Fluid sprinkling – spraying – and diffusing – Reaction motor discharge nozzle – With means controlling amount – shape or direction of...
Reexamination Certificate
1999-12-18
2001-10-09
Freay, Charles G. (Department: 3746)
Fluid sprinkling, spraying, and diffusing
Reaction motor discharge nozzle
With means controlling amount, shape or direction of...
C239S265190, C239S265390, C239S265350, C060S265000
Reexamination Certificate
active
06299077
ABSTRACT:
TECHNICAL FIELD
This invention relates to exhaust nozzles for gas turbine engines for powering aircraft and more particularly to the actuation system for a two dimensional exhaust nozzle.
BACKGROUND OF THE INVENTION
As one skilled in the aircraft turbine engine technology appreciates, it is abundantly important that the weight and size of the hardware in the exhaust nozzle is held to the minimum in order to assure that the thrust to weight ratio is optimized. Of course, it is equally well known that due to the aircraft and engine configurations, the size of the hardware is dictated by the aircraft manufacturer. In aircrafts that utilize vectoring nozzles, this is particularly true because these aircraft are typically made for the military and the performance of the aircraft is of the utmost importance.
In order to meet these goals and reduce actuator size, we have found that we can provide a nozzle actuation system that locates the actuator so that its load is tangential to the attached bell crank arm. Additionally the link interconnecting the other bell crank arm is oriented so that it is substantially normal to the convergent flap at the maximum loading condition and a pressure balancing hood is attached to the forward convergent flap hinge point. This nozzle actuation system made in accordance with the teachings of this invention affords the following advantages over the heretofore known nozzle actuation systems.
1. The systems horsepower requirements are lowered.
2. The distortion on the convergent flaps is minimized and the throat area remains more constant.
3. The vertical loads on the convergent flap's forward hinge is reduced.
4. Because of the reduction in flap distortion, this invention reduces the friction in the convergent/divergent hinge.
5. The load distribution is more even than heretofore known systems with a consequential load improvement on the supporting duct structure.
SUMMARY OF THE INVENTION
An object of this invention is to provide for a gas turbine engine with a two-dimensional vectoring exhaust system that powers and maneuvers aircraft an improved actuation system.
A feature of this invention is the location of the actuator relative to the bell crank of the linkage system in a convergent/divergent nozzle of a two-dimensional actuation system so that the load of the actuator is tangential to the arm of the bell crank.
Another feature of this invention of the nozzle actuation system is the linkage connected to the hinge point of the convergent/divergent nozzle is judiciously located to be substantially normal thereto at the maximum load condition.
Another feature of this invention is the judicious location of the pressure balancing hood extending from the forward end of the convergent flap so as augment the horsepower reduction of the actuator.
The foregoing and other features of the present invention will become more apparent from the following description and accompanying drawings.
REFERENCES:
patent: 5934564 (1999-08-01), Bouiller et al.
Harmon Kenneth E.
Petty Dale W.
Freay Charles G.
Friedland Norman
Hayes Eric
United Technologies Corporation
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