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Ignition system for rocket engine combustion chambers operated by non-hypergolic propellant components

  • US 3,943,706 A
  • Filed: 12/27/1973
  • Issued: 03/16/1976
  • Est. Priority Date: 01/10/1973
  • Status: Expired due to Term
First Claim
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1. An ignition system for rocket engine combustion chambers operated by non-hypergolic propellant components, and particularly for precombustion chambers of main stream engines, comprising wall means defining a main combustion chamber having a thrust nozzle discharge and a precombustion chamber connected to said main combustion chamber, said precombustion chamber generating gases having one propellant component in excess of the other, a gas turbine in the connection between said main and said precombustion chambers operable by the gases perfused by said precombustion chamber and discharging these gases after use into said main combustion chamber, first and second propellant component pumps connected to and driven by said turbine, storage means for an igniting agent for storing said igniting agent in a gaseous state under a pressure which is lower relative to a pressure required to transport the igniting agent to said precombustion chamber, a first propellant component supply tank for storing a first propellant component which is non-hypergolically reactive with said igniting agent and which is connected to said first propellant component pump, a second propellant component supply tank for storing a second propellant component which is hypergolically reactive with said igniting agent but not with said first propellant component and which is connected to said second propellant component pump, respective first and second delivery conduits connected between said first and second propellant component pumps and said precombustion chamber for the flow of said components to said precombustion chamber, piston means movable in said storage means and dividing said storage means into an ignition agent space on one side of said piston means and a pressurizing gas-receiving space on the other side of said piston means, first and second storage tanks for separately storing second and first gaseous non-hypergolic propellant components under high pressure connected respectively to said precombustion chamber and to said pressurizing gas-receiving space for forcing said piston to move in a direction to compress the igniting agent and to subsequently direct it through said first delivery conduit to said precombustion chamber, said storage space means having a port uncoverable by substantially complete movement of said piston to evacuate said ignition agent and to communicate the space containing said first gaseous propellant component with said first delivery conduit for its flow through said first delivery conduit after the flow of the ignition agent, said first storage tank connection to said pressurizing gas-receiving space having valve means operable only upon starting of said engine to pressurize said pressurizing gas-receiving space.

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