Patent GB-719946-A (GB)
Title: Improvements in or relating to rocket type jet propulsion units
Inventor: MORLEY ARNOLD WILLIAM
IPC: F02K9/68
Filed: 1952-01-16
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.