In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the chevrons having a root region and
In one embodiment, a gas turbine engine exhaust nozzle comprises a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface, and a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron. Other embodiments may be described.
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1. A gas turbine engine exhaust nozzle, comprising: a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface wherein the housing has a thickness that is substantially constant in cross-sectional stations forward of an aft en
1. A gas turbine engine exhaust nozzle, comprising: a housing having a length which extends along a central longitudinal axis and comprising an interior surface and an exterior surface wherein the housing has a thickness that is substantially constant in cross-sectional stations forward of an aft end of the housing; anda row of chevrons extending from the aft end of the housing, the chevrons having a root region and a tip,wherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron forming a scallop shaped region of reduced thickness relative to the rest of the chevron, andwherein the housing has a thickness that varies in cross-sectional stations proximate the root regions of the chevrons between a maximum thickness at a point along a longitudinal axis extending through the tip of each chevron to a minimum at a point along a longitudinal axis extending through the base of the chevron. 2. The gas turbine engine exhaust nozzle of claim 1, wherein: the housing comprises a contoured surface which converges toward the central longitudinal axis proximate the aft end of the housing; andthe row of chevrons follows the contoured surface such that the tip of the chevrons lie in a plane that intersects the central longitudinal axis. 3. The gas turbine engine exhaust nozzle of claim 1, wherein the chevrons measure between 10 centimeters and 60 centimeters from the base to the tip and the scalloped root regions measure between 5 and 75 centimeters in width and between 5 and 90 centimeters in length. 4. The gas turbine engine exhaust nozzle of claim 3, wherein the thickness of the housing varies between a maximum thickness of 2.5 centimeters and a minimum thickness of 0.25 centimeters. 5. The gas turbine engine exhaust nozzle of claim 4, wherein: the row of chevrons extend about the entire aft end of the housing; andthe chevrons are substantially uniform in size and shape. 6. The gas turbine engine exhaust nozzle of claim 4, wherein: the row of chevrons extend about the entire aft end of the housing; andthe chevrons vary in size and shape. 7. A gas turbine engine assembly, comprising: an engine assembly disposed about a longitudinal axis;a first housing surrounding portions of the engine assembly and having a length which extends along the longitudinal axis, an interior surface and an exterior surface, and defining a core flow aperture at an aft end of the housing, and a thickness that is substantially constant in cross-sectional stations forward of an aft end of the housing;a second housing surrounding portions of the first housing and having a length which extends along the longitudinal axis, an interior surface and an exterior surface, the exterior surface of the first housing and the interior surface of the second housing defining a fan flow aperture at an aft end of the second housing, and a thickness that is substantially constant in cross-sectional stations forward of an aft end of the housing, andwherein at least one of the first housing or the second housing comprises: a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, andwherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron forming a scallop shaped region of reduced thickness relative to the rest of the chevron, and the housing has a thickness that varies in cross-sectional stations proximate the root regions of the chevrons between a maximum thickness at a point along a longitudinal axis extending through the tip of each chevron to a minimum at a point along a longitudinal axis extending through the base of the chevron. 8. The gas turbine engine assembly of claim 7, wherein: at least one of the first housing or the second housing comprises a contoured surface which converges toward the central longitudinal axis proximate the aft end of the housing; andthe row of chevrons follows the contoured surface such that the tip of the chevrons point toward the central longitudinal axis. 9. The gas turbine engine assembly of claim 7, wherein: the chevrons measure between 10 centimeters and 60 centimeters from the base to the tip and the scalloped root regions measure between 5 and 75 centimeters in width and between 5 and 90 centimeters in length. 10. The gas turbine engine assembly of claim 7, wherein: the thickness of the housing varies between a maximum thickness of 2.5 centimeters and a minimum thickness of 0.25 centimeters. 11. The gas turbine engine assembly of claim 10, wherein: the row of chevrons extends about the entire end of the housing; andthe chevrons are substantially uniform in size and shape. 12. The gas turbine engine assembly of claim 10, wherein: the row of chevrons extends about the entire end of the housing; andthe chevrons vary in size and shape. 13. An aircraft, comprising: a fuselage;wings; anda gas turbine engine assembly, comprising: an engine assembly disposed about a longitudinal axis;a first housing surrounding portions of the engine assembly and having a length which extends along the longitudinal axis, an interior surface and an exterior surface, and defining a core flow aperture at an aft end of the housing and a thickness that is substantially constant in cross-sectional stations forward of an aft end of the housing;a second housing surrounding portions of the first housing and having a length which extends along the longitudinal axis, an interior surface and an exterior surface, the exterior surface of the first housing and the interior surface of the second housing defining a fan flow aperture at an aft end of the second housing and a thickness that is substantially constant in cross-sectional stations forward of an aft end of the housing,wherein at least one of the first housing or the second housing comprises: a row of chevrons extending from an aft end of the housing, the chevrons having a root region and a tip, andwherein at least a portion of at least one of the interior surface or the exterior surface is scalloped proximate the root region of a chevron forming a scallop shaped region of reduced thickness relative to the rest of the chevron, and the housing has a thickness that varies in cross-sectional stations proximate the root regions of the chevrons between a maximum thickness at a point along a longitudinal axis extending through the tip of each chevron to a minimum at a point along a longitudinal axis extending through the base of the chevron. 14. The aircraft of claim 13, wherein: at least one of the first housing or the second housing comprises a contoured surface which converges toward the central longitudinal axis proximate the aft end of the housing; andthe row of chevrons follows the contoured surface such that the tips of the chevrons lie in a plane that intersects the central longitudinal axis. 15. The aircraft of claim 13, wherein: the chevrons measure between 10 centimeters and 60 centimeters from the base to the tip and the scalloped root regions measure between 5 and 75 centimeters in width and between 5 and 90 centimeters in length. 16. The aircraft of claim 13, wherein: the thickness of the housing varies between a maximum thickness of 2.5 centimeters and a minimum thickness of 0.25 centimeters. 17. The aircraft of claim 16, wherein: the row of chevrons extends about the entire end of the housing; andthe chevrons are substantially uniform in size and shape. 18. The gas turbine engine assembly of claim 16, wherein: the row of chevrons extends about the entire end of the housing; andthe chevrons vary in size and shape.
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이 특허에 인용된 특허 (2)
John F. Brausch ; Bangalore A. Janardan ; John W. Barter, IV ; Gregory E. Hoff, Chevron exhaust nozzle for a gas turbine engine.
Cerra, David F.; Gea, Lie-Mine; Willie, Robert H.; Hebert, Leonard J.; Robinson, Donald E., Gas turbine engine nozzle including housing having scalloped root regions.
Szydlowski, Julien; Bodard, Guillaume; Leyko, Matthieu; Langridge, Jonathan, Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle.
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