A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an
A retainer plate is provided for retaining a dovetail root of a fan blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a fan disc. In use, the plate locates in a cavity formed at an end of the slot such that a first side of the plate is arranged for contact with an axial end face of the dovetail root and an opposite second side of the plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. The retainer plate is a unitary component and has a layered structure including a first layer at the first side of the plate, a second layer at the second side of the plate, and an intermediate layer between the first and the second layers.
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1. A fan assembly of a gas turbine engine, the assembly having: a fan disc;a circumferential row of fan blades, each fan blade having a dovetail root which is retained in a corresponding axially-extending slot in a rim of the fan disc; each slot having a cavity formed at an end of the slot; anda cir
1. A fan assembly of a gas turbine engine, the assembly having: a fan disc;a circumferential row of fan blades, each fan blade having a dovetail root which is retained in a corresponding axially-extending slot in a rim of the fan disc; each slot having a cavity formed at an end of the slot; anda circumferential row of first retainer plates, each first retainer plate having a layered structure including a first layer at a first side of the first retainer plate, a second layer at a second side of the first retainer plate, and an intermediate layer between the first and the second layers, the first, intermediate and second layers being formed of different materials each having a different Young's Modulus, and the Young's moduli of the first and intermediate layers being less than the Young's Modulus of the second layer;wherein each first retainer plate is located in a respective one of the cavities such that the first side of the first retainer plate is arranged for contact with an axial end face of the respective dovetail root and the opposite second side of the first retainer plate is arranged for contact with an abutment surface of the cavity to limit axial movement of the root along the slot. 2. A fan assembly according to claim 1 which further has: a further cavity formed at an axially opposite end of each axially-extending slot;a circumferential row of second retainer plates,each second retainer plate having a layered structure including a first layer at the first side of the second retainer plate, a second layer at the second side of the second retainer plate, and an intermediate layer between the first and the second layers, the first, intermediate and second layers being formed of different materials each having a different Young's Modulus, and the Young's moduli of the first and intermediate layers being less than the Young's Modulus of the second layer;wherein each second retainer plate is located in a respective one of the further cavities such that the first side of the second retainer plate is arranged for contact with an axial end face of the respective dovetail root and the opposite second side of the second retainer plate is arranged for contact with an abutment surface of the further cavity to limit axial movement of the root along the slot. 3. A fan assembly according to claim 1, wherein the abutment surface of each cavity is formed as a pair of abutment surface portions which extend along respective circumferentially-spaced edges of the respective retainer plate. 4. A fan assembly according to claim 1, wherein each first retainer plate has a circumferentially extending groove for location therein of a support ring, wherein the circumferential row of first retainer plates is supported by a respective support ring which locates in the circumferentially extending grooves of the first retainer plates of the row. 5. A fan assembly according to claim 2, wherein each second retainer plate has a circumferentially extending groove for location therein of a support ring, wherein the circumferential row of second retainer plates is supported by a respective support ring which locates in the circumferentially extending grooves of the second retainer plates of the row. 6. A fan assembly according to claim 1, wherein each fan blade is radially outwardly chocked in its slot by a respective slider inserted into the slot radially inwardly of the dovetail root. 7. A fan assembly according to claim 6, wherein the slider carries a spring element which urges the fan blade radially outwardly. 8. A fan assembly according to claim 1, wherein at least the dovetail roots of the fan blades are formed of polymer matrix, fibre reinforced, composite material. 9. A gas turbine engine having the fan assembly of claim 1. 10. A fan assembly according to claim 1, wherein in each first retainer plate the first layer forms a barrier to galvanic corrosion between the dovetail root and the intermediate and second layers of the first retainer plate. 11. A fan assembly according to claim 1, wherein in each first retainer plate the second layer is curved to give the second side a concave outer face. 12. A fan assembly according to claim 1, wherein in each first retainer plate the layered structure further includes a crush layer which is permanently crushable at a lower compressive stress than that of the second layer. 13. A fan assembly according to claim 1, wherein in each first retainer plate the layered structure further includes an additional layer between the intermediate and the second layers, the Young's moduli of the first and intermediate layers also being less than the Young's Modulus of the additional layer. 14. A fan assembly according to claim 13, wherein in each first retainer plate the additional layer is spaced from the second layer.
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이 특허에 인용된 특허 (3)
Szpunar Stephen J. (West Chester OH) Bulman David E. (Cincinnati OH), Bladed disk assembly.
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