초록 ▼

A tripropellant coaxial pintle injector for a rocket engine which enables smooth transitioning between two types of propellants that are adapted to be alternatively mixed with a third type of propellant in a combustion chamber of a rocket engine. The tripropellant coaxial injector includes a pintle

A tripropellant coaxial pintle injector for a rocket engine which enables smooth transitioning between two types of propellants that are adapted to be alternatively mixed with a third type of propellant in a combustion chamber of a rocket engine. The tripropellant coaxial injector includes a pintle for expelling a first propellant into a combustion chamber in a generally radial direction and two or more concentric metering sleeves which define orifices for expelling two or more different propellants into the combustion chamber in an axial direction thus, such a configuration allows for alternative mixing of two propellants with a third propellant in the combustion chamber of a rocket engine.

대표청구항 ▼

[ What is claimed and desired to be covered by a Letters Patent is as follows:] [1.] A tripropellant injector for a rocket engine comprising:a first input manifold for receiving a first propellant;an elongated hollow annular pintle defining a longitudinal axis and forming a generally hollow cylindri

[ What is claimed and desired to be covered by a Letters Patent is as follows:] [1.] A tripropellant injector for a rocket engine comprising:a first input manifold for receiving a first propellant;an elongated hollow annular pintle defining a longitudinal axis and forming a generally hollow cylindrical cavity, said pintle closed on first and second opposing ends and formed with a plurality of radial passageways and in ronmnunication with said fit input manifold, said pintle also configured with a first orifice for expelling said first propellant into said combustion chamber in a radial direction;a second input manifold for receiving a second propellant;a first annular metering sleeve concentrically located relative to said longitudinal axis defining a second orifice for expelling said second propellant into said combustion chamber, said second orifice being in communication with said second input manifold;a third input manifold for receiving a third propellant;a second annular metering sleeve concentrically located relative to said longitudinal axis and said first metering sleeve defining a third orifice, said third orifice being in communication with said third input manifold, said first and second metering sleeves being disposed radially outwardly relative to said generally hollow cylindrical cavity; anda first cone type projection disposed adjacent said first opposing end of said pintle, said cone-type projection axially aligned with said input radial passageways to deflect said first propellant in an axial direction.