Compressor for a gas turbine

Abstract

A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement ( 20 ) between the shroud ( 8 ) and rotor hub ( 3 ) is formed by a discharge arrangement ( 23 ) for leakage air.

1 . A compressor for a gas turbine, comprising:
 a rotor hub carrying rotor blades;   a stator having stator vanes;   a shroud associated with the stator vanes; and   an arrangement providing sealing between the shroud and rotor hub to prevent leakage, the sealing arrangement being formed by a discharge arrangement for leakage air.   
   
   
       2 . The compressor of  claim 1 , wherein the discharge arrangement is an exhaust cavity positioned within the shroud and the stator vanes, to discharge the leakage air to the outside. 
   
   
       3 . The compressor of  claim 2 , wherein a static pressure applied to the exhaust cavity is lower than a pressure prevailing within a shroud cavity. 
   
   
       4 . The compressor of  claim 3 , further comprising a return line connecting the exhaust cavity to an upstream compressor duct. 
   
   
       5 . The compressor of  claim 3 , wherein the exhaust cavity is connected to a secondary air system of the engine. 
   
   
       6 . The compressor of  claim 5 , and further comprising a defined throat positioned within at least one of the exhaust cavity and the air discharge duct of the discharge arrangement to regulate flow. 
   
   
       7 . The compressor of  claim 6 , wherein a flow-wetted area of an air discharge opening of the air discharge arrangement is determined by pressures of boundary layers ingested before and behind the shroud or in the shroud cavity, respectively. 
   
   
       8 . The compressor of  claim 7 , wherein at least one of the exhaust cavity and a cross-section of the air discharge opening in the shroud is provided as a discrete polygonal, round or elliptical opening. 
   
   
       9 . The compressor of  claim 7 , wherein the exhaust cavity in one of the stator vanes is provided as at least one of a round hole, an oblong hole, a slot and a hollow chamber. 
   
   
       10 . The compressor of  claim 1 , wherein a static pressure applied to the exhaust cavity is lower than a pressure prevailing within a shroud cavity. 
   
   
       11 . The compressor of  claim 1 , and further comprising a return line connecting the exhaust cavity to an upstream compressor duct. 
   
   
       12 . The compressor of  claim 1 , wherein the exhaust cavity is connected to a secondary air system of the engine. 
   
   
       13 . The compressor of  claim 1 , and further comprising a defined throat positioned within at least one of the exhaust cavity and the air discharge duct of the discharge arrangement to regulate flow.