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US 5,511,376 AGranted
Axisymmetric vectoring nozzle
AssigneeUnited Technologies Corporation
InventorWilliam K. Barcza
Life of this patent
Estimating the term…
Abstract
A convergent/divergent nozzle (14) has five trains of flaps. Each train is comprised of an inboard (26) and outboard (20) convergent flap, an inboard (48) and outboard (44) divergent flap and an external flap (62). The five external flaps (62) maintain their symmetry while vectoring, whereby overlapping of adjacent flaps is obtained. The inboard and outboard convergent flaps are individually driven (32,36) by a common unison ring (28).
Claims13
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising:
- a static structure for axial flow of gas therethrough;
- a plurality of outboard flap supports on said static structure;
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports;
- a plurality of inboard flap supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said inboard convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith;
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports;
- a plurality of outboard divergent flaps universally secured to the aft end of said outboard convergent flaps;
- a plurality of inboard divergent flaps universally secured to the aft end of said inboard convergent flaps;
- a plurality of overlapping external flaps;
- a plurality of support links, each support link pivotally secured to one of said external flaps at one end and pivotally secured to one of said outboard convergent flaps and inboard convergent flaps at the other end;
- and
- divergent drive means for positioning said external flaps.
9 more elements
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising:
- a static structure for axial flow of gas therethrough;
- plurality of outboard flap supports On said static structure;
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports:
- a plurality of inboard flap supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said inboard convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith:
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports:
- a plurality of outboard divergent flaps universally secured to the aft end of said outboard convergent flaps:
- a plurality of inboard divergent flaps universally secured to the aft end of said inboard convergent flaps;
- a plurality of overlapping external flaps:
- a plurality of support links pivotally secured to one of said external flaps and to one of said outboard convergent and said inboard convergent flaps:
- divergent drive means for positioning said external flaps:
- and
- said throat drive means comprising,
- a convergent unison ring surrounding said static structure,
- at least three actuators for axially positioning said convergent unison ring, an inboard flap link from said ring to each of said inboard convergent flaps and an outboard flap link from said ring to each of said outboard convergent flaps.
12 more elements
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising:
- a static structure for axial flow of gas therethrough;
- a plurality of outboard flap supports on said static structure;
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports;
- a plurality of inboard flap supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said inboard convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith;
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports;
- a plurality of outboard divergent flaps universally secured to the aft end of said outboard convergent flaps;
- a plurality of inboard divergent flaps universally secured to the aft end of said inboard convergent flaps;
- a plurality of overlapping
- a plurality of support links pivotally secured to one of said external flaps and to one of said outboard convergent and said inboard convergent flaps;
- divergent drive means for positioning said external flaps;
- and
- the aft end of said divergent flaps slidably pinned to the aft end of said external flaps.
10 more elements
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising;
- a static structure for axial flow of gas therethrough;
- a plurality of outboard flap supports on said static structure;
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports:
- a plurality of inboard flap supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said in board convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith;
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports;
- a plurality of outboard divergent flaps universally secured to the aft end of said outboard convergent flaps;
- a plurality of inboard divergent flaps universally secured to the aft end of said inboard convergent flaps;
- a plurality of overlapping external flaps;
- a plurality of support links pivotally secured to one of said external flaps and to one of said outboard convergent and said inboard convergent flaps;
- divergent drive means for positioning said external flaps;
- the aft end of said divergent flaps slidably pinned to the aft end of said external flaps:
- a slot located at the aft end of each external flap;
- a pin located at the aft end of each divergent flap;
- and
- said slot curved to maintain an opening between the aft end of said divergent flaps and said external flaps.
13 more elements
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising:
- a static structure for axial flow of gas therethrough;
- a plurality of outboard flap supports on said static structure:
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports:
- a plurality of inboard flap supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said inboard convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith;
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports;
- a plurality of outboard divergent flaps, universally secured to the aft end of said outboard convergent flaps:
- a plurality of inboard divergent flaps universally secured to the aft end of said inboard convergent flaps:
- a plurality of overlapping external flaps;
- a plurality of support links pivotally secured to one of said external flaps and to one of said outboard convergent and said inboard convergent flaps:
- divergent drive means for positioning said external flaps;
- a center point located on a central axis through said static structure;
- said divergent drive means including a divergent drive ring pivotable around said center point;
- and
- said support links located such that an extension of said links extends through said center point in the unvectored nozzle position.
12 more elements
An axisymmetric vectoring convergent/divergent nozzle for a gas turbine engine, comprising:
- a static structure for axial flow of gas therethrough;
- a plurality of outboard flap supports on said static structure;
- a plurality of N outboard convergent flaps, each pivotally supported on one of said outboard flap supports;
- a plurality of inboard flap Supports on said static structure;
- a plurality of N inboard convergent flaps, each pivotally supported on one of said inboard flap supports, said inboard convergent flaps located between adjacent outboard convergent flaps on the inboard side thereof in sealing contact therewith:
- throat drive means for simultaneously rotating said outboard convergent flaps and said inboard convergent flaps around their respective supports:
- a plurality of outboard divergent flaps universally secured to the aft end of said outboard convergent flaps;
- a plurality of overlapping external flaps;
- a plurality of support links pivotally secured to one of said external flaps and to one of said outboard convergent and said inboard convergent flaps:
- divergent drive means for positioning said external flaps:
- a center point located on a central axis through said static structure;
- said divergent drive means including a divergent drive ring pivotable around said center point;
- said support links located such that an extension of said links extends through said center point in the unvectored nozzle position;
- said static structure having a section with a spherical outer surface;
- said divergent drive ring having a cylindrical inside surface and surrounding said spherical portion of said static structure;
- and
- the center of said spherical surface being said center point toward which said supports are aligned.
14 more elements
Dependencies are inferred from the claim text.