GB439805A - Improvements in jet propulsion apparatus for aircraft, projectiles and turbine apparatus - Google Patents
Improvements in jet propulsion apparatus for aircraft, projectiles and turbine apparatusInfo
- Publication number
- GB439805A GB439805A GB16861/34A GB1686134A GB439805A GB 439805 A GB439805 A GB 439805A GB 16861/34 A GB16861/34 A GB 16861/34A GB 1686134 A GB1686134 A GB 1686134A GB 439805 A GB439805 A GB 439805A
- Authority
- GB
- United Kingdom
- Prior art keywords
- nozzle
- passages
- walls
- fluid
- nozzles
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
439,805. Aircraft; jet-reaction apparatus. LEDUC, R., 3, Avenue Gabriel Dupont, Le Vesinet, Seine-et-Oise, France. June 6, 1934, Nos. 16861 and 18140. Convention dates, June 7, 1933 and Jan. 2, 1934. [Classes 4 and 114] [See also Groups XXI and XXVI] Jet - propulsion apparatus for aircraft, projectiles, and turbines comprises a nozzle of varying section and provided with a heat source so as to produce a cyclical variation of temperature and velocity of the fluid passing through it without mechanical means, the nozzle having a rearwardly divergent section immediately upstream from the source of heat and convergent directly afterwards, and to prevent separation of the streams of fluid from the nozzle walls, passages are formed in the walls between zones of different pressures. Fig. 3 shows the simplest form of nozzle wherein cold air entering at 0 is compressed by reason of the divergence of the nozzles from 0 to 1 and is then heated in its passage from 1 to 2 and finally expanded by reason of the convergence of the nozzle and the consequent fall of pressure until the air is discharged at 3. Fig. 1 shows a nozzle in which heat is applied in a divergent section from 0 to 1 and the fluid expanded in the section 1 to 2 cooled during its passage from 2 to 3 and finally compressed in the section 3 to 4 before discharge. A nozzle combining these two forms also is described. To prevent separation of the fluid stream from the nozzle walls in the divergent sections fluid is conveyed from ducts 8, Fig. 7, where the pressure is high to annular nozzles 10 and discharged tangentially in the direction of the main stream. Alternatively air may be drawn through rearwardly convergent passages through the nozzle walls from outside or the boundary layer within the nozzle may be sucked off through rearwardly divergent passages to the outside. Fig. 10 shows an aeroplane, having planes 7<a>, driven by a nozzle 1<a> surrounding the rear end of an enclosed nacelle 2a kept at a normal pressure inside. The hot source consists of burners 3a supplied with fuel vapourized in a radiator 4a which acts as the cold source. An annular guide vane 9a is provided near the entrance to the nozzle. For starting, a turbine or motor-driven propeller may be provided in front of the hot source and stopped during normal flight. The planes also may be fitted with nozzles as shown in Fig. 12 which also indicates the application to a projectile. The fluid enters at 29, and a hot source 28 and passages through the nozzle walls are provided. Fig. 13 shows a turbine in which air enters radially divergent passages 33 separated by blades, burners 34 being provided in the passages and supplied with fuel through a hollow shaft 36 and radial conduits 35. The fuel may be preheated in a radiator 37 swept by the exhaust gases. Alternatively the nozzles and burners may be stationary and the gases discharged at the peripheral speed of a bladed wheel. The temperature in the combustion chamber is kept below 500‹ C. The Specification as open to inspection under Sect. 91 comprises also the following subjectmatter. Where the nozzles are combined with a turbine, loose discs may be provided on each side of the turbine discs to reduce air friction. A projectile 15, Fig. 12 (Cancelled), is provided in front with a nozzle 16 to prevent the formation of an impact wave. The nozzle has passages 20 in its walls and may have a hot source 17. Fig. 13 (Cancelled), shows aprojectile provided with a casing 22 having holes 23 near its front end through which air is sucked and discharged at the rear end 24. A cap 25 obstructs the opening 24 during the firing of the gun. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR439805X | 1933-06-07 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB439805A true GB439805A (en) | 1935-12-06 |
