Blade clearance system for a turbine engine
View Patent ↗A blade gap control system configured to move a blade ring of a turbine engine relative to a blade assembly to reduce the gaps between the tips of the blades and the blade rings to increase the efficiency of the turbine engine is provided. The blade rings can be at an acute angle with respect to the rotational axis of the blade assembly. The axial movement of the blade ring can be done by a pressure differential supplied across the blade ring, the thermal expansion and/or contraction of a linkage or by a piston.
1. A blade clearance control system for a turbine engine having an outer casing and a rotor assembly, the system comprising:
a blade ring concentric with the rotor assembly and positioned radially outward from blade tips of the rotor assembly, the blade ring having a radially inner wall that is radially outward of the blade tips to define a gap therebetween; and
one or more plenums positioned upstream and downstream of the blade ring, the one or more plenums being selectively pressurized to move the blade ring relative to the blade tips to adjust the gap;
wherein the radially inner wall of the blade ring is oblique to a rotational axis of the rotor assembly, and
wherein the one or more plenums move the blade ring axially relative to the blade tips to adjust the gap.
2. The system of claim 1 , further comprising at least one guide pin, wherein the blade ring has a post that is slideably connected to the guide pin.
3. The system of claim 1 , wherein the one or more plenums are defined in part by a radially outer wall of the blade ring.
4. The system of claim 1 , wherein the blade ring comprises a plurality of blade ring segments.
5. The system of claim 1 , wherein the one or more plenums are first and second plenums, wherein the blade ring has a post that is slideably connected to the outer casing, and wherein the first and second plenums are selectively pressurized to move the blade ring axially relative to the blade tips to adjust the gap.
6. The system of claim 1 , wherein the radially inner wall of the blade ring is at an acute angle with respect to the rotational axis and is substantially equal to a tip angle defined by the blade tips and the rotational axis.
7. The system of claim 1 , wherein the blade clearance control system is in the compressor section of the turbine engine.
8. A turbine engine comprising:
an outer casing;
a blade assembly formed from at least one row of blades extending radially from a rotor, wherein the at least one row is formed from a plurality of blades having blade tips;
one or more blade rings positioned radially outward of the blade assembly, wherein a radially inner wall of each of the one or more blade rings is offset radially outward from the blade tips creating gaps and wherein the one or more blade rings are positioned at an acute angle with respect to a rotational axis of the blade assembly; and
a gap control system having a first linkage that thermally expands or contracts to move the one or more blade rings axially relative to the blade tips to adjust the gaps.
9. The turbine engine of claim 8 , wherein the gap control system has a second linkage, wherein the first linkage is pivotally connected at one end to the outer casing and at the other end to the second linkage.
10. The turbine engine of claim 9 , wherein the second linkage amplifies the thermal expansion or contraction of the first linkage.
11. The turbine engine of claim 8 , further comprising at least one guide pin, wherein the one or more blade rings slide along the at least one guide pin.
12. The turbine engine of claim 11 , wherein the one or more blade rings have a post that is slideably connected to the at least one guide pin.
13. The turbine engine of claim 8 , wherein the first linkage is a high alpha material.
14. The turbine engine of claim 8 , wherein the first linkage is a shape memory alloy.
15. The turbine engine of claim 8 , wherein the one or more blade rings comprise a plurality of blade ring segments each having the first linkage that thermally expands to move the plurality of blade ring segments axially relative to the blade tips to adjust the gaps.
16. The turbine engine of claim 8 , wherein the gap control system adjusts the gaps in a compressor section of the turbine engine.
17. A method of blade clearance control in a gas turbine comprising:
positioning a blade ring concentric with a rotor assembly and radially outward from blade tips of the rotor assembly,
positioning a radially inner wall of the blade ring oblique to a rotational axis of the rotor assembly, the radially inner wall being radially outward of the blade tips to define a gap therebetween; and
supplying a pressurized fluid to the blade ring to selectively create a pressure differential across a portion of the blade ring, the pressure differential moving the blade ring relative to the blade tips to adjust the gap;
aligning the radially inner wall of the blade ring and the blade tips at a substantially equal acute angle with respect to the rotational axis of the rotor assembly.
18. The method of claim 17 , further comprising slideably connecting the blade ring to an outer casing of the gas turbine.