A GB 885713 A GB885713 A GB 885713A GB 19336/57 A GB19336/57 A GB 19336/57A GB 1933657 A GB1933657 A GB 1933657A GB 885713 A GB885713 A GB 885713A
- Authority
- GB
- United Kingdom
- Prior art keywords
- discharge
- area
- silencer
- central
- aperture
- 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
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)
- Exhaust Silencers (AREA)
Abstract
885,713. Jet propulsion nozzles. FAIREY CO. Ltd. June 19, 1958 [June 19, 1957], No. 19336/57. Class 110 (3). In a jet propulsion nozzle silencer which comprises a multi-point cross-tail nozzle whose discharge area is afforded by a number of narrow nozzle slots extending radially outwardly from an unobscured central discharge aperture, the nozzle slots being formed at the end of a corresponding number of flutes protruding radially from a tapered frusto-conical central passage which terminates in the central discharge aperture, the area of the central discharge aperture is between one tenth and one twentieth of the total discharge area. Preferably the area of the central unobscured discharge aperture should be between one tenth and one eleventh of the total silencer discharge area. The smallest number of slots that will provide the necessary discharge areas should be used. The silencer 10 comprises a convergent-open-ended frusto-conical tunnel 15 leading from a circular intake 16 to a small central discharge aperture 17, the walls of the tunnel being of fluted form. The flutes terminate in discharge slots 19 disposed around the aperture 17. The silencer is made up of a number of sheet metal plates which are bent and then welded to each other. These plates are welded at the inlet end to a ring 29 and at their outlet end to a ring 30. Webs 31 are also provided. In the arrangement shown the area of the discharge aperture 17 is a little less than one tenth of the total discharge area of the silencer. The actual dimensions of the nozzle are also given.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB19336/57A GB885713A (en) | 1957-06-19 | 1957-06-19 | Improvements relating to exhaust silencers for jet-propulsion engines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB19336/57A GB885713A (en) | 1957-06-19 | 1957-06-19 | Improvements relating to exhaust silencers for jet-propulsion engines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB885713A true GB885713A (en) | 1961-12-28 |
Family
ID=10127643
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB19336/57A Expired GB885713A (en) | 1957-06-19 | 1957-06-19 | Improvements relating to exhaust silencers for jet-propulsion engines |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB885713A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5265807A (en) * | 1992-06-01 | 1993-11-30 | Rohr, Inc. | Aerodynamic stiffening ring for an aircraft turbine engine mixer |
| EP1338784A1 (en) * | 2002-02-06 | 2003-08-27 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Lobe mixer for jet flow |
| CN109473194A (en) * | 2018-11-12 | 2019-03-15 | 中国原子能科学研究院 | An Attenuation Cylinder for Deep Pool Low Temperature Heating Reactor |
-
1957
- 1957-06-19 GB GB19336/57A patent/GB885713A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5265807A (en) * | 1992-06-01 | 1993-11-30 | Rohr, Inc. | Aerodynamic stiffening ring for an aircraft turbine engine mixer |
| EP1338784A1 (en) * | 2002-02-06 | 2003-08-27 | Ishikawajima-Harima Heavy Industries Co., Ltd. | Lobe mixer for jet flow |
| US7017332B2 (en) | 2002-02-06 | 2006-03-28 | Ishikawajima-Harima Heavy Industries Co., Ltd | Lobe mixer for jet flow |
| CN109473194A (en) * | 2018-11-12 | 2019-03-15 | 中国原子能科学研究院 | An Attenuation Cylinder for Deep Pool Low Temperature Heating Reactor |
| CN109473194B (en) * | 2018-11-12 | 2024-05-14 | 中国原子能科学研究院 | Attenuation tube for deep water tank type low-temperature heat supply stack |
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