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US 8,291,710B2 78 sealingengagementWithoneanother,andtheexitareaofthe nozzle 12 is reduced. The reduction in the exit area of the noZZle12increasesthevelocityoftheexhaustgasstreamand improvese?iciency.Theshapememorymaterialmembers38 arepositionedradiallyoutsidethecompositemember 30 and move the composite member 30 from a non-deployed posi tiontoadeployedpositiontochangetheshapeofthetab82. The composite article actuator described above may be used additionally in gas turbine engine aerofoils, e.g., com pressor blades and compressor vanes to change their shape, forthecontrolsurfacesofaircraft,e.g.,?aps,ailerons,spoil ers,etc.onaircraftWingsorcontrolof?oW of?uidsinducts, heat exchanger ?oWs, etc. What isclaimedis: 1.A gasturbineenginecomprising: anexhaustnoZZle,theexhaustnoZZlehavingadoWnstream end; at least one tab extending in a doWnstream direction from thedoWnstreamendoftheexhaustnoZZle,thetabhaving 20 a composite article, With a composite member, a ?exible member, and atleastone shapememory materialmem ber, theatleastone shapememory materialmember extending substantiallyparalleltothecompositememberandthe 25 ?exiblememberbeingpositionedbetWeenthecompos itemember andtheatleastone shapememory material membertobondtheatleastoneshapememory material member to the composite member and to maintain a separation betWeen the composite member and the at 30 least one shape memory material member, theatleastone shapememory materialmember havingan actuatortomove thetabbetWeenasecondnon-deployed position and ?rst deployed position, the composite memberopposingactuationoftheatleastoneshape 35 memory materialmember. 2.A gasturbineengineasclaimedinclaim1Whereinthe exhaust noZZle is selected from the group comprising a fan exhaust noZZle and a core exhaust noZZle. 3.A gasturbineengineasclaimedinclaim1Whereinthere 40 are heating means to heat the at least one shape memory material member such that the at least one shape memory material member moves the composite member betWeen the secondnon-deployedpositionandthe?rstdeployedposition. 4.A gasturbineengineasclaimedinclaim1Whereinthe 45 composite member has longitudinally extending ?bres in a matrixmaterial. 5.A gasturbineengineasclaimedinclaim1Whereintheat least one shape memory material member comprises a plu ralityofshapememory materialWires. 50 6.A gasturbineengineasclaimedinclaim1Whereintheat least one shape memory material member comprises a plu ralityofshapememory materialtapes. 7.A gasturbineengineasclaimedinclaim1Whereintheat leastoneshapememorymaterialmemberisembeddedinthe 55 ?exiblemember. 8.A gasturbineengineasclaimedinclaim1Whereintheat least one shape memory material member comprises at least one shape memory alloy or shape memory metal. 9.A gasturbineengineasclaimedinclaim7Whereinaheat 60 conductingmember isprovidedaroundtheatleastone shape memory materialmember. 10.A gasturbineenginecomprising: anexhaustnoZZle,theexhaustnoZZlehavingadoWnstream a composite article, With a composite member, a ?exible member, and atleastone shapememory materialmem ber, theatleastone shapememory materialmember extending substantially parallel to the composite member and the ?exiblememberbeingpositionedbetWeenthecompos itemember andtheatleastone shapememory material member tobondtheatleastone shapememory material member to the composite member and to maintain a separation betWeen the composite member and the at least one shape memory material member, the at least one shape memory material member being embedded in the ?exible member, the atleastone shape memory material member having an actuatortomove thetabbetWeenasecondnon-deployed positionand?rstdeployedposition,and a heat conducting member being provided around the shape memory material member, Wherein the heat conducting member is embedded in the ?exiblemember andextendstoanexteriorsurfaceofthe ?exiblemember. 11.A gasturbineenginecomprising: anexhaustnoZZle,theexhaustnoZZlehavingadoWnstream end; at least one tab extending in a doWnstream direction from thedoWnstreamendoftheexhaustnoZZle,thetabhaving a composite article, With a composite member, a ?exible member, and atleastone shapememory materialmem ber, theatleastone shapememory materialmember extending substantially parallel to the composite member and the ?exiblememberbeingpositionedbetWeenthecompos itemember andtheatleastone shapememory material member tobondtheatleastone shapememory material member to the composite member and to maintain a separation betWeen the composite member and the at least one shape memory material member, the atleastone shape memory material member having an actuatortomove thetabbetWeenasecondnon-deployed positionand?rstdeployedposition, the at least one shape memory material member compris ingapluralityofshapememorymaterialtapes,Wherein the shape memory material tapes are embedded in the ?exible member and a portion of each tape projects outWardly from the ?exible member to form cooling ?ns. 12.A gasturbineengineasclaimedinclaim1Whereina thermal conductor layer or a thermal insulator layer is pro vided over on atleastone shape memory material member. 13.A gasturbineengineasclaimedinclaim12Whereinthe thermalinsulatorlayerorthermalconductorlayerisarranged on the at least one shape memory material member, partially on the at least one shape memory material member and par tially on an exterior surface of the ?exible member or on an exteriorsurfaceofthe?exiblemember. 14.A gasturbineengineasclaimedinclaim1Whereinthe tabispre-stressed,thecompositememberisstressedinbend ing and the at least one shape memory material member is prestressedintensionorcompression. 15.A gasturbineengineasclaimedinclaim1Whereinthe atleastone shapememory materialmember isselectedfrom thegroupcomprisingamagneticshapememorymaterial member, anelectricshapememory materialmemory member and a heat shape memory material member. end; 65 at least one tab extending in a doWnstream direction from thedoWnstreamendoftheexhaustnoZZle,thetabhavingPDF Image | Shape Memory Material
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