Patent ID: 11927111
Assignee: GENERAL ELECTRIC COMPANY
Field: Engines, pumps, turbines (Mechanical engineering)
Classification: CPC F | IPC F

Claim 9:
10. The component of claim 1 located within a turbine engine, comprising:
an engine core extending along an engine centerline and including a compressor section, a combustor, and a turbine section in axial flow arrangement and defining a flow path;
a temperature sensor within the engine and configured to detect an exhaust gas temperature (EGT) within the engine core;
a set of nozzles circumferentially arranged in the turbine section and defining a number of nozzles (NN); and
a set of blades circumferentially arranged in the turbine section adjacent to, and downstream of, the set of nozzles, the set of blades defining a number of blades (NB);
wherein a blade in the set of blades comprises:
an outer wall bounding an interior and having an exterior surface, with the outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a chord-wise direction, and also extending between a tip and a root to define a span-wise direction;
a cooling conduit within the interior;
a tip radius (TR) defined between the engine centerline and the tip under standard day conditions of 15° C. at mean sea level altitude and 101.3 kPa atmospheric pressure;
a radial length (R) defined by a span-wise line extending between a first location on the outer wall and a second location on the outer wall, with the first location and the second location having a common chord-wise position;
a surface length (Lmax) defined by a contour line along the outer wall between the first location and the second location at the common chord-wise position; and
a blade parameter (BP) defined as a ratio of the surface length to the radial length (BP=Lmax/R);
wherein the exhaust gas temperature EGT, the number of blades NB, the number of nozzles NN, the tip radius TR, and the blade parameter BP define a blade tip durability factor (BTDF) by the following expression:, BTDF
   =
   
    
     (
     
      TR
      EGT
     
     )
    
    ×
    
     (
     
      NB
      NN
     
     )
    
    ×
    BP
   
  
  ;
 

wherein the blade tip durability factor BTDF is between 0.020 and 0.033 in/° C., and the blade parameter BP is between 1-1.234.