Gas turbine engine systems involving baffle assemblies
Gas turbine engine systems involving baffle assemblies are provided. In this regard, a representative baffle assembly for a gas turbine engine includes: a cooling plenum defining a cooling air path; and a baffle sized and shaped to extend between surfaces of the cooling plenum such that a cooling air path of reduced cross-section is formed between the baffle and the surfaces, the baffle being operative to increase a flow rate of cooling air as the cooling air directed to the cooling air path is redirected through the cooling air path of reduced cross-section.
1. A baffle assembly for a gas turbine engine comprising:
a first blade with a first airfoil and a first platform, the first platform between a gas path side and a non-gas path side, a first rail on the non-gas path side;
a second blade having a second airfoil and a second platform, the second platform between the gas path side and the a non-gas path side, a second rail on the non-gas path side; and
a baffle which rides on the first rail and the second rail such that a cooling air path is formed between the baffle and the respective first platform and the second platform.
2. The assembly of claim 1 , further comprising a feather seal positioned between the baffle and respective inner diameter sides of the first platform and the second platform, the feather seal operative to seal a gap between the first platform and the second platform.
3. The assembly of claim 1 , wherein:
the first platform and the second platform have cooling holes formed therethrough, the cooling holes being oriented to direct cooling air from inner diameter sides to outer diameter sides of the platforms; and
the baffle operative to route cooling air to the cooling holes.
4. The assembly of claim 1 , further comprising pin fins extend from an inner diameter side of the first platform, with at least some of the pin fins being positioned to provide structural support for the baffle.
5. The assembly of claim 1 , wherein the baffle is operative to shift position responsive to vibration of the first and second blades such that the baffle damps vibrations of the blades.
6. The assembly of claim 1 , wherein the baffle is manufactured of cobalt sheet metal.
7. The assembly of claim 1 , wherein the first rail and the second rail are located to position the baffle at a distance of between approximately 0.030 inches (0.762 mm) and approximately 0.200 inches (5.08 mm), from the underside of the platforms.
8. The assembly of claim 1 , wherein the first rail and the second rail are located to position the baffle at a distance of between approximately 0.030 inches (0.762 mm) and approximately 0.060 inches (1.524 mm) from the underside of the platforms.
9. The assembly of claim 1 , wherein the first rail and the second rail are adjacent to the respective the first platform and the second platform.
10. The assembly of claim 1 , wherein the first rail and the second rail extend from the respective the first platform and the second platform.
11. A gas turbine engine assembly comprising:
a turbine disk;
a first blade mounted to the turbine disk, the first blade having a first platform between a gas path side and a non-gas path side, a first rail on said non-gas path side;
a second blade mounted to the turbine disk, the second blade having a second platform between the gas path side and the non-gas path side, a second rail on said non-gas path side; and
a baffle which rides on the first rail and the second rail to form a cooling air path between the baffle and the first platform and the second platform.
12. The assembly of claim 11 , wherein:
the first platform has cooling holes formed therethrough; and
the baffle is operative to route cooling air to the cooling holes.
13. The assembly of claim 11 , further comprising a feather seal positioned radially outboard of the baffle the feather seal operative to seal a gap between the first platform and the second platform.
14. The assembly of claim 11 , wherein the first rail and the second rail are adjacent to an inner surface of the respective first platform and the second platform.