HYBRID GENERATOR

• US 3,782,112 A
• Filed: 02/24/1972
• Issued: 01/01/1974
• Est. Priority Date: 02/24/1972
• Status: Expired due to Term

• Current Assignee: Raymond J. Muzzy
• Original Assignee: Raymond J. Muzzy
• Inventors: Muzzy, Raymond J.
• Primary Examiner(s): Feinberg, Samuel
• Application Number:
  US05/230,538
• Time in Patent Office: 677 Days
• Field of Search: 60/220,251,260
• US Class Current: 60/251
• CPC Class Codes: F02K 9/72 using liquid and solid propellants, i.e. hybrid rocket-engine plants

Abstract

An improved hybrid injector to gasify and aerate a liquid oxidizer. A solid propellant gas generator is enclosed in an annular manifold surrounding the passageway leading from a source of liquid oxidizer to the main combustion chamber. Openings through the manifold communicate the gas generator with the liquid oxidizer passageway to thereby gasify and aerate the liquid oxidizer passing into the main combustion chamber.

Claims

1. In a hybrid rocket motor having an injector means for injecting an oxidizer into a combustion chamber, the improvement comprising:

a manifold radially outwardly from said injector means having an annular passageway surrounding said injector means and openings therein which communicate the annular passageway with the injector means;

said openings being substantially perpendicular to the flow of oxidizer in said injector means to cause turbulent flow in the injector means;

a gas generating means in communication with said manifold to heat and aerate the oxidizer prior to entry into the combustion chamber;

said injector means comprising a central passageway connected at one end to a source of oxidizer and at the other end to the combustion chamber;

a shaft disposed along the longitudinal axis of said central passageway;

a frustoconical enlarged portion of said shaft at said other end of said passageway;

a frustoconical beveled surface forming a part of said other end of said passageway; and

at least one of said openings extending through said frustoconical beveled surface normal to the frustoconical enlarged portion.

2. A hybrid rocket motor comprising:

a combustion chamber;

injector means having a wall forming a passageway extending to an oxidizer inlet in the combustion chamber for injecting oxidizer directly into the combustion chamber;

an annular chamber radially outwardly of and surrounding said injector means wall and passageway, said injector means wall also being a wall of said annular chamber, at least one opening in the wall of the injector means upstream of said combustion chamber oxidizer inlet to thereby provide direct communication between the injector means passageway and the annular chamber; and

a gas generating means in communication with said annular chamber for gasifying and aerating the oxidizer upstream of the combustion chamber.

3. The device of claim 2 wherein said gas generating means is contained within said annular chamber.

4. The device of claim 3 wherein said gas generating means comprises a solid propellant.

5. The device of claim 4 having a space in said annulaR chamber between said solid propellant and said injector means wall.

6. The device of claim 2 wherein said at least one opening is perpendicular to the main flow of oxidizer in said passageway to thereby produce turbulent flow in the oxidizer.

7. The device of claim 2 wherein said wall contains a plurality of openings providing communication between the injector means passageway and the annular chamber.

8. The device of claim 2 wherein at least one additional opening directly communicates the gas generating means with the combustion chamber of the hybrid rocket motor.

9. The device of claim 7 wherein at least one channel leads from the gas generating means to thereby pressurize a bladder in the oxidizer supply container.