Retaining ring

Abstract

A retaining ring assembly for a gas turbine engine. The retaining ring assembly may include a discontinuous ring member having first and second portions of reduced cross-sectional area. The second portion may be configured to overlap the first portion. Further, the first and second portions may each include a transition portion configured to transition from a main portion of the ring member to a respective one of the first and second portions. Also, each transition portion may include a rounded fillet extending along the length of the transition portion.

What is claimed is:  
     
         1 . A retaining ring assembly for a gas turbine engine, comprising:
 a discontinuous ring member having first and second portions of reduced cross-sectional area, the second portion being configured to overlap the first portion;   wherein the first and second portions each include a transition portion configured to transition from a main portion of the ring member to a respective one of the first and second portions; and   wherein each transition portion includes a rounded fillet extending along the length of the transition portion.   
     
     
         2 . The retaining ring assembly of  claim 1 , wherein each of the rounded fillets includes a radius of curvature greater than about 0.400 inches. 
     
     
         3 . The retaining ring assembly of  claim 2 , wherein each of the rounded fillets includes a radius of curvature of about 0.500 inches. 
     
     
         4 . The retaining ring assembly of  claim 1 , wherein the rounded fillet is continuously curved and devoid of any angle or taper. 
     
     
         5 . The retaining ring assembly of  claim 1 , wherein the ring member is biased radially outward when positioned within the gas turbine engine. 
     
     
         6 . The retaining ring assembly of  claim 1 , wherein the ring member is comprised of a material configured to thermally expand and contract. 
     
     
         7 . The retaining ring assembly of  claim 6 , wherein the material includes Waspaloy®. 
     
     
         8 . The retaining ring assembly of  claim 1 , wherein each of the first and second portions are configured to move relative to one another. 
     
     
         9 . A turbine engine assembly, comprising:
 a rotary shaft;   a plurality of turbine blades including a corresponding plurality of axially extending arms having retention portions; and   a retaining ring configured for receipt within the retention portion of each of the plurality of turbine blades, the retaining ring including:
 a discontinuous ring member having first and second portions of reduced cross-sectional area, the second portion being configured to overlap the first portion; 
 wherein the first and second portions each include a transition portion configured to transition from a main portion of the ring member to a respective one of the first and second portions; and 
 wherein each transition portion includes a rounded fillet. 
   
     
     
         10 . The assembly of  claim 9 , wherein each of the rounded fillets includes a radius of curvature greater than about 0.400 inches. 
     
     
         11 . The assembly of  claim 10 , wherein each of the rounded fillets includes a radius of curvature of about 0.500 inches. 
     
     
         12 . The assembly of  claim 9 , wherein the ring member is biased radially outward when positioned in the turbine engine. 
     
     
         13 . The assembly of  claim 9 , wherein the ring member is comprised of a material configured to thermally expand and contract. 
     
     
         14 . The assembly of  claim 13 , wherein the material includes Waspaloy®. 
     
     
         15 . The assembly of  claim 9 , wherein the retaining ring and the plurality of arms are configured to cooperate so as to maintain an alignment of the plurality of turbine blades within the rotary shaft. 
     
     
         16 . The assembly of  claim 9 , wherein each of the plurality of turbine blades includes an insert configured to slide axially within a correspondingly shaped slot of a plurality of slots on the rotary shaft. 
     
     
         17 . The assembly of  claim 9 , wherein each of the first and second portions are configured to move relative to one another. 
     
     
         18 . A method of reducing stress concentration of a retaining ring within a gas turbine engine, comprising:
 operating a gas turbine engine;   radially compressing and positioning a retaining ring within the gas turbine engine, the retaining ring including a discontinuous ring member having a pair of rounded fillets;   releasing the radially compressed retaining ring within the gas turbine engine; and   decreasing a stress concentration in the retaining ring at a location adjacent to each of the pair of rounded fillets.   
     
     
         19 . The method of  claim 18 , further including:
 applying radially outward spring pressure to a plurality of turbine blades so as to maintain an axial alignment of the plurality of turbine blades.   
     
     
         20 . The method of  claim 18 , wherein each of the rounded fillets includes a radius of curvature of about 0.500 inches.