GB634332A - Improvements in and relating to rotary wing aircraft - Google Patents
Improvements in and relating to rotary wing aircraftInfo
- Publication number
- GB634332A GB634332A GB19226/47A GB1922647A GB634332A GB 634332 A GB634332 A GB 634332A GB 19226/47 A GB19226/47 A GB 19226/47A GB 1922647 A GB1922647 A GB 1922647A GB 634332 A GB634332 A GB 634332A
- Authority
- GB
- United Kingdom
- Prior art keywords
- blade
- compressor
- turbine
- jet
- air
- 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
- B64C27/04—Helicopters
- B64C27/12—Rotor drives
- B64C27/16—Drive of rotors by means, e.g. propellers, mounted on rotor blades
- B64C27/18—Drive of rotors by means, e.g. propellers, mounted on rotor blades the means being jet-reaction apparatus
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Supercharger (AREA)
Abstract
634,332. Rotary-wing aircraft. SOC. NATIONALE DE CONSTRUCTIONS AERONAUTIQUES DU CENTRE. July 18, 1947, Nos. 19226 and 19227. Convention dates, July 25, 1946, and June 18, 1947. [Class 4] [Also in Group XXVI] A rotary-wing aircraft is provided with a jet-driven lifting rotor, the compressed air for feeding the blade jets being drawn from the compressor of a turbo-jet engine, part of the combustion products of which are employed for translational propulsion of the aircraft. As shown in Fig. 2, the turbo-jet unit A is mounted in the fuselage 9, the jet 6 discharging below the tail control surfaces. Air for the blade jets 14 may be bled through a pipe 8 connected to a suitable stage of the compressor 2, Fig. 1 (not shown), or from the outlet thereof, Fig. 18, while in addition combustion - gases may be fed through a second pipe 58 either before or after passing through the turbine 5. In a further arrangement, Fig. 22 (not shown), a portion of the air from the compressor byepasses the turbine and is mixed with part of the turbine exhaust. Fig. 24 shows a construction in which a second compressor 70a is coupled to the turbine compressor 72a, its delivery being controlled by a valve 74 so that any desired proportion of its delivery may byepass the turbine. Such air may pass through a heat exchanger supplied with the turbine exhaust gases, Fig. 23 (not shown). The air or mixed air and combustion products are fed to a distributer at the top of the rotor shaft, and as shown in Fig. 7 the distributer 31 may be provided with a non- rotatable tiltable member 30 controlled by rods 33, 34 in order that the supply of gases to the blade jets may be subject to cyclical variation. A similar effect may be obtained by providing cyclically adjustable flaps to control the outlet area of the blade nozzles, Fig. 25 (not shown). Auxiliary fuel burners may be fitted in the ducts leading to the blade nozzles, or at the nozzles themselves. Boundary layer control may be effected through slots in the rotor blades, such slots being connected to points 42a, 42b, 42c ... in the compressor diffuser, Fig. 18, for suction effect, or to a suitable pressure stage of the compressor for blowing the boundary layer from the blades. Fig. 29 shows a rotor blade with suction slots 97 in the upper trailing edge of the inner portion of the blade length, the blade section being divided into two portions 98, 99, the former communicating with the slots 97 and the latter with the blade nozzle 101. For directional control purposes, the discharge nozzle of the main turbo-jet unit may be mounted for lateral movement about a vertical axis, or the jet may discharge over a movable rudder surface, Figs. 20 and 21 (not shown). The Specification as open to inspection under Sect. 91 comprises also an arrangement, Fig. 25 (Cancelled), in which an internal-combustion engine 78 drives a compressor 80, the discharge from which cools the engine and passes through byepasses 81 fitted with venturis 82 in the region of the engine exhaust pipes 83. An auxiliary fuel burner 84 may be fitted. In the arrangement according to Fig. 26 (Cancelled), the engine exhaust pipes have a common outlet 83a. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR634332X | 1946-07-25 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB634332A true GB634332A (en) | 1950-03-15 |
Family
ID=8993502
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB19226/47A Expired GB634332A (en) | 1946-07-25 | 1947-07-18 | Improvements in and relating to rotary wing aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB634332A (en) |
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2927748A (en) * | 1954-04-30 | 1960-03-08 | Elizabeth M Griswold | Direct lift airfoils |
US2944609A (en) * | 1956-06-01 | 1960-07-12 | United Aircraft Corp | Helicopter power transmission system |
US3032120A (en) * | 1960-07-11 | 1962-05-01 | United Aircraft Corp | Helicopter with jet driven blades |
US3853424A (en) * | 1973-07-18 | 1974-12-10 | H Bernaerts | Labyrinth air valve for rotor hub |
US3990811A (en) * | 1975-02-26 | 1976-11-09 | The United States Of America As Represented By The Secretary Of The Navy | Circulation controlled rotary wing aircraft and control system therefor |
US4169567A (en) * | 1974-12-13 | 1979-10-02 | Tamura Raymond M | Helicopter lifting and propelling apparatus |
US4214722A (en) * | 1974-12-13 | 1980-07-29 | Tamura Raymond M | Pollution reducing aircraft propulsion |
US4493612A (en) * | 1982-09-30 | 1985-01-15 | United Technologies Corporation | Axially slideable plenum for circulation control aircraft |
US4519563A (en) * | 1974-12-13 | 1985-05-28 | Tamura Raymond M | Pollution reducing aircraft propulsion |
WO2022112616A1 (en) * | 2020-11-30 | 2022-06-02 | Genesis Aerotech Limited | A rotor blade and pressure regulating arrangement |
-
1947
- 1947-07-18 GB GB19226/47A patent/GB634332A/en not_active Expired
Cited By (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2927748A (en) * | 1954-04-30 | 1960-03-08 | Elizabeth M Griswold | Direct lift airfoils |
US2944609A (en) * | 1956-06-01 | 1960-07-12 | United Aircraft Corp | Helicopter power transmission system |
US3032120A (en) * | 1960-07-11 | 1962-05-01 | United Aircraft Corp | Helicopter with jet driven blades |
US3853424A (en) * | 1973-07-18 | 1974-12-10 | H Bernaerts | Labyrinth air valve for rotor hub |
US4169567A (en) * | 1974-12-13 | 1979-10-02 | Tamura Raymond M | Helicopter lifting and propelling apparatus |
US4214722A (en) * | 1974-12-13 | 1980-07-29 | Tamura Raymond M | Pollution reducing aircraft propulsion |
US4519563A (en) * | 1974-12-13 | 1985-05-28 | Tamura Raymond M | Pollution reducing aircraft propulsion |
US3990811A (en) * | 1975-02-26 | 1976-11-09 | The United States Of America As Represented By The Secretary Of The Navy | Circulation controlled rotary wing aircraft and control system therefor |
US4493612A (en) * | 1982-09-30 | 1985-01-15 | United Technologies Corporation | Axially slideable plenum for circulation control aircraft |
WO2022112616A1 (en) * | 2020-11-30 | 2022-06-02 | Genesis Aerotech Limited | A rotor blade and pressure regulating arrangement |
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