System and method for reduction of unsteady pressures in turbomachinery

Abstract

A turbomachinery system is provided. The system includes a first set of blades and a second set of blades moving relative to the first set of blades, wherein the second set of blades includes a first subset of blades having multiple first geometric parameters. The second set of blades also includes at least a second subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades such that unsteady pressures generated from the wakes of the first set of blades interacting with the second set of blades is below an acceptable level. Further, the at least second subset of blades include multiple second geometric parameters that are different or identical to the multiple first geometric parameters.

1 . A turbomachinery system, comprising:
 a first set of blades; and   a second set of blades moving relative to the first set of blades, the second set of blades comprising:
 a first subset of blades comprising a plurality of first geometric parameters; and 
 at least a second subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades such that unsteady pressures generated from the wakes of the first set of blades interacting with the second set of blades is below an acceptable level, the at least second subset of blades comprising a plurality of second geometric parameters that are different or identical to the plurality of first geometric parameters. 
   
   
   
       2 . The system of  claim 1 , wherein the first subset of blades is stationary and the second set of blades is rotating. 
   
   
       3 . The system of  claim 1 , wherein the first set of blades is rotating and the second set of blades is stationary. 
   
   
       4 . The system of  claim 1 , wherein the first set of blades and the second set of blades are counter-rotating. 
   
   
       5 . The system of  claim 1 , wherein the second set of blades further comprises a third subset of blades spaced circumferentially and axially relative to the first subset of blades and the second subset of blades. 
   
   
       6 . The system of  claim 1 , wherein the plurality of first geometric parameters and the plurality of second geometric parameters comprises a camber, a stagger, a chord, a thickness, a chordwise distribution and a spanwise distribution of the camber, the thickness and the stagger respectively. 
   
   
       7 . The system of  claim 1 , wherein the turbomachinery system comprises an aircraft engine, gas turbine, steam turbine, a wind turbine, a hydro turbine, or a heating-ventillating-airconditioning system. 
   
   
       8 . A method for manufacturing a turbomachine comprising:
 providing a first set of blades; and   providing a second set of blades moving relative to the first set of blades, the second set of blades comprising:
 a first subset of blades comprising a plurality of first geometric parameters; and 
 at least a second subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades such that unsteady pressures generated from the wakes of the first set of blades interacting with the second set of blades is below an acceptable level, the at least second subset of blades comprising a plurality of second geometric parameters that are different or identical to the plurality of first geometric parameters. 
   
   
   
       9 . The method of  claim 8 , wherein said providing a first set of blades comprises rotating a first set of blades. 
   
   
       10 . The method of  claim 8 , wherein said providing a second set of blades comprises rotating the second set of blades. 
   
   
       11 . The method of  claim 8 , wherein providing a second set of blades further comprises providing a third subset of blades non-uniformly spaced circumferentially and axially relative to the first subset of blades and the second subset of blades. 
   
   
       12 . The method of  claim 8 , wherein providing a second set of blades further comprises providing a unique spacing circumferentially and axially and unique geometric definition for each blade in the second set.