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A spacer arrangement 1, 40 is provided in which wedges 5, 6; 45, 46 are arranged to have an interface 7, 47 between them such that a thermally variable member 8, 48 can cause relative motion between the wedges 5, 6; 45, 46 to adjust an arrangement lateral dimension dependent upon temperature. In suc

A spacer arrangement 1, 40 is provided in which wedges 5, 6; 45, 46 are arranged to have an interface 7, 47 between them such that a thermally variable member 8, 48 can cause relative motion between the wedges 5, 6; 45, 46 to adjust an arrangement lateral dimension dependent upon temperature. In such circumstances with the arrangement 1, 40 positioned within a gap 3 between a casing 14 and unison ring 13, retention of position of that unison ring 13 can be maintained. The unison ring is arranged to adjust position of variable vanes.

대표청구항 ▼

I claim: 1. A spacer arrangement for a gas turbine engine, the arrangement comprising a first wedge and a second wedge with an interface between the first wedge and the second wedges, the first and second wedges are arranged between a first component and a second component, and a thermally variable

I claim: 1. A spacer arrangement for a gas turbine engine, the arrangement comprising a first wedge and a second wedge with an interface between the first wedge and the second wedges, the first and second wedges are arranged between a first component and a second component, and a thermally variable member is arranged to act across the first wedge and the second wedge for thermally dependent displacement about the interface whereby a desired lateral dimension of the arrangement is varied for positional reaction across a gap between the first and the second components. 2. An arrangement as claimed in claim 1 wherein the thermally dependent displacement is a slide motion along the interface. 3. An arrangement as claimed in claim 1 wherein the thermally dependent displacement is a divergent separation across the interface. 4. An arrangement as claimed in claim 1 wherein the lateral dimension varied is between respective surfaces of the first wedge and the second wedge either side of the interface. 5. An arrangement as claimed in claim 1 wherein the lateral dimension varied is between the surfaces of the first wedge and the second wedge at either end of the interface. 6. An arrangement as claimed in any claim 1 wherein the thermally variable member is entrant within the interface. 7. An arrangement as claimed in claim 1 wherein the thermally variable member is keyed into reciprocal recesses of the interface. 8. An arrangement as claimed in claim 7 wherein the thermally variable member has a dumb-bell shape. 9. An arrangement as claimed in claim 1 wherein the thermally variable member is selected from the group comprising a high co-efficient of thermal expansion material and a shape memory alloy. 10. An arrangement as claimed in claim 1 wherein the thermally variable member is a band secured either side of the arrangement and extending about one end of the arrangement to engage one of the first wedge or the second wedge. 11. An arrangement as claimed in claim 10 wherein the band is a bi-metallic strip anchored either side of the arrangement. 12. An arrangement as claimed in claim 1 wherein the first and second wedge is formed from a low co-efficient of thermal expansion material. 13. An arrangement as claimed in claim 1 wherein one wedge is arranged to be fixed to a structure whilst the other is arranged to be allowed to slide upon the interface and/or relative to a component. 14. A vane assembly for a gas turbine engine wherein that vane assembly incorporates a spacer arrangement as claimed in claim 1. 15. A vane assembly as claimed in claim 14 wherein the vane assembly comprises a plurality of vanes, the vanes have spindles, the spindles extend through apertures in a casing, a unison ring is arranged around the casing, the vanes of the vane assembly are variable in orientation by rotation of the spindles in apertures in the casing utilising a unison ring. 16. An assembly as claimed in claim 15 wherein the spacer arrangement is utilised between the unison ring and the casing in order to control the effective gap between the casing and the unison ring. 17. A gas turbine engine incorporating a spacer arrangement as claimed in claim 1. 18. A gas turbine engine as claimed in claim 17 wherein the gas turbine engine incorporates a casing and a unison ring with the arrangement provided to ensure consistent relative positioning of the unison ring within the gas turbine engine.