US 6,269,647 B1Granted

Rotor system

OwnerRobert S. Thompson, Jr., Gregg G. Williamsinventors

Life of this patent

Estimating the term…

Loading patent…

Abstract

A rotor system for a rocket engine comprises a first hollow shaft portion and a surrounding annular duct. The interior of the first hollow shaft portion is adapted to receive a first propellant component, and is in fluid communication with a first rotary orifice. The annular duct is adapted to receive a second propellant component, and is in fluid communication with a second rotary orifice located proximate to the first rotary orifice. The rotor system further comprises a third rotary orifice operatively connected to second hollow shaft portion and in fluid communication with the interior of the first hollow shaft portion for discharging a second portion of the first propellant component at second location. The rotary orifices are operatively connected to respective rotary pressure traps that isolate the pressure at the respective rotary orifices from the respective inlet pressures of the respective propellant components.

Claims26

Dependent claims

A rotor system for a rocket engine, comprising:

a. a first hollow shaft portion having an axis of rotation, wherein a first end of said first hollow shaft portion is adapted to receive a first fluid propellant component;
b. at least one first rotary orifice operatively coupled to said first hollow shaft portion, wherein said at least one first rotary orifice is in fluid communication with an interior of said first hollow shaft portion;
c. an annular duct surrounding at least a portion of said first hollow shaft portion, wherein a first end of said annular duct is adapted to receive a second fluid propellant component;
d. at least one second rotary orifice operatively coupled to said first hollow shaft portion, wherein said at least one second rotary orifice is in fluid communication with said annular duct;
e. a second hollow shaft portion, wherein a first end of said second hollow shaft portion is operatively coupled to a second end of said first hollow shaft portion, and an interior of said second hollow shaft portion is in fluid communication with said interior of said first hollow shaft portion;
and
f. at least one third rotary orifice, wherein said at least one third rotary orifice is in fluid communication with said interior of said second hollow shaft portion.

4 more elements

Dependencies are inferred from the claim text.

Facts

Application: 09/522,873Filed 10 Mar 2000 · us provisional application
Priority: 10 Mar 1999
Granted: 7 Aug 2001
Term ends: Not estimatedThe source records don’t support an estimate.

Classification9 codes

F02K 9/52
Feeding propellants: injectors
F02K 9/48
Using pumps: driven by a gas turbine fed by propellant combustion gases or fed by vaporized propellants or other gases
F02K 9/62
Constructional parts; Details not otherwise provided for: combustion or thrust chambers
F02K 9/64
Combustion or thrust chambers: having cooling arrangements