Seal for a joint or juncture – Seal between relatively movable parts – Relatively rotatable radially extending sealing face member
Reexamination Certificate
1989-09-26
2001-11-06
Jordan, Charles T. (Department: 3641)
Seal for a joint or juncture
Seal between relatively movable parts
Relatively rotatable radially extending sealing face member
C277S377000, C277S377000, C277S377000, C415S113000, C415S119000
Reexamination Certificate
active
06311983
ABSTRACT:
FIELD OF THE INVENTION
This invention relates to a rocket engine turbopump shaft seal; particularly to a combination static lift-off face contact seal and a floating ring shaft seal.
BACKGROUND OF THE INVENTION
In rocket engines it is critical for proper performance that the amount of fuel entering the engine be carefully controlled. Therefore a static face seal is employed around the turbine shaft to prevent fuel leaking into or around the combustion chamber before ignition. Once the engine is started, the static face seal, due to friction, would soon wear out. Therefore, it is removed from contact with the rotating mating ring when the engine starts and is pushed back into contact with the rotating mating ring when the engine is shut down.
A second seal, a floating ring seal, is employed around the turbine shaft to prevent fuel flow-by while the shaft is turning at high speed.
In the past, the static lift-off face seal and its mechanism for movement and the floating seal ring were separate more complex units.
SUMMARY OF THE INVENTION
The present invention combines the static lift-off face seal and the floating ring seal into one part. When the engine is turned on, the pressure of the fuel in the pump pushes the face seal portion of the floating ring seal away from contact with the rotating mating ring. The face seal portion of the floating ring seal is returned to contact with the rotating mating ring by a bellows spring to seal the fuel from leaking when the engine is off.
Combining the face seal and the floating ring seal in one unit, and using the pressure of the fuel to move the unit reduces the complexity of the turbopump, and reduces its cost.
REFERENCES:
patent: 819635 (1906-05-01), Callan
patent: 3874677 (1975-04-01), Ludwig et al.
patent: 4099727 (1978-07-01), Weiler
patent: 4373858 (1983-02-01), Eastman
patent: 4722663 (1988-02-01), Swearingen
patent: 4738453 (1988-04-01), Ide
patent: 4744721 (1988-05-01), Villeneuve
patent: 308722 (1930-01-01), None
Field Harry B.
Jordan Charles T.
Semunegus Lulit
The Boeing Company
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