Protective device for a turbomachine

Abstract

A protective device ( 10 ) for a turbomachine, in particular a gas turbine, having a containment ring ( 12 ) which is disposed on the radially inner side of a casing element ( 14 ) of the turbomachine and which at least substantially prevents the casing element ( 14 ) from being penetrated by a fragment of a component of the turbomachine in the event of a structural failure of this component is provided. The containment ring ( 12 ) is composed, at least in the circumferential direction, of a plurality of ring segments ( 16 ) which are form-fittingly interconnected. A second aspect of the present invention relates to an aircraft engine.

What is claimed is: 
     
         1 . A protective device for a turbomachine, the protective device comprising:
 a containment ring disposed on a radially inner side of a casing element of the turbomachine, the containment ring at least substantially preventing the casing element from being penetrated by a fragment of a component of the turbomachine in the event of a structural failure of the component,   the containment ring being composed, at least in a circumferential direction, of a plurality of ring segments form-fittingly interconnected.   
     
     
         2 . The protective device as recited in  claim 1  wherein some play is provided between the individual ring segments in the circumferential direction to allow compensation for expansions of the ring segments caused by thermal loading. 
     
     
         3 . The protective device as recited in  claim 1  wherein the ring segments are form-fittingly interconnected by notched engagement and/or toothed engagement. 
     
     
         4 . The protective device as recited in  claim 1  wherein the containment ring is clamped axially by a clamp. 
     
     
         5 . The protective device as recited in  claim 4  wherein the clamping device includes at least one stator, a casing projection, a hook or a baffle at least partially engaging the containment ring axially. 
     
     
         6 . The protective device as recited in  claim 1  wherein the plurality of ring segments includes at least two rows of ring segments, with at least axially adjacent side faces of the ring segments being interconnected by a notched engagement, a toothed engagement or a staggered arrangement along the circumferential direction. 
     
     
         7 . The protective device as recited in  claim 6  wherein the at least two rows have an undulating profile along the circumferential direction at the axially adjacent side faces. 
     
     
         8 . The protective device as recited in  claim 6  wherein the at least two rows have a sawtooth profile along the circumferential direction at the axially adjacent side faces. 
     
     
         9 . The protective device as recited in  claim 6  wherein the at least two rows have corresponding shoulders along the circumferential direction at the axially adjacent side faces. 
     
     
         10 . The protective device as recited in  claim 1  wherein the ring segments have corresponding indentations or projections at contacting side faces or end faces at least in portions thereof. 
     
     
         11 . The protective device as recited in  claim 1  wherein the containment ring is disposed radially outwardly of an abradable coating. 
     
     
         12 . The protective device as recited in  claim 1  wherein the ring segments are formed from a ceramic material. 
     
     
         13 . The protective device as recited in  claim 1  wherein the ceramic material is a fiber-reinforced ceramic material, an oxide ceramic material, or a silicon carbide. 
     
     
         14 . The protective device as recited in  claim 1  wherein each ring segment extends circumferentially over 30°. 
     
     
         15 . The protective device as recited in  claim 1  wherein the containment ring is disposed radially between at least one airfoil ring of the turbomachine and the casing element. 
     
     
         16 . An aircraft engine comprising the protective device as recited in  claim 1 . 
     
     
         17 . The aircraft engine as recited in  claim 16  further comprising the component, the component being radially interior of the containment ring. 
     
     
         18 . A gas turbine comprising the protective device as recited in  claim 1 .