US 4,782,660 AGranted

Sequenced and pressure controlled injector

AssigneeRockwell International Corporation

InventorsFrank F. Domyan, Frank J. Gombos

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Abstract

An injector assembly 10 for injecting fuel and oxidizer in a combustion chamber 38 of a fluid-fueled rocket engine. Injector assembly 10 comprises a stationary housing 12, a plate member 14 attached to the housing 12, at least one injector subassembly 18 and actuation means 16. Each injector subassembly 18 includes a plug 44 attached to the housing 12 and a movable elongated throttle means 64 connected to the actuation means 16. When the throttle is at least partially open, fuel flows through inlet 20, orifice 110, inner passageway 66, orifice 112 and finally to the combustion chamber 38. Oxidizer flows through inlet 22, orifice 114, outer passageway 68, orifice 116 and finally to the combustion chamber 38. Controlling the flow of propellants at upstream orifices 110,114 controls the propellant pressure at the downstream orifices 112,116 during thrust level changes and corresponding combustion chamber pressure changes of the engine, thereby maintaining a constant stream momentum and combustion efficiency.

An injector assembly for injecting first and second propellants into a combustion chamber of a fluid fueled rocket engine, comprising:

a stationary housing;
a plate member rigidly attached to said housing, said plate member having an upstream face and a downstream face, the downstream face being adjacent a combustion chamber, said plate member having at least one opening therethrough;
an injector subassembly contained within said opening, including:
a plug centrally disposed therein, said plug being rigidly attached to said housing, an outer surface of said plug and an inner surface of said plate member forming said opening cooperatively defining a flow passageway;
and
an elongated injector throttle means comprising a single element surrounding said plug and located within said flow passageway for dividing said flow passageway into an inner passageway for a flow of said first propellant and an outer passageway for a flow of said second propellant, said throttle means being movable within said flow passageway for simultaneous flow control of each propellant at inner and outer downstream sealing locations adjacent the downstream face of said plate member and at inner and outer upstream sealing locations adjacent the upstream face of said plate member, this simultaneous flow control being dependent upon the position of the throttle means within the plate member, said throttle means including:
an upstream end portion;
an upstream sealing portion, located adjacent said upstream end portion and at said upstream sealing locations, said upstream sealing portion having a cross-sectional area substantially equal to the area of said flow passageway;
a downstream sealing portion located at said downstream sealing locations with a cross-sectional area substantially equal to the area of said flow passageway;
and
a decreased cross-sectional area portion located between said upstream sealing portion and said downstream sealing portion;
and
actuation means for controlling the movement of said throttle means, said actuation means being operably engaged with said upstream end portion,
said upstream sealing portion serving to control the flow of propellants at said upstream locations for controlling the propellant pressure at the downstream sealing locations during thrust level changes and corresponding combustion chamber pressure changes of the engine, thereby maintaining a constant stream momentum and combustion efficiency.

11 more elements

Abstract

Claims9