Compressor

Abstract

A compressor 13, for example for a gas turbine engine ( 10, FIG. 1 ), comprises a circumferentially extending static casing component 20 defining a generally axially extending main gas flow path 24. The compressor also includes a rotating aerofoil arrangement 26 comprising an aerofoil support 30 and a plurality of aerofoils 28 extending radially from the aerofoil support 30 into the main gas flow path 24. The aerofoil support 30 and the circumferentially extending static casing component 20 define a circumferentially extending generally radial passage 40 having an outlet 42 in communication with the main gas flow path 24 through which leakage air may flow into the main gas flow path 24, and the static casing component 20 includes a continuous circumferentially extending projection formation 44 projecting into the radial passage 40 to control the flow of leakage air into the main gas flow path 24.

1 . A compressor comprising:
 a circumferentially extending static casing component defining a generally axially extending main gas flow path;   a rotating aerofoil arrangement comprising an aerofoil support and a plurality of aerofoils extending radially from the aerofoil support into the main gas flow path;   the aerofoil support and the circumferentially extending static casing component defining a circumferentially extending generally radial passage having an outlet in communication with the main gas flow path through which leakage air may flow into the main gas flow path;   wherein the static casing component includes a continuous circumferentially extending projection formation projecting into the radial passage to control the flow of leakage air into the main gas flow path.   
   
   
       2 . A compressor according to  claim 1 , wherein the projection formation is located substantially at or substantially adjacent to the outlet of the circumferentially extending radial passage. 
   
   
       3 . A compressor according to  claim 1 , wherein the projection formation includes a first continuous circumferentially extending projection projecting into the circumferentially extending radial passage. 
   
   
       4 . A compressor according to  claim 3 , wherein the first continuous circumferentially extending projection includes a radially inner sloping side surface having a generally concave profile. 
   
   
       5 . A compressor according to  claim 3 , wherein the first continuous circumferentially extending projection includes a radially outer sloping side surface having a generally concave profile. 
   
   
       6 . A compressor according to  claim 4 , wherein either one or both of the radially inner and radially outer sloping side surfaces have a half angle of between 5° and 30°. 
   
   
       7 . A compressor according to  claim 3 , wherein the first continuous circumferentially extending projection projects across at least 10% of the width of the circumferentially extending radial passage. 
   
   
       8 . A compressor according to  claim 3 , wherein the first continuous circumferentially extending projection projects across between 10% and 20% of the width of the circumferentially extending radial passage. 
   
   
       9 . A compressor according to  claim 3 , wherein the distance between the centreline of the first continuous circumferentially extending projection and the outlet of the circumferentially extending radial passage is between 33% and 66% of the radial dimension of a securing member of one of the plurality of aerofoils. 
   
   
       10 . A compressor according to  claim 3 , wherein the projection formation includes a second continuous circumferentially extending projection projecting into the circumferentially extending radial passage. 
   
   
       11 . A compressor according to  claim 10 , wherein the first and second continuous circumferentially extending projections are located substantially adjacent to each other. 
   
   
       12 . A compressor according to  claim 10 , wherein the first continuous circumferentially extending projection is located radially inwardly of the second continuous circumferentially extending projection. 
   
   
       13 . A compressor according to  claim 10 , wherein the second continuous circumferentially extending projection has a radially inner sloping side surface having a generally concave profile. 
   
   
       14 . A compressor according to  claim 10 , wherein the second continuous circumferentially extending projection projects across between 10% and 20% of the width of the circumferentially extending radial passage. 
   
   
       15 . A compressor according to  claim 10 , wherein the radially inner sloping side surface of the second continuous circumferentially extending projection has a half angle of between 5° and 30°. 
   
   
       16 . A compressor according to  claim 1 , wherein aerofoil comprises a rotor blade. 
   
   
       17 . A compressor according to  claim 1 , wherein the aerofoil support comprises a rotor blade mounting disc. 
   
   
       18 . A compressor according to  claim 1 , wherein the compressor is a multi-stage axial compressor for a gas turbine engine. 
   
   
       19 . A gas turbine engine including a compressor according to  claim 1 .