Turbine blade tip clearance control device
View Patent ↗A sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of a turbine engine. The sealing system includes one or more seal lands extending from a shrouded turbine blade toward a stationary shroud of a turbine engine. During operation of the turbine engine, the seal lands straighten and extend towards the stationary shroud of the turbine engine, thereby reducing the leakage of air past the shrouded turbine blades and increasing the efficiency of the turbine engine. The sealing system may also include one or more protrusions extending from the stationary shroud towards the tips of the shrouded turbine blades.
1. A turbine engine having a sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of the turbine engine, comprising:
at least one shrouded turbine blade;
at least one seal land coupled to at least one shrouded turbine blade, the at least one seal land extending from a tip of the at least one shrouded turbine blade toward the stationary shroud of the turbine engine and having a curved configuration;
wherein the at least one seal land is adapted to straighten from a curved resting position to an operating position where a tip of the at least one seal land is closer to the stationary shroud of the turbine engine than when the turbine engine is in a resting position; and
wherein the at least one seal land is attached to the at least one shrouded turbine blade by sliding the at least one seal land into a slot in the tip of the at least one shrouded turbine blade.
2. The turbine engine of claim 1 , further comprising at least one protrusion extending from the stationary shroud toward the at least one shrouded turbine blade.
3. The turbine engine of claim 2 , wherein at least one protrusion extends circumferentially about an axis of rotation of the at least one shrouded turbine blade.
4. The turbine engine of claim 2 , wherein the at least one seal land comprises at least a first seal land and a second seal land, wherein the first seal land is positioned on the at least one shrouded turbine blade upstream of the at least one protrusion extending from the stationary shroud, and the second seal land is positioned on the at least one shrouded turbine blade downstream of the at least one protrusion extending from the stationary shroud.
5. The turbine engine of claim 1 , wherein the at least one seal land is brazed to the tip of the at least one shrouded turbine blade.
6. The turbine engine claim 1 , wherein the at least one seal land is curved into a gas flow.
7. The turbine engine of claim 1 , wherein the at least one seal land is formed from a curved bi-metallic strip.
8. The turbine engine of claim 7 , wherein the at least one seal land is formed from a first material having a first coefficient of thermal expansion and a second material having a second coefficient of thermal expansion greater than the first coefficient of the thermal expansion, wherein the first material forms the outer perimeter of the at least one seal land and the second material forms the inner perimeter of the at least one seal land.
9. A turbine engine having a sealing system for reducing a gap between a tip of a shrouded turbine blade and a stationary shroud of the turbine engine, comprising:
at least one shrouded turbine blade;
at least one seal land coupled to at least one shrouded turbine blade, the at least one seal land extending from a tip of the at least one shrouded turbine blade toward the station shroud of the turbine engine and having curd configuration;
wherein the at least one seal land is adapted to straighten from a curved resting position to an operating position where a tip of the at least one seal land is closer to the stationary shroud of the turbine engine than when the turbine engine is in a resting position; and wherein the at least one seal land is formed from a curved bi-metallic strip.
10. The turbine engine of claim 9 , wherein the at least one seal land is formed from a first material having a first coefficient of thermal expansion and a second material having a second coefficient of thermal expansion greater than the first coefficient of the thermal expansion, wherein the first material forms the outer perimeter of the at least one seal land and the second material forms the inner perimeter of the at least one seal land.
11. The scaling system turbine engine of claim 9 , further comprising at least one protrusion extending from the stationary shroud toward the at least one shrouded turbine blade.
12. The turbine engine of claim 11 wherein the at least one protrusion extends circumferentially about an axis of rotation.
13. The turbine engine of claim 11 , wherein the at least one seal land comprises at least a first seal land and a second seal land, wherein the first seal land is positioned on the at least one shrouded turbine blade upstream of the at least one protrusion extending from the stationary shroud, and the second seal land is positioned on the at least one shrouded turbine blade downstream of the at least one protrusion extending from the stationary shroud.
14. The turbine engine of claim 7 , wherein the at least one seal land is brazed to the tip of the at least one shrouded turbine blade.
15. The turbine engine of claim 9 , wherein the at least one seal land is curved into a gas flow.