Turbine engine shroud assembly

Abstract

Disclosed herein is an interlocking shroud assembly for a turbine engine with a plurality of radially extending, circumferentially spaced airfoils terminating in a shroud element and having opposing radial sides with first and second interlock elements. Further provided is a method of forming a shroud about a plurality of rotating blades in a turbine engine.

What is claimed is: 
     
         1 . A turbine engine comprising:
 a rotor having a plurality of radially extending airfoils spaced circumferentially about the rotor, with the airfoils terminating in a tip; and   a shroud assembly circumscribing the airfoils and comprising a shroud element mounted to each tip and having opposing radial sides with first and second interlock elements;   wherein the first interlock element of one shroud element mates with a second interlock element of a circumferentially adjacent element to form a plurality of interlocks between adjacent shroud elements about the circumference of the airfoils.   
     
     
         2 . The turbine engine of  claim 1 , wherein the shroud element is integrally formed with the airfoil. 
     
     
         3 . The turbine engine of  claim 2 , wherein the airfoil is a blade. 
     
     
         4 . The turbine engine of  claim 3 , wherein the blade terminates in a dove tail opposite the tip and the dove tail is mounted to the rotor. 
     
     
         5 . The turbine engine of  claim 1 , wherein the airfoil is sized such that the airfoil is sprung when interlocked with adjacent airfoils to apply a preload to the interlocks. 
     
     
         6 . The turbine engine of  claim 1 , wherein the first interlock comprises a first flange, the second interlock comprises a second flange, and the first flange overlies and abuts the second flange. 
     
     
         7 . The turbine engine of  claim 6 , wherein the first interlock further comprises a seat spaced circumferentially from the first flange and the second flange sits within the seat. 
     
     
         8 . The turbine engine of  claim 7 , wherein the seat is formed by a first radial edge and the first flange. 
     
     
         9 . The turbine engine of  claim 8 , wherein the first flange projects circumferentially beyond the first radial edge. 
     
     
         10 . The turbine engine of  claim 9 , wherein the first flange is circumferentially outboard of the first radial edge. 
     
     
         11 . The turbine engine of  claim 10 , wherein the second flange is a second radial edge of an adjacent shroud element. 
     
     
         12 . The turbine engine of  claim 11 , wherein the airfoil is sized such that the airfoil is sprung when interlocked with adjacent airfoils to apply a preload to the interlocks causing the second radial edge to bias toward the first flange. 
     
     
         13 . An interlocking shroud assembly for a turbine engine comprising a plurality of radially extending, circumferentially spaced airfoils terminating in a shroud element and having opposing radial sides with first and second interlock elements, which interlock to form interlocks between circumferentially adjacent airfoils. 
     
     
         14 . The interlocking shroud assembly of  claim 13 , wherein the airfoil is sized such that the airfoil is sprung when interlocked with adjacent airfoils to apply a preload to the interlocks. 
     
     
         15 . The interlocking shroud assembly of  claim 14 , wherein the first interlock comprises a first flange, the second interlock comprises a second flange and the first flange overlies and abuts the second flange. 
     
     
         16 . The interlocking shroud assembly of  claim 15 , wherein the first interlock further comprises a seat spaced circumferentially from the first flange and the second flange sits within the seat. 
     
     
         17 . The interlocking shroud assembly of  claim 16 , wherein the seat is formed by a first radial edge and the first flange. 
     
     
         18 . The interlocking shroud assembly of  claim 17 , wherein the first flange projects circumferentially beyond the first radial edge. 
     
     
         19 . The interlocking shroud assembly of  claim 18 , wherein the first flange is circumferentially outboard of the first radial edge. 
     
     
         20 . The interlocking shroud assembly of  claim 19 , wherein the second flange is a second radial edge of an adjacent shroud element. 
     
     
         21 . A method of forming a shroud about a plurality of rotating blades in a turbine engines comprising:
 forming an interlock between circumferentially adjacent tips of the blades; and   preloading the interlock.   
     
     
         22 . The method of  claim 21 , wherein forming the interlock comprises forming an interlock on circumferentially opposite sides of the tip of the blade. 
     
     
         23 . The method of  claim 21 , wherein preloading the interlock comprises springing the blade.