A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the
A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.
대표청구항▼
1. A gas turbine engine component assembly comprising: a first component;a second component circumferentially spaced from the first component relative to an engine center axis;a first baffle associated with the first component;a second baffle associated with the second component, wherein each of the
1. A gas turbine engine component assembly comprising: a first component;a second component circumferentially spaced from the first component relative to an engine center axis;a first baffle associated with the first component;a second baffle associated with the second component, wherein each of the first and second baffles includes at least one radial baffle tab;a gap between the first and second baffles to define a cooling air inlet;a first coverplate associated with the first baffle to cover a first portion of the gap;a second coverplate associated with the second baffle to cover a second portion of the gap, wherein the first and second coverplates are separate from each other, and wherein each of the first and second coverplates includes at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates; andwherein the first and second coverplates each include at least one plate standoff extending in a radial direction opposite from the at least one coverplate radial tab. 2. The component assembly according to claim 1 wherein the at least one plate standoff and the at least one coverplate radial tab are circumferentially offset from each other. 3. The component assembly according to claim 1 wherein the first component comprises a first airfoil extending from a platform and the second component comprises a second airfoil extending from a platform. 4. The component assembly according to claim 3 wherein the first and second airfoils comprise vanes. 5. The component assembly according to claim 3 wherein the first and second baffles include a baffle surface that faces an airfoil surface, and including channels formed between the baffle and airfoil surfaces, and wherein the first and second coverplates are positioned within the gap and spaced apart from each other to define an air inlet into the channels. 6. A gas turbine engine component assembly comprising: a first component;a second component circumferentially spaced from the first component relative to an engine center axis;a first baffle associated with the first component;a second baffle associated with the second component, wherein each of the first and second baffles includes at least one radial baffle tab;a gap between the first and second baffles to define a cooling air inlet;a first coverplate associated with the first baffle to cover a first portion of the gap;a second coverplate associated with the second baffle to cover a second portion of the gap, wherein the first and second coverplates are separate from each other, and wherein each of the first and second coverplates includes at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates; andwherein a tolerance range is defined between a first set of tolerances and a second set of tolerances with a nominal tolerance condition being defined between the first and second sets of tolerances, and wherein a channel is provided between a baffle surface of the first and second baffles and a component surface of the first and second components, and wherein a nominal channel height is defined at the nominal tolerance condition, and whereinthe at least one baffle radial tab and the at least one coverplate radial tab are located at a first position relative to each other when in the nominal tolerance condition,the at least one baffle radial tab and the at least one coverplate radial tab are located at a second position wherein the coverplate radial tab is radially outward of the first position and the baffle radial tab is radially inward of the first position when at the first set of tolerances, andthe at least one baffle radial tab and the at least one coverplate radial tab are located at a third position wherein the coverplate radial tab is radially inward of the first position and the baffle radial tab is radially outward of the first position when at the second set of tolerances. 7. A gas turbine engine component assembly comprising: a first component;a second component circumferentially spaced from the first component relative to an engine center axis;a first baffle associated with the first component;a second baffle associated with the second component, wherein each of the first and second baffles includes at least one radial baffle tab;a gap between the first and second baffles to define a cooling air inlet;a first coverplate associated with the first baffle to cover a first portion of the gap;a second coverplate associated with the second baffle to cover a second portion of the gap, wherein the first and second coverplates are separate from each other, and wherein each of the first and second coverplates includes at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates; andwherein a tolerance range is defined between a first set of tolerances and a second set of tolerances with a nominal tolerance condition being defined between the first and second sets of tolerances, and wherein a plate gap is provided between the first and second coverplates, and wherein a nominal plate gap is defined at the nominal tolerance condition, and whereinthe plate gap is defined by a first distance when in the nominal tolerance condition,the plate gap is defined by a second distance that is circumferentially decreased relative to the first distance when at the first set of tolerances, andthe plate gap is defined by a third distance that is circumferentially increased relative to the first distance when at the second set of tolerances. 8. A gas turbine engine component assembly comprising: a first component;a second component circumferentially spaced from the first component relative to an engine center axis, and wherein the first component comprises a first airfoil extending from a platform and the second component comprises a second airfoil extending from a platform;a first baffle associated with the first component;a second baffle associated with the second component, wherein each of the first and second baffles includes at least one radial baffle tab;a gap between the first and second baffles to define a cooling air inlet;a first coverplate associated with the first baffle to cover a first portion of the gap;a second coverplate associated with the second baffle to cover a second portion of the gap, wherein the first and second coverplates are separate from each other, and wherein each of the first and second coverplates includes at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates;wherein the first and second baffles include a baffle surface that faces an airfoil surface, and including channels formed between the baffle and airfoil surfaces, and wherein the first and second coverplates are positioned within the gap and spaced apart from each other to define an air inlet into the channels; andwherein the coverplate radial tabs and the baffle radial tabs are positioned at different radial positions relative to each other to maintain a desired channel height throughout a tolerance range defined by the first and second airfoils. 9. The component assembly according to claim 8 wherein the air inlet varies in a circumferential direction throughout the tolerance range. 10. A gas turbine engine comprising; a compressor section defining an engine center axis; anda turbine section downstream of the compressor section, the turbine section including a plurality of vane segments that are circumferentially attached to each other to form an array of vanes, wherein at least one of the vane segments comprisesa first baffle associated with a first vane,a second baffle associated with a second vane, wherein each of the first and second baffles includes at least one baffle radial tab,a gap between the first and second baffles to define a cooling air inlet;a first coverplate associated with the first baffle to cover a first portion of the gap;a second coverplate associated with the second baffle to cover a second portion of the gap, wherein the first and second coverplates are separate from each other and each of the first and second coverplates includes at least one coverplate radial tab that cooperates with an associated baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates; andwherein each of the first and second coverplates includes a base plate extending between circumferentially spaced edges with the at least one radial plate tab extending radially outwardly from one of the edges. 11. The gas turbine engine assembly according to claim 10 wherein the first and second coverplates each include at least one plate standoff extending in a radial direction opposite from the at least one coverplate radial tab. 12. The gas turbine engine assembly according to claim 11 wherein the at least one plate standoff and the at least one coverplate plate tab are circumferentially offset from each other. 13. The gas turbine engine assembly according to claim 10 wherein associated coverplate radial tabs and baffle radial tabs are in direct abutting engagement with each other. 14. The gas turbine engine assembly according to claim 13 wherein the first and second baffles include a baffle surface that faces a vane surface, and including channels formed between the baffle and airfoil surfaces, and wherein the first and second coverplates are positioned within the gap and spaced apart from each other to define the cooling air inlet into the channels. 15. The gas turbine engine assembly according to claim 14 wherein the coverplate radial tabs and the baffle radial tabs are positioned at different radial positions relative to each other to maintain a desired channel height throughout a tolerance range defined by the first and second vanes. 16. The gas turbine engine assembly according to claim 14 wherein the cooling air inlet varies in a circumferential direction throughout the tolerance range. 17. The gas turbine engine assembly according to claim 16 wherein the cooling air inlet decreases in size relative to a nominal tolerance size when vanes are positioned circumferentially closer to each other than when the vanes are positioned at a nominal tolerance distance. 18. The gas turbine engine assembly according to claim 16 wherein the cooling air inlet increases in size relative to a nominal tolerance size when vanes are positioned circumferentially father apart from each other than when the vanes are positioned at a nominal tolerance distance.
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이 특허에 인용된 특허 (16)
McCaffrey, Michael G.; Caprario, Joseph T.; Allen, George E.; Moore, Christopher; Gagnon, Ronald R., Angled on-board injector.
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