Turbine shroud for a turbomachine

Abstract

A turbine shroud includes a body having an upstream edge, a downstream edge, and first and second side edges that collectively define a flowpath surface. A first interface member is arranged on the upstream edge at the first side edge. The first interface member includes a first edge portion having an end portion that extends out at a first non-perpendicular angle relative to the upstream edge and the first side edge from the flowpath surface to a second end portion. A second interface member is arranged on the upstream edge at the second side edge. The second interface member includes an edge section having an end section that extends into at a second non-perpendicular angle relative to the upstream edge and the second side edge the flowpath surface to a second end section.

What is claimed is: 
     
         1 . A turbine shroud comprising:
 a body including an upstream edge, a downstream edge, and first and second side edges that collectively define a flowpath surface;   a first interface member arranged on the upstream edge at the first side edge, the first interface member including a first edge portion having a first end portion that extends out at a first non-perpendicular angle relative to the upstream edge and the first side edge from the flowpath surface to a second end portion, and a second edge portion that extends from the second end portion of the first edge portion to the first side edge; and   a second interface member arranged on the upstream edge at the second side edge, the second interface member including a first edge section having a first end section that extends into at a second non-perpendicular angle relative to the upstream edge and the second side edge the flowpath surface to a second end section, and a second edge section that extends from the second end section of the first edge section to the second side edge.   
     
     
         2 . The turbine shroud according to  claim 1 , wherein the second edge portion is substantially parallel to the upstream edge. 
     
     
         3 . The turbine shroud according to  claim 1 , wherein the second edge section is substantially parallel to the upstream edge. 
     
     
         4 . The turbine shroud according to  claim 1 , further comprising: a seal slot formed in first side edge. 
     
     
         5 . The turbine shroud according to  claim 4 , further comprising: a seal positioned in the seal slot, the seal extending circumferentially outwardly from the first side edge. 
     
     
         6 . The turbine shroud according to  claim 1 , wherein the first interface member is configured and disposed to receive a second interface member from an adjacent turbine shroud to form an angled slashface interface between the turbine shroud and the adjacent turbine shroud. 
     
     
         7 . The turbine shroud according to  claim 1 , wherein the first non-perpendicular angle is complementary to the second non-perpendicular angle. 
     
     
         8 . A turbomachine comprising:
 a turbine portion including a casing defining a hot gas path;   a plurality of turbine blades rotatably mounted in the turbine portion along the hot gas path, the each of the plurality of turbine blades including a tip portion;   at least one turbine shroud mounted to the casing and spaced from the tip portion of each of the plurality of turbine blades, the at least one turbine shroud comprising:
 a body including an upstream edge, a downstream edge, and first and second side edges that collectively define a flowpath surface; 
 a first interface member arranged on the upstream edge at the first side edge, the first interface member including a first edge portion having a first end portion that extends out at a first non-perpendicular angle relative to the upstream edge and the first side edge from the flowpath surface to a second end portion, and a second edge portion that extends from the second end portion of the first edge portion to the first side edge; and 
 a second interface member arranged on the upstream edge at the second side edge, the second interface member including a first edge section having a first end section that extends into at a second non-perpendicular angle relative to the upstream edge and the second side edge the flowpath surface to a second end section, and a second edge section that extends from the second end section of the first edge section to the second side edge. 
   
     
     
         9 . The turbomachine according to  claim 8 , wherein the second edge portion is substantially parallel to the upstream edge. 
     
     
         10 . The turbomachine according to  claim 8 , wherein the second edge section is substantially parallel to the upstream edge. 
     
     
         11 . The turbomachine according to  claim 8 , further comprising: a seal slot formed in first side edge. 
     
     
         12 . The turbomachine according to  claim 11 , further comprising: a seal positioned in the seal slot, the seal extending circumferentially outwardly from the first side edge. 
     
     
         13 . The turbomachine according to  claim 8 , wherein the at least one turbine shroud includes a first turbine shroud and a second turbine shroud, the second turbine shroud being arranged directly adjacent to the first turbine shroud. 
     
     
         14 . The turbomachine according to  claim 13 , wherein the first turbine shroud includes the first interface member and the second interface member, and the second turbine shroud includes another second interface member. 
     
     
         15 . The turbomachine according to  claim 13 , wherein the first interface member of the first turbine shroud is configured and disposed to receive the another second interface member from the second turbine shroud to form an angled slashface interface between the first and second turbine shrouds. 
     
     
         16 . The turbomachine according to  claim 8 , wherein the first non-perpendicular angle is complementary to the second non-perpendicular angle.