Feather Seals and Gas Turbine Engine Systems Involving Such Seals

Abstract

Feather seals and gas turbine engine systems involving such seals are provided. In this regard, a representative feather seal for a gas turbine engine includes: an elongate body portion; and a locating tab extending longitudinally along the body portion and extending outwardly therefrom.

1 . An outer air seal assembly for a gas turbine engine comprising:
 a first outer air seal segment having a first sealing surface and a first end;   a second outer air seal segment having a second sealing surface and a second end;   the first outer air seal segment and the second outer air seal segment being oriented in an end-to-end annular arrangement such that the first end and the second end define a gap therebetween; and   a feather seal having an elongate body portion and a locating tab extending outwardly from the body portion, the body portion having a first sealing surface and a second sealing surface, the locating tab being positioned between the first sealing surface and the second sealing surface such that, in an operative position in which the first sealing surface of the feather seal contacts the first sealing surface of the outer air seal and the second sealing surface of the feather seal contacts the second sealing surface of the outer air seal, the locating tab extends into the gap and between the first outer air seal segment and the second outer air seal segment.   
   
   
       2 . The assembly of  claim 1 , further comprising a mounting ring operative to mount the first outer air seal segment and the second outer air seal segment in an annular arrangement. 
   
   
       3 . The assembly of  claim 1 , wherein the locating tab extends outwardly from a longitudinal centerline of the body portion. 
   
   
       4 . The assembly of  claim 1 , wherein the first sealing surface of the first outer air seal segment is an outer diameter surface. 
   
   
       5 . The assembly of  claim 1 , further comprising a retention component located radially outboard of the feather seal, the retention component being operative to restrict radial movement of the feather seal. 
   
   
       6 . The assembly of  claim 5 , wherein:
 the assembly further comprises a mounting ring operative to mount the first outer air seal segment and the second outer air seal segment in an annular arrangement; and   the retention component is associated with the mounting ring.   
   
   
       7 . The assembly of  claim 5 , wherein the retention component is not attached to either the first outer air seal segment or the second outer air seal segment. 
   
   
       8 . The assembly of  claim 1 , wherein the locating tab is operative to maintain at least a minimum spacing between the first outer air seal segment and the second outer air seal segment. 
   
   
       9 . The assembly of  claim 1 , wherein the locating tab extends the length of the body portion. 
   
   
       10 . A feather seal for a gas turbine engine comprising:
 an elongate body portion; and   a locating tab extending longitudinally along the body portion and extending outwardly therefrom.   
   
   
       11 . The feather seal of  claim 10 , wherein, as viewed in end view, the feather seal is T-shaped. 
   
   
       12 . The feather seal of  claim 10 , wherein the locating tab extends the length of the body portion. 
   
   
       13 . The feather seal of  claim 10 , wherein the body portion has a first sealing surface and a second sealing surface, the locating tab being positioned between the first sealing surface and the second sealing surface. 
   
   
       14 . The feather seal of  claim 10 , wherein the locating tab extends outwardly from a longitudinal centerline of the body portion. 
   
   
       15 . A gas turbine engine comprising:
 a compressor;   a combustion section;   a turbine operative to drive the compressor responsive to energy imparted thereto by the combustion section, the turbine having a rotatable blade; and   an outer air seal assembly annularly arranged about the turbine, at least a portion of the outer air seal being located radially outboard of the blade, the outer air seal assembly comprising:
 a first outer air seal segment; 
 a second outer air seal segment; and 
 a feather seal having an elongate body portion and a locating tab extending longitudinally along the body portion and extending outwardly therefrom; 
 the first outer air seal segment and the second outer air seal segment being oriented in an end-to-end annular arrangement such that the first end and the second end define a gap therebetween, the locating tab extending into the gap. 
   
   
   
       16 . The engine of  claim 15 , further comprising a retention component located radially outboard of the feather seal, the retention component being operative to restrict radial movement of the feather seal. 
   
   
       17 . The engine of  claim 15 , wherein, as viewed in end view, the feather seal is T-shaped. 
   
   
       18 . The engine of  claim 15 , wherein the locating tab extends the length of the body portion. 
   
   
       19 . The engine of  claim 15 , wherein the body portion has a first sealing surface operative to contact the first outer air seal segment and a second sealing surface operative to contact the second outer air seal segment, the locating tab being positioned between the first sealing surface and the second sealing surface. 
   
   
       20 . The engine of  claim 15 , wherein the locating tab is operative to maintain at least a minimum spacing between the first outer air seal segment and the second outer air seal segment.