GB505873A - Improvements in and relating to arrangements for preventing the formation of ice on aircraft - Google Patents
Improvements in and relating to arrangements for preventing the formation of ice on aircraftInfo
- Publication number
- GB505873A GB505873A GB20925/38A GB2092538A GB505873A GB 505873 A GB505873 A GB 505873A GB 20925/38 A GB20925/38 A GB 20925/38A GB 2092538 A GB2092538 A GB 2092538A GB 505873 A GB505873 A GB 505873A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chamber
- air
- passages
- walls
- wing
- 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 2
- 238000002485 combustion reaction Methods 0.000 abstract 1
- 239000007788 liquid Substances 0.000 abstract 1
- 238000005192 partition Methods 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)
- Supercharger (AREA)
Abstract
505,873. Preventing formation of ice on aircraft. GROVES, W. W. (Junkers Flugzeug-und-Motorenwerke Akt.-Ges.) July 14, 1938, No. 20925. [Class 4] In means for preventing ice-formation on aircraft in which a gaseous or liquid heatcarrier is led into a chamber of large crosssection located inside the structure to be protected, e.g. a wing, strut, fin or rudder, and then passes along and in contact with the outer skin of the structure through one or more passages, the boundary walls of the chamber form at least part of the walls of the passages. In one form, Fig. 1, air is heated by passing it through aradiator 6 surrounding the exhaust pipe 3 and is led via a pipe 7 to chamber 8 extending along the entire wing span. The air then passes through an opening 9, formed along the front of the chamber, into passages 25 formed between the wing skin 10 and the walls 11 of the chamber, and finally escapes through openings in the rear part of the wing. The walls 11 may be formed by channel members, or . corrugated plates secured to the skin 10. In a second form, Fig. 5, which may also serve as a cooler for combustion air for a supercharged engine, air, heated, e.g. by passage through a blower or one stage of a multi-stage blower, enters a chamber 32 similar to the chamber 8 and passes via passages 33 into a second chamber 35 separated from the chamber 32 by a heat-insulating partition 36. The air then passes out via a pipe 37, e.g. to the carburetter or the next stage of the blower.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB20925/38A GB505873A (en) | 1938-07-14 | 1938-07-14 | Improvements in and relating to arrangements for preventing the formation of ice on aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB20925/38A GB505873A (en) | 1938-07-14 | 1938-07-14 | Improvements in and relating to arrangements for preventing the formation of ice on aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB505873A true GB505873A (en) | 1939-05-18 |
Family
ID=10154114
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB20925/38A Expired GB505873A (en) | 1938-07-14 | 1938-07-14 | Improvements in and relating to arrangements for preventing the formation of ice on aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB505873A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103600845A (en) * | 2013-08-23 | 2014-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Heat channel area adjustable slat anti-icing design method |
-
1938
- 1938-07-14 GB GB20925/38A patent/GB505873A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN103600845A (en) * | 2013-08-23 | 2014-02-26 | 中国航空工业集团公司西安飞机设计研究所 | Heat channel area adjustable slat anti-icing design method |
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