GB719946A - Improvements in or relating to rocket type jet propulsion units - Google Patents
Improvements in or relating to rocket type jet propulsion unitsInfo
- Publication number
- GB719946A GB719946A GB129152A GB129152A GB719946A GB 719946 A GB719946 A GB 719946A GB 129152 A GB129152 A GB 129152A GB 129152 A GB129152 A GB 129152A GB 719946 A GB719946 A GB 719946A
- Authority
- GB
- United Kingdom
- Prior art keywords
- chamber
- fuel
- reaction
- passage
- valves
- 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
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
- F02K9/68—Decomposition chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/44—Feeding propellants
- F02K9/46—Feeding propellants using pumps
- F02K9/48—Feeding propellants using pumps driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
Abstract
719,946. Jet propulsion plant. NAPIER & SON, Ltd., D. Jan. 2, 1953 [Jan. 16, 1952], No. 1291/52. Class 110(3) [Also in Group XII] A rocket using a single fuel in which a reaction is initiated by heating the fuel to an appropriate temperature and maintained by the heat of the reaction, has the fuel delivered to the reaction chamber, by a turbine driven pump the turbine of which is actuated by a part of the reaction products from the chamber, and a pressure fuel accumulator charged by a hand pump which discharges a limited quantity of fuel into the reaction chamber for starting. The rocket shown comprises two reaction chambers A and B having separate propulsion nozzles A<SP>1</SP>, B<SP>1</SP>. The chamber B is used for combat and cruising conditions and both the chambers for take off and climb. The chamber A has an auxiliary compartment A<SP>2</SP> connected to it by a throat A<SP>3</SP> which is small as compared with the throat of the propulsion nozzle A<SP>1</SP>. When it is desired to start the rocket, fuel is first pumped by the hand pump L from the tank F into the accumulator K. The master controller R is then moved into a first position in which the valves M, M<SP>1</SP> are opened and the cartridge C<SP>1</SP>, B<SP>4</SP> or similar igniters fired. Fuel then flows through the passages E<SP>2</SP> and O into the auxiliary compartments A2, B<SP>2</SP> and a reaction started therein by the hot gases from the igniters. A part of the gases from the compartment B<SP>2</SP> pass into the chamber B and from there through the passage Q to the turbine Q<SP>1</SP> which then drives the fuel pump G. The exhaust from the turbine Q<SP>1</SP> passes through a passage Q<SP>2</SP> to an auxiliary propulsion nozzle Q<SP>3</SP>. The fuel pump G supplies fuel to the main fuel supply passage H. The controller R may then be moved into one or other of three further positions which open the valves M<SP>2</SP>, M<SP>3</SP>, M<SP>4</SP> and cause fuel to be supplied to the chamber B in which the reaction is started by the hot reation products from the chamber B<SP>2</SP>. One or more of the valves M<SP>2</SP>, M<SP>3</SP>, M<SP>4</SP> are opened according to the thrust required from the chamber B. As soon as a pre-determined pressure has been built up in the auxiliary chamber A<SP>2</SP> it acts through a passage N<SP>4</SP> on the diaphragm N<SP>2</SP> and opens the valve N. Fuel can then flow into the chamber A through the passage E<SP>1</SP> and nozzles D<SP>2</SP>. The chamber A is then brought into operation by the hot reaction products from the chamber A<SP>2</SP>. As soon as a pre-determined pressure has been reached in the chamber A, it acts through a passage N<SP>5</SP> on a diaphragm N<SP>3</SP> and opens the valve N<SP>1</SP>. Further fuel is then admitted to the chamber A through the passage E and nozzles D<SP>1</SP>. The chamber A may be cut out of operation by moving the master controller R to a further position in which the valve M is closed and the valves M<SP>2</SP>, M<SP>3</SP>, M<SP>4</SP> and possiblv M<SP>1</SP> still under selective control. The passage N<SP>4</SP> may be controlled by an electricallv controlled valve S<SP>3</SP> actuated by the controller R so that the chamber A may be put into or taken out of operation at the discretion of the pilot. The reaction chambers A and B may have two or more sets of injections some of which may direct fuel into the reaction chamber in the upstream direction and some in the downstream direction.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB129152A GB719946A (en) | 1952-01-16 | 1952-01-16 | Improvements in or relating to rocket type jet propulsion units |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB129152A GB719946A (en) | 1952-01-16 | 1952-01-16 | Improvements in or relating to rocket type jet propulsion units |
Publications (1)
Publication Number | Publication Date |
---|---|
GB719946A true GB719946A (en) | 1954-12-08 |
Family
ID=9719423
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB129152A Expired GB719946A (en) | 1952-01-16 | 1952-01-16 | Improvements in or relating to rocket type jet propulsion units |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB719946A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2897649A (en) * | 1956-07-03 | 1959-08-04 | Reddy Robert | Igniter |
US2930187A (en) * | 1956-11-23 | 1960-03-29 | Charles W Chillson | Variable thrust rocket engine |
US2986004A (en) * | 1958-06-30 | 1961-05-30 | Clary Corp | Electromagnetically controllable fluid propellant type rocket motor system |
US3000179A (en) * | 1959-12-11 | 1961-09-19 | Samms Adolphus | Rocket engine pump feed system |
US3031842A (en) * | 1959-05-18 | 1962-05-01 | United Aircraft Corp | Thrust control for solid rocket |
US3034293A (en) * | 1959-04-06 | 1962-05-15 | De Lacy F Ferris | Booster and sustainer thrust devices |
US3117417A (en) * | 1958-11-26 | 1964-01-14 | Jr Eugene V Rutkowski | Two-stage valve |
-
1952
- 1952-01-16 GB GB129152A patent/GB719946A/en not_active Expired
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2897649A (en) * | 1956-07-03 | 1959-08-04 | Reddy Robert | Igniter |
US2930187A (en) * | 1956-11-23 | 1960-03-29 | Charles W Chillson | Variable thrust rocket engine |
US2986004A (en) * | 1958-06-30 | 1961-05-30 | Clary Corp | Electromagnetically controllable fluid propellant type rocket motor system |
US3117417A (en) * | 1958-11-26 | 1964-01-14 | Jr Eugene V Rutkowski | Two-stage valve |
US3034293A (en) * | 1959-04-06 | 1962-05-15 | De Lacy F Ferris | Booster and sustainer thrust devices |
US3031842A (en) * | 1959-05-18 | 1962-05-01 | United Aircraft Corp | Thrust control for solid rocket |
US3000179A (en) * | 1959-12-11 | 1961-09-19 | Samms Adolphus | Rocket engine pump feed system |
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