Patent GB-800354-A (GB)
Title: Combustion chamber for gas generation provided with cooling means and a system for operating the same
Inventor: ROSS CHANDLER COLE
IPC: F02C3/30
Filed: 1955-12-23
Abstract: 800,354. Gas turbine plant. AEROJETGENERAL CORPORATION. Dec. 23, 1955, No. 36909/55. Class 110 (3). [Also in Group XII] A combustion apparatus comprises a combustion chamber F which communicates through a constriction T with a cooling chamber C, the combustion chamber being provided with means 30, 41 for the introduction of fuel and oxidizer, e.g. aniline and red fuming nitric acid, and the cooling chamber having a discharge nozzle 47 at its downstream end and means for the introduction of a cooling liquid downstream of the constriction. The combustion chamber F has a spiral fin on its outer surface which with the outer casing 11 forms a spiral passage through which fuel is circulated from inlet 25 to outlet 24 thus cooling the chamber and pre-heating the fuel. A spiral passage is also formed around the cooling chamber C by means of an outer casing 17 and a spiral fin 16, cooling fluid such as water entering through inlet 22 and discharging into the chamber C through inlets 21 just downstream of the constriction T, whereby combustion gases from the chamber F are cooled uniformly before discharging through the nozzles 47 to a gas turbine. The head of the combustion chamber is constructed to form fuel and oxidizer injectors, the fuel issuing through orifices 32 impinging at points P with oxidizer issuing through orifices 38. The outer casing 11 of the combustion chamber and the wall 4 of the cooling chamber C are formed integrally. The fuel supply system is shown in Fig. 9 in which a motor M drives through shaft 75 a coolant pump 76, a fuel pump 61 and an oxidizer pump 62. A gas turbine 60 is also mounted on the shaft 75 and when supplied with gases takes over the drive of the pumps, an overriding clutch 51 being provided for this purpose. Coolant liquid will flow from the pump 76 into the conduits 80, 81 and 87, but the valves 89 and 83 are closed so that coolant flows through conduit 87 to one side of the spring-loaded piston 88 which operates through linkage to open valve 100 in the fuel supply line. Throttle valve 83 is now opened and coolant will flow through the inlet 22 into the jacket around the cooling chamber C finally entering the chamber C through openings 21. Fuel will flow from the pump 61 into the duct 69 through control valve 72 to the valve 96 which is still closed; some fuel will be led off through conduit 69a, through the jacket around the combustion chamber F and then through the conduit 74 back to the suction side of the pump 61. At the same time, oxidizer flows from the pump 62 through the conduit 67 and control valve 77 to the stillclosed valve 95. During the starting period, the solenoid-operated four-way valve 93 has been so positioned that coolant fluid passes to one side of piston 104 thereby maintaining the three valves 96, 95 and 89 in their closed positions. When the coolant pump has built up sufficient pressure to operate the piston 88 thus opening the valve 100, the electrical contacts 110, 111 close and the solenoid 106 is energized whereby the four-way valve 93 is moved so as to allow coolant fluid to flow to the right-hand side of the piston 104, this causing the three valves 96, 95 and 89 to open. Fuel and oxidizer now flow to the combustion chamber F, the fuel passing through the already-open valve 100. The gases from the combustion apparatus drive the turbine 60 which now takes over driving of the pumps 62, 61 and 76 from the motor M, the pumps 61 and 62 supplying fuel and oxidizer to an apparatus in which it is to be used. If the supply of coolant should fail, the piston 88 will move to the right under the action of the spring 101 thus causing the fuel valve 100 to close, whereby the entire unit will automatically shut down.