GB635082A - Airfoil - Google Patents
AirfoilInfo
- Publication number
- GB635082A GB635082A GB13212/47A GB1321247A GB635082A GB 635082 A GB635082 A GB 635082A GB 13212/47 A GB13212/47 A GB 13212/47A GB 1321247 A GB1321247 A GB 1321247A GB 635082 A GB635082 A GB 635082A
- Authority
- GB
- United Kingdom
- Prior art keywords
- spar
- blade
- leading edge
- holes
- ribs
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/473—Constructional features
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
Abstract
635,082. Aerofoils. GOODYEAR AIRCRAFT CORPORATION. May 16, 1947, No. 13212. Convention date, Nov. 29, 1946. [Class 4] An aerofoil, more particularly a helicopter rotor blade, comprises a spar formed from two interengaging U- shaped members 2, 3 arranged with their limbs horizontal, a monocoque leading edge section 6 of stainless steel, and ribs 4 to which are secured laminar trailing edge cover strips 9, 10, the laminations comprising a layer of fabric-reinforced thermosetting plastic 18 covered by sheets of stainless steel 19, 20. Lightening holes 14, 15, 17 are provided in the spar and ribs, the holes 15 and some of the holes 17 being closed by air-tight membranes to prevent the building up of pressure differentials due to the rotation of the blade. A trailing edge member 11 of triangular section, and made of a fabric-reinforced thermosetting plastic, is cemented to the middle layer 18 of the trailing edge cover strips 9, 10. The leading edge of the blade forms a passage for hot de-icing gases which are discharged through a hole 29 in the upper surface of the blade tip 12. A baffle plate 5 is secured to the spar member 2, and a heat transfer fin 8a is embedded in a counterweight 8 extending along the leading edge. Drain holes are provided in the lower corners of the ribs and spar, and in the tip member 12. The blade root member is inserted between the spar members 2, 3 and bolted thereto. The leading edge of the blade may be made as described in Specification 634,583, [Group XXII], and the root spar as in Specification 635,084, [Group XXII].
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US635082XA | 1946-11-29 | 1946-11-29 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB635082A true GB635082A (en) | 1950-04-05 |
Family
ID=22049662
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB13212/47A Expired GB635082A (en) | 1946-11-29 | 1947-05-16 | Airfoil |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB635082A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2943624A1 (en) * | 2009-03-27 | 2010-10-01 | Airbus France | AIRCRAFT NACELLE COMPRISING AN ENHANCED EXTERIOR WALL |
-
1947
- 1947-05-16 GB GB13212/47A patent/GB635082A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2943624A1 (en) * | 2009-03-27 | 2010-10-01 | Airbus France | AIRCRAFT NACELLE COMPRISING AN ENHANCED EXTERIOR WALL |
| WO2010109152A3 (en) * | 2009-03-27 | 2010-12-23 | Airbus Operations Sas | Aircraft nacelle comprising a reinforced outer wall |
| US9114884B2 (en) | 2009-03-27 | 2015-08-25 | Airbus Operations Sas | Aircraft nacelle comprising a reinforced outer wall |
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