GB509622A - Improved means for preventing the formation of ice on the wings of aircraft - Google Patents
Improved means for preventing the formation of ice on the wings of aircraftInfo
- Publication number
- GB509622A GB509622A GB2665/38A GB266538A GB509622A GB 509622 A GB509622 A GB 509622A GB 2665/38 A GB2665/38 A GB 2665/38A GB 266538 A GB266538 A GB 266538A GB 509622 A GB509622 A GB 509622A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- nozzle
- air
- partition
- conduit
- 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
- 230000015572 biosynthetic process Effects 0.000 title abstract 3
- 239000007789 gas Substances 0.000 abstract 7
- 238000005192 partition Methods 0.000 abstract 6
- 239000000463 material Substances 0.000 abstract 2
- 230000004048 modification Effects 0.000 abstract 2
- 238000012986 modification Methods 0.000 abstract 2
- 229910000669 Chrome steel Inorganic materials 0.000 abstract 1
- 230000000694 effects Effects 0.000 abstract 1
- 230000001141 propulsive effect Effects 0.000 abstract 1
- 230000003584 silencer Effects 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Exhaust Silencers (AREA)
Abstract
509,622. Preventing formation of ice on aircraft wings. COWDREY, C. L. Jan. 27, 1938, No. 2665. [Class 4] Means for preventing the formation of ice on an aircraft wing comprise a conduit connected to the engine exhaust manifold and having a. part of its wall formed by the leading edge, and a second conduit extending along, the wing behind the exhaust-gas conduit and arranged to lead air along the back of the latter. In a preferred form, the manifold is arranged inside the engine cowling and the air conduit is connected to a jacket surrounding the manifold. In the form. shown in Figs. 2 and 3, exhaust gases are led from the engine manifold 10 through a conduit 16 formed between the leading edge 13, which may be formed of a heat-resisting material such as nickel-chrome steel, and a partition 15 riveted to it, and are discharged through a nozzle 17 located beneath the wing tip. The partition 15 is provided with perforations 18 to allow the gases to pass into a silencer 19 filled with heat-insulating and sound-deadening material and formed between the partition 15 and a partition 20 also riveted to the leading edge, Air enters through a divergent inlet 25, is heated by passage through a jacket 24 and passes along a conduit 23, formed between the partition 20 and a partition 22, to an outlet nozzle 26 surrounding the nozzle 17. The exhaust gases leaving the nozzle 17 exert an ejector effect on the air. The leading edge and conduits are formed as a unit which is attached to the main part of the wing at 21. In a modification, Fig. 7, the air and exhaust gases are discharged through nozzles 31, 30 at the trailing edge. In a further modification, Fig. 9, the exhaust gases are discharged through a nozzle 40 before reaching the end of the wing and the air is discharged at the end of the wing through a nozzle 41. In this form, the outboard portion of the wing is heated by the air alone. The exhaust gas discharge nozzle may be designed as set forth in Specification 471,177 to give a jet reaction propulsive effect.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2665/38A GB509622A (en) | 1938-01-27 | 1938-01-27 | Improved means for preventing the formation of ice on the wings of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2665/38A GB509622A (en) | 1938-01-27 | 1938-01-27 | Improved means for preventing the formation of ice on the wings of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB509622A true GB509622A (en) | 1939-07-19 |
Family
ID=9743610
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2665/38A Expired GB509622A (en) | 1938-01-27 | 1938-01-27 | Improved means for preventing the formation of ice on the wings of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB509622A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211668A (en) * | 2011-04-27 | 2011-10-12 | 成都艾迈计算机辅助工程有限责任公司 | Dew prevention system using tail gas for aircraft windshield, and implementation method thereof |
| CN103850800A (en) * | 2012-11-29 | 2014-06-11 | 中航商用航空发动机有限责任公司 | Air inlet anticer and civil turbofan engine |
-
1938
- 1938-01-27 GB GB2665/38A patent/GB509622A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102211668A (en) * | 2011-04-27 | 2011-10-12 | 成都艾迈计算机辅助工程有限责任公司 | Dew prevention system using tail gas for aircraft windshield, and implementation method thereof |
| CN103850800A (en) * | 2012-11-29 | 2014-06-11 | 中航商用航空发动机有限责任公司 | Air inlet anticer and civil turbofan engine |
| CN103850800B (en) * | 2012-11-29 | 2016-04-06 | 中航商用航空发动机有限责任公司 | Intake duct deicer and civilian turbofan engine |
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