Family
ID=8899988
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB16861/34A Expired GB439805A (en) | 1933-06-07 | 1934-06-06 | Improvements in jet propulsion apparatus for aircraft, projectiles and turbine apparatus |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB439805A (en) |
Cited By (32)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2425904A (en) * | 1941-11-29 | 1947-08-19 | James B Vernon | Turbine |
US2461797A (en) * | 1944-10-23 | 1949-02-15 | Aerojet Engineering Corp | Reaction propelled device for operation through water |
US2470729A (en) * | 1947-05-14 | 1949-05-17 | Edward A Stalker | Gas turbine power plant |
US2486990A (en) * | 1945-01-04 | 1949-11-01 | Franklin Inst Of The State Of | Jet propulsion motor |
US2518000A (en) * | 1946-03-01 | 1950-08-08 | Daniel And Florence Guggenheim | Auxiliary combustion chambers for reaction jet propulsion apparatus |
US2554187A (en) * | 1945-08-20 | 1951-05-22 | Rolls Royce | Fluid-solid boundary surface for aircraft |
US2566319A (en) * | 1946-04-12 | 1951-09-04 | Walter K Deacon | Ram jet fuel metering unit |
US2589945A (en) * | 1947-02-28 | 1952-03-18 | Leduc Rene | Athodyd having air permeable converging intake section for boundary layer controls |
US2596435A (en) * | 1946-09-18 | 1952-05-13 | Robert Roger Aime | Jet-propelled aircraft |
US2620882A (en) * | 1944-09-26 | 1952-12-09 | Morain Paul Henri Leon | Helicopter with jet-propelled rotor |
US2623355A (en) * | 1946-04-30 | 1952-12-30 | Boulet Georges | Hot pressurized gas producing means |
US2632994A (en) * | 1948-04-05 | 1953-03-31 | Mcdonnell Aircraft Corp | Ram jet engine and flame holder therefor |
US2639580A (en) * | 1945-03-21 | 1953-05-26 | James L Stuart | Valveless pulse jet engine |
US2675196A (en) * | 1947-06-30 | 1954-04-13 | Sncase | Jet propulsion engine for aircraft |
US2698512A (en) * | 1949-04-04 | 1955-01-04 | Phillips Petroleum Co | Method of operating ram-jet engines |
US2704645A (en) * | 1955-03-22 | colvin | ||
US2709337A (en) * | 1952-03-28 | 1955-05-31 | United Aircraft Corp | Boundary layer control for the diffuser of a gas turbine |
US2721444A (en) * | 1948-09-21 | 1955-10-25 | Johnson Horace James | Series-type multiple ram jet propulsion system |
US2811828A (en) * | 1950-12-02 | 1957-11-05 | United Aircraft Corp | Bleed means for confined supersonic flow |
US2840990A (en) * | 1952-07-17 | 1958-07-01 | John P Longwell | Multistage fuel injection for ram-jet combustor |
US2840988A (en) * | 1952-07-17 | 1958-07-01 | John P Longwell | Fuel control apparatus for supersonic ramjet |
US2881588A (en) * | 1948-04-27 | 1959-04-14 | Wilbur H Goss | Injector and method for fuel injection |
US2892410A (en) * | 1946-04-03 | 1959-06-30 | David H Sloan | Ram jet projectile |
US2906089A (en) * | 1951-01-04 | 1959-09-29 | Snecma | Air intake control for jet propulsion units |
US2912825A (en) * | 1956-02-29 | 1959-11-17 | United Aircraft Corp | Flameholder with boundary layer control |
US2961197A (en) * | 1953-11-19 | 1960-11-22 | Hertel Heinrich | Missile carrying aircrafts |
US2971724A (en) * | 1952-02-19 | 1961-02-14 | Helmut Ph G A R Von Zborowski | Annular wing flying machines |
US2977753A (en) * | 1954-02-13 | 1961-04-04 | Rech Etudes Prod | Improvements in continuous flow gas engines |
US3001364A (en) * | 1958-07-18 | 1961-09-26 | Lee R Woodworth | Method of gas stabilizing a supersonic inlet |
