GB506179A - Improved means for preventing the formation of ice on aircraft - Google Patents
Improved means for preventing the formation of ice on aircraftInfo
- Publication number
- GB506179A GB506179A GB32396/37A GB3239637A GB506179A GB 506179 A GB506179 A GB 506179A GB 32396/37 A GB32396/37 A GB 32396/37A GB 3239637 A GB3239637 A GB 3239637A GB 506179 A GB506179 A GB 506179A
- Authority
- GB
- United Kingdom
- Prior art keywords
- engine
- aircraft
- air
- ice
- formation
- 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
- 238000001816 cooling 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)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
506,179. Preventing formation of ice on aircraft. ELLOR, J. E. Nov. 24, 1937, No. 32396. [Class 4] To prevent the formation of ice on aircraft, the air-stream for cooling the engine enters through a diverging inlet and after becoming heated by the engine, which may be of eithei air-cooled or liquidcooled type, passes along conduits, at the leading edges of the wings or at other parts, and leaves by converging outlets The kinetic energy of the stream is thus first con verted into pressure energy and then re-converted to kinetic energy, the air heated by the engine or radiator being taken from a point at low pressure and velocity. Air enters at diverging inlets 13 above the two engines, and after passing over the radiators 11 passes by converging conduits 14, 15 to outlets 17, 18. In Fig. 4 (not shown), the aircraft has a single engine in the nose with a single radiator below it, and in Fig. 6 (not shown) a single engine has two radiators. The engine oil-cooler, if provided, may also be situated in the passage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB32396/37A GB506179A (en) | 1937-11-24 | 1937-11-24 | Improved means for preventing the formation of ice on aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB32396/37A GB506179A (en) | 1937-11-24 | 1937-11-24 | Improved means for preventing the formation of ice on aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB506179A true GB506179A (en) | 1939-05-24 |
Family
ID=10337967
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB32396/37A Expired GB506179A (en) | 1937-11-24 | 1937-11-24 | Improved means for preventing the formation of ice on aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB506179A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4385899A1 (en) * | 2022-12-13 | 2024-06-19 | Pratt & Whitney Canada Corp. | Aircraft thermal anti-icing system |
-
1937
- 1937-11-24 GB GB32396/37A patent/GB506179A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP4385899A1 (en) * | 2022-12-13 | 2024-06-19 | Pratt & Whitney Canada Corp. | Aircraft thermal anti-icing system |
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