Slider for chocking a dovetail root of a blade of a gas turbine engine
A slider for chocking a dovetail root of a blade of a gas turbine engine in a corresponding axially-extending slot in the rim of a disc. The slider, in use, is slidingly inserted in an axially-extending cavity formed in the base of the root and in the disc at the base of the slot to urge the blade radially outwardly and thereby mate flanks of the root to flanks of the slot. The slider is arc-shaped and the cavity is correspondingly arc-shaped. The normal to the plane of the arc of the arc-shaped cavity is substantially perpendicular to the engine axis such that, when inserted in the cavity, the slider also retains the root axially in the slot.
1. A rotor assembly of a gas turbine engine, the assembly comprising:
a disc;
a circumferential row of blades, each of the blades having a dovetail root which is retained in a corresponding axially-extending slot in a rim of the disc;
a circumferentially-extending row of axially-extending arc-shaped cavities, each of the cavities being formed in a base of a respective one of the dovetails roots and in the disc at a base of the corresponding axially-extending slot; and
a circumferential row of correspondingly arc-shaped sliders, each of the arc-shaped sliders being slidingly inserted in a corresponding one of the axially-extending arc-shaped cavities,
wherein each of the axially-extending arc-shaped cavities has at least one upper cavity portion formed in the respective one of the dovetail roots and at least one lower cavity portion formed in the disc at the base of the corresponding axially-extending slot.
2. The rotor assembly according to claim 1 , wherein the normal to the plane of the arc of each of the axially-extending arc-shaped cavities is substantially perpendicular to the engine axis and to the radial direction.
3. The rotor assembly according to claim 1 , wherein a concave side of each of the axially-extending arc-shaped cavities faces radially outwardly.
4. The rotor assembly according to claim 3 , each of the axially-extending arc-shaped cavities has two upper cavity portions formed in ends of the root and a single lower cavity portion formed at a center of the base of the slot.
5. The rotor assembly according to claim 1 , wherein a concave side of each of the axially-extending arc-shaped cavities faces radially inwardly.
6. The rotor assembly according to claim 5 , each of the axially-extending arc-shaped cavities has two lower cavity portions formed in ends of the base of the slot and a single upper cavity portion formed at a center of the root.
7. The rotor assembly according to claim 1 , wherein each of the arc-shaped sliders has a relatively compliant outer layer for enhanced contact of each of the arc-shaped sliders with the respective root.
8. The rotor assembly according to claim 1 , wherein each of the arc-shaped sliders has a relatively compliant inner layer for enhanced contact of each of the arc-shaped sliders with the disc.
9. The rotor assembly according to claim 1 , wherein each of the arc-shaped sliders has a low friction coating at the innermost and/or outermost surface thereof.
10. The rotor assembly according to claim 1 , wherein each of the arc-shaped sliders has a stop at an end thereof which, in use, abuts a face of the disc or the root when the slider is fully inserted in the respective arc-shaped cavity to prevent over-insertion of the slider.
11. The rotor assembly according to claim 1 , wherein each of the arc-shaped sliders contains one or more pockets filled with vibration damping material.
12. The rotor assembly according to claim 1 , further comprising one or more chock springs which are arranged to act, in use, on the disc at the base of the slot to urge the blade radially outwardly.
13. A gas turbine engine including a rotor assembly, the rotor assembly comprising:
a disc;
a circumferential row of blades, each of the blades having a dovetail root which is retained in a corresponding axially-extending slot in a rim of the disc;
a circumferentially-extending row of axially-extending arc-shaped cavities, each of the cavities being formed in a base of a respective one of the dovetails roots and in the disc at a base of the corresponding axially-extending slot; and
a circumferential row of correspondingly arc-shaped sliders, each of the arc-shaped sliders being slidingly inserted in a corresponding one of the axially-extending arc-shaped cavities,
wherein each of the axially-extending arc-shaped cavities has at least one upper cavity portion formed in the respective one of the dovetail roots and at least one lower cavity portion formed in the disc at the base of the corresponding axially-extending slot.
14. The gas turbine engine according to claim 13 , wherein the normal to the plane of the arc of each of the axially-extending arc-shaped cavities is substantially perpendicular to the engine axis and to the radial direction.
15. The gas turbine engine according to claim 13 , wherein a concave side of each of the axially-extending arc-shaped cavities faces radially outwardly.
16. The gas turbine engine according to claim 15 , each of the axially-extending arc-shaped cavities has two upper cavity portions formed in ends of the root and a single lower cavity portion formed at a center of the base of the slot.
17. The gas turbine engine according to claim 13 , wherein a concave side of each of the axially-extending arc-shaped cavities faces radially inwardly.
18. The gas turbine engine according to claim 17 , each of the axially-extending arc-shaped cavities has two lower cavity portions formed in ends of the base of the slot and a single upper cavity portion formed at a center of the root.