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An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the v

An apparatus for attaching a transition duct to a turbine section of a gas turbine engine includes an annular shaped vane carrier that engages with a transition aft frame. The transition aft frame includes an outwardly extending clamp that is at least partially inserted into a radial recess of the vane carrier structure. A spacer is inserted into the recess. A first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess. At least one of the pairs of mating surfaces is inclined at an angle with respect to a radial plane of the vane carrier structure. A retention device secures the spacer to the vane carrier structure.

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1. An apparatus for attaching a transition duct to a turbine section of a gas turbine engine, comprising: an annular shaped vane carrier structure comprising a radial recess,a transition aft frame that engages with the vane carrier structure, the transition aft frame comprising an outwardly extendin

1. An apparatus for attaching a transition duct to a turbine section of a gas turbine engine, comprising: an annular shaped vane carrier structure comprising a radial recess,a transition aft frame that engages with the vane carrier structure, the transition aft frame comprising an outwardly extending clamp that is at least partially inserted into the recess,a spacer inserted into the recess whereby the clamp and the spacer are arranged axially adjacent to each other within the recess, wherein a first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess, wherein the first pair and/or second pair of mating surfaces are inclined at an angle with respect to a radial plane of the vane carrier structure,a retention device for securing the spacer to the vane carrier structure, the retention device comprising a radial retention bolt configured to apply an axial load on the clamp when tightened;wherein the recess has a circumferential contour that comprises at least a pair of valleys delimiting a radially outward extent of the recess, the valleys being interspaced by a radially inwardly projecting tang, wherein a radially outer end of the clamp has a shape that corresponds to the contour of the recess, whereby the tang provides a circumferential constraint of the transition aft frame to the vane carrier structure. 2. The apparatus according to claim 1, wherein the angle is in the range of 3° to 10°. 3. The apparatus according to claim 1, wherein the spacer comprises an internal threading that engages with the radial retention bolt. 4. The apparatus according to claim 1, wherein the radial retention bolt is housed in a radial clearance hole provided in the vane carrier structure. 5. The apparatus according to claim 1, wherein the radial recess is formed on a forward face of the vane carrier structure facing a flow of a working medium. 6. The apparatus according to claim 1, wherein the clamp has a further end face that mates with a further wall of the recess, wherein the further end face comprises a protrusion that engages with a groove on the further wall of the recess. 7. A gas turbine engine comprising: a combustor section for producing a working medium by combustion of a mixture of fuel and an oxidant,a turbine section located downstream of the combustor section for expanding the working medium, anda transition duct arranged fluidically between the combustor section and the turbine section, for directing the working medium from the combustor section to a first row of stationary vanes arranged on an annular vane carrier structure in the turbine section,wherein the transition duct comprises a transition aft frame that engages with the vane carrier structure,wherein vane carrier structure comprises a radial recess,wherein the transition aft frame comprises an outwardly extending clamp that is at least partially inserted into the recess,wherein a spacer is inserted into the recess whereby the clamp and the spacer are arranged axially adjacent to each other within the recess, wherein a first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess, wherein the first pair and/or second pair of mating surfaces are inclined at an angle with respect to a radial plane of the vane carrier structure,wherein the spacer is secured to the vane carrier structure by a retention device, the retention device comprising a radial retention bolt configured to apply an axial load on the clamp when tightened,wherein the recess has a circumferential contour that comprises at least a pair of valleys delimiting a radially outward extent of the recess, the valleys being interspaced by a radially inwardly projecting tang, wherein a radially outer end of the clamp has a shape that corresponds to the contour of the recess, whereby the tang provides a circumferential constraint of the transition aft frame to the vane carrier structure. 8. A method for attaching a transition duct to a turbine section of a gas turbine engine, comprising: engaging a transition aft frame comprising an outwardly extending clamp with an annular shaped vane carrier structure, such that the clamp is at least partially inserted into a radial recess provided in the vane carrier structure,inserting a spacer into the recess whereby the clamp and the spacer are arranged axially adjacent to each other within the recess, wherein a first pair of mating surfaces is formed by a first end face of the spacer and an end face of the clamp and a second pair of mating surfaces is formed by a second end face of the spacer and a wall of the recess, wherein the first pair and/or second pair of mating surfaces are inclined at an angle with respect to a radial plane of the vane carrier structure, andsecurely fastening the spacer to the vane carrier structure via a radial retention bolt configured to apply an axial load on the clamp when tightened,wherein the recess has a circumferential contour that comprises at least a pair of valleys delimiting a radially outward extent of the recess, the valleys being interspaced by a radially inwardly projecting tang, wherein a radially outer end of the clamp has a shape that corresponds to the contour of the recess, whereby the tang provides a circumferential constraint of the transition aft frame to the vane carrier structure. 9. The method according to claim 8, wherein the angle is in the range of 3° to 10°. 10. The method according to claim 8, wherein the spacer comprises an internal threading that engages with the radial retention bolt. 11. The method according to claim 8, wherein the radial retention bolt is housed in a radial clearance hole provided in the vane carrier structure. 12. The method according to claim 8, wherein the radial recess is formed on a forward face of the vane carrier structure facing a flow of a working medium. 13. The method according to claim 8, wherein the clamp is inserted into the recess such that a further end face of the clamp mates with a further wall of the recess, wherein the further end face comprises a protrusion that engages with a groove on the further wall of the recess. 14. The method according to claim 8, wherein the transition aft frame is assembled axially to the vane carrier structure to insert the clamp within the recess. 15. The method according to claim 8, wherein the spacer is inserted in a radial direction into the recess.