Granted Patent B2

US 12,215,599 · App. 18/675,388 · Granted Feb 4, 2025

Inventors: Marc Edward Blohm (Greenville, SC); Vasantharuban S (Bangalore, IN); Sharan Shanti (Bangalore, IN); Prakash Dalsania (Bangalore, IN); Corey Lynn Hubbert (Greenville, SC); Siddaraja Mallikarjuna Devangada (Bangalore, IN)

Assignee: GE Infrastructure Technology LLC

F01D5/141F05D2220/3217F05D2220/3219F05D2240/301F05D2240/306F05D2250/74

Abstract

Claims (24)

1. A rotor blade comprising:

an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table III, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.

2. The rotor blade of claim 1 , wherein the airfoil includes a stagger angle distribution in accordance with Table XII, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.

3. The rotor blade of claim 1 , wherein the rotor blade forms part of a stage of a compressor section.

4. The rotor blade of claim 3 , wherein the stage of the compressor section is a mid stage of the compressor section.

5. The rotor blade of claim 1 , wherein the rotor blade is a sixth stage compressor rotor blade.

6. The rotor blade of claim 1 , wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

7. The rotor blade of claim 1 , wherein the scaling factor is between about 0.01 inches and about 10 inches.

8. The rotor blade of claim 1 , wherein the X, Y and Z values are scalable as a function of the scaling factor to provide a scaled-up or scaled-down airfoil.

9. A rotor blade comprising:

an airfoil having a nominal suction-side profile substantially in accordance with suction-side Cartesian coordinate values of X, Y and Z set forth in Table III, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define suction-side profile sections at each Z value, the suction-side profile sections at the Z values being joined smoothly with one another to form a complete airfoil suction-side shape.

10. The rotor blade of claim 9 , wherein the airfoil includes a stagger angle distribution in accordance with Table XII, each stagger angle in the stagger angle distribution being measured between a chord line of the airfoil and a rotary axis of the airfoil.

11. The rotor blade of claim 9 , wherein the rotor blade forms part of a stage of a compressor section.

12. The rotor blade of claim 11 , wherein the stage of the compressor section is a mid stage of the compressor section.

13. The rotor blade of claim 9 , wherein the rotor blade is a sixth stage compressor rotor blade.

14. The rotor blade of claim 9 , wherein the nominal suction-side profile lies in an envelope within +/−5% of a chord length in a direction normal to any airfoil surface location.

15. The rotor blade of claim 9 , wherein the scaling factor is between about 0.01 inches and about 10 inches.

16. The rotor blade of claim 9 , wherein the X, Y and Z values are scalable as a function of the scaling factor to provide a scaled-up or scaled-down airfoil.

17. A compressor section comprising:

a plurality of rotor blades arranged in a plurality of stages, each rotor blade of the plurality of rotor blades comprising an airfoil having an airfoil shape, the airfoil shapes of the plurality of rotor blades each having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in one of Table III, Table IV, or Table V, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a scaling factor of the airfoil in the unit of distance; and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape;

wherein the plurality of stages comprises:

a sixth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table III;

a seventh stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table IV; and

an eighth stage comprising the airfoil having the airfoil shape with the nominal profile substantially in accordance with the Cartesian coordinate values of X, Y and Z set forth in Table V.

Assignments (2)

Priority Claims (1)

Continuity (3)

References Cited (21)