US3008667A (en) * | 1953-03-27 | 1961-11-14 | Frank A Dean | Ramjet diffuser |
US3023571A (en) * | 1955-07-20 | 1962-03-06 | Gene J Pietrangeli | Cascade diffuser |
US4544115A (en) * | 1979-05-01 | 1985-10-01 | Edgley Aircraft Limited | Ducted propeller aircraft |
-
1934
- 1934-06-06 GB GB16861/34A patent/GB439805A/en not_active Expired
Cited By (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2704645A (en) * | 1955-03-22 | colvin | ||
US2425904A (en) * | 1941-11-29 | 1947-08-19 | James B Vernon | Turbine |
US2620882A (en) * | 1944-09-26 | 1952-12-09 | Morain Paul Henri Leon | Helicopter with jet-propelled rotor |
US2461797A (en) * | 1944-10-23 | 1949-02-15 | Aerojet Engineering Corp | Reaction propelled device for operation through water |
US2486990A (en) * | 1945-01-04 | 1949-11-01 | Franklin Inst Of The State Of | Jet propulsion motor |
US2639580A (en) * | 1945-03-21 | 1953-05-26 | James L Stuart | Valveless pulse jet engine |
US2554187A (en) * | 1945-08-20 | 1951-05-22 | Rolls Royce | Fluid-solid boundary surface for aircraft |
US2518000A (en) * | 1946-03-01 | 1950-08-08 | Daniel And Florence Guggenheim | Auxiliary combustion chambers for reaction jet propulsion apparatus |
US2892410A (en) * | 1946-04-03 | 1959-06-30 | David H Sloan | Ram jet projectile |
US2566319A (en) * | 1946-04-12 | 1951-09-04 | Walter K Deacon | Ram jet fuel metering unit |
US2623355A (en) * | 1946-04-30 | 1952-12-30 | Boulet Georges | Hot pressurized gas producing means |
US2596435A (en) * | 1946-09-18 | 1952-05-13 | Robert Roger Aime | Jet-propelled aircraft |
US2589945A (en) * | 1947-02-28 | 1952-03-18 | Leduc Rene | Athodyd having air permeable converging intake section for boundary layer controls |
US2470729A (en) * | 1947-05-14 | 1949-05-17 | Edward A Stalker | Gas turbine power plant |
US2675196A (en) * | 1947-06-30 | 1954-04-13 | Sncase | Jet propulsion engine for aircraft |
US2632994A (en) * | 1948-04-05 | 1953-03-31 | Mcdonnell Aircraft Corp | Ram jet engine and flame holder therefor |
US2881588A (en) * | 1948-04-27 | 1959-04-14 | Wilbur H Goss | Injector and method for fuel injection |
US2721444A (en) * | 1948-09-21 | 1955-10-25 | Johnson Horace James | Series-type multiple ram jet propulsion system |
US2698512A (en) * | 1949-04-04 | 1955-01-04 | Phillips Petroleum Co | Method of operating ram-jet engines |
US2811828A (en) * | 1950-12-02 | 1957-11-05 | United Aircraft Corp | Bleed means for confined supersonic flow |
US2906089A (en) * | 1951-01-04 | 1959-09-29 | Snecma | Air intake control for jet propulsion units |
US2971724A (en) * | 1952-02-19 | 1961-02-14 | Helmut Ph G A R Von Zborowski | Annular wing flying machines |
US2709337A (en) * | 1952-03-28 | 1955-05-31 | United Aircraft Corp | Boundary layer control for the diffuser of a gas turbine |
US2840988A (en) * | 1952-07-17 | 1958-07-01 | John P Longwell | Fuel control apparatus for supersonic ramjet |
US2840990A (en) * | 1952-07-17 | 1958-07-01 | John P Longwell | Multistage fuel injection for ram-jet combustor |
US3008667A (en) * | 1953-03-27 | 1961-11-14 | Frank A Dean | Ramjet diffuser |
US2961197A (en) * | 1953-11-19 | 1960-11-22 | Hertel Heinrich | Missile carrying aircrafts |
US2977753A (en) * | 1954-02-13 | 1961-04-04 | Rech Etudes Prod | Improvements in continuous flow gas engines |
US3023571A (en) * | 1955-07-20 | 1962-03-06 | Gene J Pietrangeli | Cascade diffuser |
US2912825A (en) * | 1956-02-29 | 1959-11-17 | United Aircraft Corp | Flameholder with boundary layer control |
US3001364A (en) * | 1958-07-18 | 1961-09-26 | Lee R Woodworth | Method of gas stabilizing a supersonic inlet |
US4544115A (en) * | 1979-05-01 | 1985-10-01 | Edgley Aircraft Limited | Ducted propeller aircraft |
US4657209A (en) * | 1979-05-01 | 1987-04-14 | Optica Industries Limited | Ducted propeller aircraft |
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