Composite tip shroud ring
A gas turbine engine includes a tip shroud ring rotatably supported on a last stage blade assembly in a turbine. The tip shroud ring is formed entirely of a fiber reinforced ceramic matrix composite material to provide a very light weight tip shroud ring, but also a very strong ring. The blades include pins extending from the tips, and the tip shroud ring includes holes in which the pins slide. Thus, the tip shroud ring is completely supported by the blade tip pins, and the centrifugal force developed by the rotation of the tip shroud ring does not add to the tensile force developed along the blades. Thus, the maximum rotational speed of the turbine rotor as defined by An 2 can be increased. Also, because the blade tips are secured to the tip shroud ring in a circumferential direction, the tip shroud ring acts to dampen the bladed turbine by allowing only the middle of the blade to vibrate.
1. A rotor assembly for a gas turbine engine, the rotor assembly having a rotor disc with a plurality of turbine blades extending there from, and a tip shroud ring rotatably secured to the blade tips, the rotor assembly comprising:
The blade tips each including at least one pin extending in a radial direction;
An annular shroud ring formed as a single piece and having at least one hole for each pin extending from the plurality of blade tips; and,
The pins and the holes securing the annular shroud ring against relative circumferential displacement to the blade tips while allowing for radial displacement so that a centrifugal force developed by the rotation of the tip shroud ring does not add to the tensile force developed along the blades.
2. The rotor assembly of claim 1 , and further comprising:
The annular shroud ring being formed substantially from a ceramic matrix composite material with fibers extending along the circumferential direction of the shroud ring.
3. The rotor assembly of claim 2 , and further comprising:
The ceramic matrix composite annular shroud ring is located on the last stage of the turbine.
4. The rotor assembly of claim 1 , and further comprising:
Each blade tip includes two pins; and,
The annular shroud ring includes two holes for each blade.
5. The rotor assembly of claim 1 , and further comprising:
The blade pins and the shroud ring holes allow for radial displacement of the annular shroud ring with respect to the blade tip pins.
6. A rotor assembly for a gas turbine engine comprising:
A plurality of turbine blades extending from a rotor disk;
An annular shroud ring rotatably connected to the turbine blades; and,
Blade tip to shroud ring connecting means to rotatably secure the shroud ring to the blade tips in the circumferential direction while allowing for the annular ring be displaced in the radial direction with respect to the blade tip during rotation of the rotor assembly.
7. The rotor assembly for a gas turbine engine of claim 6 , and further comprising:
The annular shroud ring being formed substantially from a ceramic matrix composite material with fibers extending along the circumferential direction of the shroud ring.
8. The rotor assembly for a gas turbine engine of claim 7 , and further comprising:
The ceramic matrix composite annular shroud ring is located on the last stage of the turbine.