GB744107A - Improvements in or relating to aircraft - Google Patents
Improvements in or relating to aircraftInfo
- Publication number
- GB744107A GB744107A GB27727/53A GB2772753A GB744107A GB 744107 A GB744107 A GB 744107A GB 27727/53 A GB27727/53 A GB 27727/53A GB 2772753 A GB2772753 A GB 2772753A GB 744107 A GB744107 A GB 744107A
- Authority
- GB
- United Kingdom
- Prior art keywords
- driven
- rotors
- blades
- compressed air
- louvres
- 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
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Control Of Turbines (AREA)
Abstract
744,107. Aircraft. BREGUET, L. Oct. 8, 1953 [Dec. 18, 1952], No. 27727/53. Class 4. [Also in Groups XII and XXVI] An aircraft comprises lift or propulsive rotors, mounted within the wings, in a plane substantially parallel to the plane of said wings, said rotors being driven by means of a gas flow directed onto the blades of blade wheels associated with said rotors. As shown in Fig. 2, the rotor 1 is driven through gearing 6 by a turbine wheel 2 driven by the flow of compressed air ducted from a compressor 3 driven by a gas turbine engine (not shown). A burner 8 (see Group XXVI) may heat the compressed air before reaching the nozzle 5. In the embodiment of Figs. 6, 7 and 13 two contra-rotating rotors 1 are disposed one in each wing, each comprising a set of lift providing blades bound by a ring 11 supporting a plurality of blades 2a driven by compressed air supplied from a nozzle 5. The rotor shaft 10 is journalled in bearings 10a mounted on the upper and lower wing surfaces, and an outer member 16 surrounding the driven blades 2a is guided by a plurality of wheels 17 supported in forks 17a fast to the wing or on a rod 15b fast to the nozzle 5. Rod 15b also supported by collars 15c, bears a rod 15a biased by a spring 15d to urge roller 15 to contact the outer ring 16 to guide it. As shown in Fig. 6, louvres 18a and 18b are provided in the upper and lower surfaces, and are opened to give free passage of air when the rotors are to provide direct lift. During forward travel, louvres 18a are shut, and 18b are somewhat open, so that air is drawn in through a forward intake 14a. The burners 8 may be shut off for forward travel. Part of the compressed air supply may be bled off to drive turbo props 23 (Fig. 13) or to give direct forward reaction thrust. In this case, louvres 18b may be slightly open to provide control of the boundary layer. Part of the airflow may be directed over the tail unit to provide manoeuvrability at low speeds or when hovering.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR744107X | 1952-12-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB744107A true GB744107A (en) | 1956-02-01 |
Family
ID=9146116
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB27727/53A Expired GB744107A (en) | 1952-12-18 | 1953-10-08 | Improvements in or relating to aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB744107A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1142505B (en) * | 1960-07-13 | 1963-01-17 | Man Turbomotoren G M B H | Drive for the hub blower vertical take off and landing aircraft |
| US3176934A (en) * | 1957-09-06 | 1965-04-06 | Gen Electric | Vtol aircraft |
| US3179353A (en) * | 1958-02-04 | 1965-04-20 | Ryan Aeronautical Co | Jet powered ducted fan convertiplane |
| WO2001004495A1 (en) * | 1999-07-10 | 2001-01-18 | Frank Iles | Axial flow fan |
-
1953
- 1953-10-08 GB GB27727/53A patent/GB744107A/en not_active Expired
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3176934A (en) * | 1957-09-06 | 1965-04-06 | Gen Electric | Vtol aircraft |
| US3179353A (en) * | 1958-02-04 | 1965-04-20 | Ryan Aeronautical Co | Jet powered ducted fan convertiplane |
| DE1142505B (en) * | 1960-07-13 | 1963-01-17 | Man Turbomotoren G M B H | Drive for the hub blower vertical take off and landing aircraft |
| WO2001004495A1 (en) * | 1999-07-10 | 2001-01-18 | Frank Iles | Axial flow fan |
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