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  Method and apparatus for increasing a durability of a bodyUSPTO Application #: 20070117480Title: Method and apparatus for increasing a durability of a body Abstract: An inseparable assembly includes a body including a ceramic matrix composite material, and a cover including a metallic wire mesh. The cover is bonded to the body so that the cover overlaps at least a portion of the body. (end of abstract) Agent: David E. Crawford, Jr. Sonnenschein Nath & Rosenthal - Chicago, IL, US Inventors: Douglas M. Carper, Michael L. Millard USPTO Applicaton #: 20070117480 - Class: 442006000 (USPTO) Related Patent Categories: Fabric (woven, Knitted, Or Nonwoven Textile Or Cloth, Etc.), Scrim (e.g., Open Net Or Mesh, Gauze, Loose Or Open Weave Or Knit, Etc.), Woven Scrim, Metal Or Metal-coated Fiber-containing Scrim The Patent Description & Claims data below is from USPTO Patent Application 20070117480. Brief Patent Description - Full Patent Description - Patent Application Claims
BACKGROUND OF THE INVENTION [0001] The present invention relates generally to ceramic matrix composite materials, and more specifically to a method and apparatus for increasing a durability of a ceramic matrix composite material. [0002] Gas turbine engines typically include a compressor, a combustor, and a turbine. Airflow entering the compressor is compressed and channeled to the combustor, wherein the air is mixed with a fuel and ignited within a combustion chamber to produce combustion gases. The combustion gases are channeled to a turbine that extracts energy from the combustion gases for powering the compressor. One turbine extracts energy from the combustion gases to power the compressor. Other turbines may be used to power an output shaft connected to a load, such as an electrical generator. In some applications, the combustion gases exiting the turbine(s) are channeled through an engine exhaust nozzle to produce thrust for propelling an aircraft in flight. [0003] Some known gas turbine aircraft engines include an engine exhaust nozzle having a variable geometry configuration, wherein a cross-sectional area of the exhaust nozzle is adjustable. Variable geometry exhaust nozzles typically have a plurality of flaps and a plurality of seals mounted circumferentially about a centerline of the exhaust nozzle. The seals are mounted generally between adjacent nozzle flaps, such that the flaps and seals form a generally continuous interior surface that directs a flow of the combustion gases through the exhaust nozzle. As their name implies, the seals seal the spaces between the flaps and shield various components of the exhaust nozzle from high temperatures and high thermal gradients during flow of the combustion gases therein. [0004] To facilitate extending a useful life at high temperature operation, some seals are fabricated from non-metallic composite materials, such as ceramic matrix composite materials. However, even such non-metallic materials experience wear and other damage due to the hostile operating environment in gas turbine engines. For example, the seal edges may erode due to frictional contact with the flaps as well as point contact rub caused by part deformation from the high thermal gradients the seals experience during operation. SUMMARY OF THE INVENTION [0005] In one aspect, an inseparable assembly is provided having a body including a ceramic matrix composite material, and a cover including a metallic wire mesh. The cover is bonded to the body so that the cover overlaps at least a portion of the body. [0006] In another aspect, a variable geometry exhaust nozzle is provided for a gas turbine engine having an exhaust centerline. The nozzle includes a plurality of flaps arranged around the exhaust centerline, each of the flaps having a sealing surface, and a plurality of flap seals. Each seal has a body which includes a sealing surface. The body is positioned between a pair of flaps of the plurality of flaps so that the sealing surface of the seal engages the sealing surface of at least one of the adjacent flaps. At least one of the seals has a cover including a metallic wire mesh bonded to the body with an adhesive so that the cover overlaps at least a portion of an edge of the body. [0007] In yet another aspect, a method is provided for increasing a durability of a body including a ceramic matrix composite material. The method includes the steps of positioning a cover including a metallic wire mesh over at least a portion of the body, and bonding the positioned cover to the body. [0008] Other features of the present invention will be in part apparent and in part pointed out hereinafter. BRIEF DESCRIPTION OF THE DRAWINGS [0009] FIG. 1 is a schematic of an exemplary gas turbine engine; [0010] FIG. 2 is a perspective of a portion of the gas turbine engine shown in FIG. 1 illustrating a portion of an exemplary exhaust nozzle assembly; [0011] FIG. 3 is a cross section of the exhaust nozzle assembly shown in FIG. 2 taken alone line 3-3 of FIG. 2; [0012] FIG. 4 is a perspective of an exemplary flap seal body for use with the exhaust nozzle assembly shown in FIG. 2; [0013] FIG. 5 is a perspective of the flap seal body shown in FIG. 4 after a material removal process; [0014] FIG. 6 is a cross-section of the flap seal body shown in FIG. 5 taken along line 6-6 of FIG. 5; [0015] FIG. 7 is a cross-section of the flap seal body shown in FIG. 5 taken along line 7-7 of FIG. 5; [0016] FIG. 8 is a perspective of an exemplary cover for use with the flap seal body shown in FIG. 5; [0017] FIG. 9 is a cross-section of the cover shown in FIG. 8 taken along line 9-9 of FIG. 8; and [0018] FIG. 10 is a perspective view of the flap seal body shown in FIG. 5 having a plurality of covers, such as the cover shown in FIG. 8, bonded thereto. [0019] Corresponding reference characters indicate corresponding parts throughout the several views of the drawings. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENT [0020] Referring now the to the drawings, FIG. 1 is a schematic of a gas turbine engine 20 including a fan 22, a high pressure compressor 24, and a combustor 26. The engine 20 also includes a high pressure turbine 28 and a low pressure turbine 30. The fan 22 and the turbine 30 are coupled by a first shaft 34, and the high pressure compressor 24 and the turbine 28 are coupled by a second shaft 36. In one embodiment, the engine 20 is a F414 engine commercially available from GE Aircraft Engines, Evendale, Ohio. Continue reading... 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