Gas turbine engine turbine vane ring arrangement
A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.
1. A gas turbine engine comprising:
an engine static structure;
a compressor section;
a combustor fluidly connected downstream from the compressor section;
a turbine section fluidly connected downstream from the combustor and including high and low pressure turbine sections;
a vane pack arranged in one of the compressor or turbine sections, the vane pack including a reinforcement ring secured around an annular arrangement of vanes and extending proud of an axial end of the vanes to an end, wherein an annular arrangement of the vane pack includes vane segments having discrete platforms secured to one another circumferentially, the end interleaving with an adjacent rotating component to provide a seal; and
a sealing ring supported by the engine static structure and engaged with the reinforcement ring.
2. The gas turbine engine according to claim 1 , wherein the reinforcement ring and the vanes include interlocking features engaging one another and configured to prevent relative axial movement between the reinforcement ring and the vanes.
3. The gas turbine engine according to claim 1 , wherein the end includes an annular lip that is received in an annular pocket of the rotating component.
4. The gas turbine engine according to claim 1 , wherein the vane pack is arranged in the turbine section.
5. The gas turbine engine according to claim 1 , wherein the rotating component includes one of a pocket and a lip, the reinforcement ring providing the other of the pocket and the lip, the lip arranged in the pocket to provide the seal.
6. The gas turbine engine according to claim 5 , wherein the rotating component is a stage of rotating blades provided by the high pressure turbine section, and the vane pack provides a mid-turbine frame.
7. The gas turbine engine according to claim 1 , wherein the vanes are hung from the engine static structure.
8. The gas turbine engine according to claim 1 , wherein the reinforcement ring is secured to the vanes by at least one of a mechanical element and an interference fit.
9. The gas turbine engine according to claim 8 , wherein the mechanical element includes at least one of a braze, a weld and fasteners.
10. The gas turbine engine according to claim 8 , wherein the reinforcement ring is secured to the vanes by an interference fit.
11. The gas turbine engine according to claim 1 , wherein the reinforcement ring is secured to an inner platform provided by the discrete platforms.
12. The gas turbine engine according to claim 11 , wherein the axial end is a leading edge.