System and method for controlling flow in turbomachinery

Abstract

A system includes a turbine. The turbine includes a first turbine blade comprising a leading edge, a blade platform coupled to the first turbine blade, and a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade. The protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge.

1 . A system, comprising:
 a turbine, comprising:
 a first turbine blade comprising a leading edge; 
 a blade platform coupled to the first turbine blade; and 
 a protrusion disposed on the blade platform adjacent the leading edge of the first turbine blade, wherein the protrusion is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of a hot gas flow near the leading edge. 
   
     
     
         2 . The system of  claim 1 , wherein the protrusion is configured to block entry of the hot gas flow into a wheel space cavity near the leading edge of the first turbine blade. 
     
     
         3 . The system of  claim 1 , comprising a second turbine blade, wherein the protrusion does not extend across a space between the first turbine blade and the second turbine blade. 
     
     
         4 . The system of  claim 1 , wherein the protrusion is configured to increase the first static pressure of the cooling flow only near the leading edge of the first turbine blade. 
     
     
         5 . The system of  claim 1 , wherein the protrusion comprises at least one of a circular cross-sectional shape, an oval cross-sectional shape, a triangular cross-sectional shape, a square cross-sectional shape, a rectangular cross-sectional shape, a polygonal cross-sectional shape, an aerodynamic cross-sectional shape, an arcuate cross-sectional shape, or a combination thereof. 
     
     
         6 . The system of  claim 1 , wherein an aspect ratio of the protrusion is less than approximately 2:1, the aspect ratio comprises a ratio of a first dimension of the protrusion to a second dimension of the protrusion. 
     
     
         7 . The system of  claim 1 , wherein the protrusion is disposed between a front edge of the blade platform and the leading edge of the first turbine blade. 
     
     
         8 . The system of  claim 1 , comprising a one-piece structure having the protrusion integrally formed on the blade platform, or a multi-piece structure having the protrusion coupled to the blade platform. 
     
     
         9 . A system, comprising:
 an ingestion restrictor configured to mount on a blade platform adjacent a leading edge of a turbine blade of a turbine, wherein the ingestion restrictor is configured to block entry of a hot gas flow into a wheel space cavity near the leading edge of the turbine blade.   
     
     
         10 . The system of  claim 9 , wherein the ingestion restrictor is configured to increase a first static pressure of a cooling flow near the leading edge above a second static pressure of the hot gas flow near the leading edge. 
     
     
         11 . The system of  claim 9 , wherein a width of the ingestion restrictor is less than a radial height of the blade platform. 
     
     
         12 . The system of  claim 11 , wherein a ratio of the radial height of the blade platform to the width of the ingestion restrictor is less than approximately 2:1. 
     
     
         13 . The system of  claim 9 , wherein the ingestion restrictor is disposed between a front edge of the blade platform and the leading edge of the turbine blade. 
     
     
         14 . The system of  claim 9 , wherein the ingestion restrictor comprises at least one of a circular cross-sectional shape, an oval cross-sectional shape, a triangular cross-sectional shape, a square cross-sectional shape, a rectangular cross-sectional shape, a polygonal cross-sectional shape, an aerodynamic cross-sectional shape, an arcuate cross-sectional shape, or a combination thereof. 
     
     
         15 . The system of  claim 9 , wherein the ingestion restrictor is oriented at an angle from an axial axis of the turbine. 
     
     
         16 . The system of  claim 9 , comprising the turbine having the ingestion restrictor. 
     
     
         17 . A method, comprising:
 mounting an ingestion restrictor on a blade platform upstream of a leading edge of a first turbine blade of a turbine, and   increasing a first static pressure of a cooling flow near the leading edge of the first turbine blade above a second static pressure of a hot gas flow using the ingestion restrictor.   
     
     
         18 . The method of  claim 17 , comprising blocking entry of the hot gas flow into a wheel space cavity near the leading edge of the first turbine blade using the ingestion restrictor. 
     
     
         19 . The method of  claim 17 , comprising disposing the ingestion restrictor between a front edge of the blade platform and the leading edge of the first turbine blade. 
     
     
         20 . The method of  claim 17 , comprising locating the ingestion restrictor to not extend across a space between the first turbine blade and a second turbine blade.