초록

A bracket for attaching a liner to the divergent flaps and seals in a gas turbine engine convergent/divergent nozzle includes a rivet connection. There is clearance between a rivet and an opening in the bracket. This clearance allows for thermal expansion in both an axial and a radial invention.

대표청구항 ▼

What is claimed is: 1. A nozzle assembly for a gas turbine engine comprising: a plurality of divergent flaps that are movable to adjust a cross-sectional area of an outlet of a nozzle; a plurality of convergent flaps and seals positioned upstream from said divergent flaps, said convergent flaps and

What is claimed is: 1. A nozzle assembly for a gas turbine engine comprising: a plurality of divergent flaps that are movable to adjust a cross-sectional area of an outlet of a nozzle; a plurality of convergent flaps and seals positioned upstream from said divergent flaps, said convergent flaps and seals being positioned to block flow of products of combustion from a location radially inwardly of said plurality of convergent flaps and seals to an internal housing radially outwardly of said convergent flaps and seals; and said convergent flaps and seals being connected to a liner facing inwardly and toward products of combustion, said liner being attached to said rear flaps and seals by a bracket, said bracket being attached to said liner by a separate mechanical fastener, said separate mechanical fasteners extending from one side of said liner, through an opening in said liner, through an opening in said bracket, and there being clearance between an outer periphery of said separate mechanical fastener and an inner periphery of said opening in said bracket, said clearance being greater in a first direction generally along an axis of said nozzle than in a direction taken perpendicular to said first direction. 2. The nozzle assembly as set forth in claim 1, wherein said mechanical fasteners are rivets. 3. The nozzle assembly as set forth in claim 2, wherein a separate collar is positioned on said rivet, and extending through said opening in said bracket, an outer periphery of said separate collar being spaced from an inner surface of said opening in said bracket by a greater dimension in said first direction than it is spaced from an inner surface periphery of said opening of said bracket in said second direction. 4. The nozzle assembly as set forth in claim 3, wherein said collar having a generally cylindrical boss portion extending along a cylindrical portion of said rivet. 5. The nozzle assembly as set forth in claim 4, wherein said cylindrical boss portion of said collar abutting an inner face of said liner. 6. The nozzle assembly as set forth in claim 3, wherein a radially inner face of said separate collar is spaced from a radially outer face of said bracket to ensure a loose fit for thermal expansion. 7. The nozzle assembly as set forth in claim 1, wherein the clearance between said opening in said bracket and said separate mechanical fastener being greater than a clearance between said separate mechanical fastener and said opening in said liner. 8. A gas turbine engine comprising: a fan section; a compressor section; a combustion section; a turbine section; and a nozzle section, said nozzle including a plurality of divergent flaps that are movable to adjust a cross-sectional area of an outlet of a nozzle; a plurality of convergent flaps and seals positioned upstream from said divergent flaps, said convergent flaps and seals being positioned to block flow of products of combustion from a location radially inwardly of said plurality of convergent flaps and seals to an internal housing radially outwardly of said convergent flaps and seals, said convergent flaps and seals being connected to a liner facing inwardly and toward products of combustion, said liner being attached to said convergent flaps and seals by a bracket, said convergent flaps and seals being connected to a liner facing inwardly and toward products of combustion, said liner being attached to said rear flaps and seals by a bracket, said bracket being attached to said liner by a separate mechanical fastener, said separate mechanical fasteners extending from one side of said liner, through an opening in said liner, through an opening in said bracket, and there being clearance between an outer periphery of said separate mechanical fastener and an inner periphery of said opening in said bracket, said clearance being greater in a first direction generally along an axis of said nozzle than in a direction taken perpendicular to said first direction. 9. The gas turbine engine as set forth in claim 8, wherein said mechanical fasteners are rivets. 10. The gas turbine engine as set forth in claim 9, wherein a separate collar is positioned on said rivet, and extending through said opening in said bracket, an outer periphery of said separate collar being spaced from an inner surface of said opening in said bracket by a greater dimension in said first direction than it is spaced from an inner surface periphery of said opening of said bracket in said second direction. 11. The gas turbine engine as set forth in claim 10, wherein said collar having a generally cylindrical boss portion extending along a cylindrical portion of said rivet. 12. The gas turbine engine as set forth in claim 11, wherein said cylindrical boss portion of said collar abutting an inner face of said liner. 13. The gas turbine engine as set forth in claim 10, wherein a radially inner face of said separate collar is spaced from a radially outer space of said bracket to provide room for thermal expansion. 14. The gas turbine engine as set forth in claim 8, wherein the clearance between said opening in said bracket and said separate mechanical fastener being greater than a clearance between said separate mechanical fastener and said opening in said liner.