Method for modifying gas turbine performance

Patent metadata

Field	Value
Publication number	US-9500085-B2
Application number	US-201213555434-A
Country	US
Kind code	B2
Filing date	Jul 23, 2012
Priority date	Jul 23, 2012
Publication date	Nov 22, 2016
Grant date	Nov 22, 2016

Abstract

A method for enhancing one or more performance parameters of a gas turbine having at least one row of clocked airfoils may generally include choosing a first, a second and a third row of airfoils where the third row is clocked relative to the first row. An unsteady computational fluid dynamics model may be used to determine at least one wake parameter of a working fluid flowing from the second row of the airfoils to the third row of the airfoils. At least one design parameter of the airfoils of the second row may be modified, and the unsteady computational fluid dynamics model may then be used to determine the effect of the airfoil design parameter modification on the at least one wake parameter. The effect on the wake parameter may be compared to a predetermined target range.

First claim

What is claimed is:

1. A method for modifying gas flow within a gas turbine where the gas flow originates from a row of rotor blades disposed axially between a first row of stator blades and a second row of stator blades where the second row of stator blades is clocked with respect to the first row of stator blades, wherein the method comprises:
a, determining a wake parameter of a gas flow wake at one or more radial positions within a gas flow volume defined between trialing edges of the rotor blades and upstream from trailing edges of the stator blades of the second row of stator blades via an unsteady computational fluid dynamics model;
b. modifying at least one rotor blade design parameter for the rotor blades in the unsteady computational fluid dynamics model in such a manner so as to increase or decrease the wake parameter to a predefined target range, wherein modifying at least one rotor blade design parameter in the unsteady computational fluid dynamics model includes modifying at least one rotor blade design parameter such that the wake width is narrower at a first radial location along the radial span of the stator blades of the second row and wider at a second radial location along the radial span of the stator blades of the second row;
c, verifying that the increase or the decrease in the wake parameter falls within the predefined target range via the unsteady computational fluid dynamics model; and
d. wherein if the wake parameter falls within the predefined target range, the method further includes retrofitting the gas turbine with replacement rotor blades which conform to the modified rotor blade design parameter and if the wake parameter falls outside of the predefined target range, the method includes repeating steps a, b and c.

2. The method as in claim 1 , wherein the wake parameter comprises a circumferential wake width of the gas flow.

3. The method as in claim 2 , wherein the wake width is determined by analyzing circumferential entropy distribution.

4. The method as in claim 1 , wherein the wake parameter comprises a radial height of the gas flow wake as measured between a root portion and a radial tip portion of the stator blades of the second row of stator blades.

5. The method as in claim 1 , wherein the wake parameter of the gas flow wake is determined at multiple radial positions within the gas flow volume so as to identify a radial and circumferential shape of the wake.

6. The method as in claim 1 , wherein determining the wake parameter of the as flow wake at one or more radial positions within the gas flow volume comprises defining the wake parameter at an axial position which is proximate to leading edges of the stator blades of the second row of stator blades.

7. The method as in claim 1 , further comprising utilizing an unsteady Navier-Stokes computational fluid dynamics computer model to determine the wake parameter.

8. The method as in claim 1 , wherein the first row of stator blades, the row of rotor blades and the second row of stator blades are modeled from a compressor of the gas turbine or a turbine of the gas turbine.

9. The method as in claim 1 , wherein modifying at least one rotor blade design parameter for the rotor blades in the unsteady computational fluid dynamics model comprises modifying at least one of stagger angle, curvature, lean, tilt, number of rotor blades, rotor blade platform shape and span height of the rotor blades.

10. A method for modifying gas flow within a gas turbine where the gas flow originates from a row of stator blades disposed axially between a first row of rotor blades and a second row of rotor blades where the second row of rotor blades is clocked with respect to the first row of rotor blades, wherein the method comprises:
a. determining a wake parameter of a gas flow wake at one or more radial positions within a gas flow volume defined between trialing edges of the stator blades and upstream from trailing edges of the rotor blades of the second row of rotor blades via an unsteady computational fluid dynamics model;
b. modifying at least one stator blade design parameter for the stator blades in the unsteady computational fluid dynamics model in such a manner so as to increase or decrease the wake parameter at one or more radial positions within the gas flow volume to a predefined target range, wherein modifying at least one stator blade design parameter for the stator blades in the unsteady computational fluid dynamics model includes modifying at least one stator blade design parameter such that the wake width is narrower at a first radial location along the radial span of the rotor blades of the second row and wider at a second radial location along the radial span of the rotor blades of the second row;
c. verifying that the increase or the decrease in the wake parameter falls within the predefined target range via the unsteady computational fluid dynamics model; and
d. wherein if the wake parameter falls within the predefined target range, the method further includes retrofitting the gas turbine with replacement stator blades which conform to the modified stator blade design parameter and if the wake parameter falls outside of the predefined target range, the method includes repeating steps a, b and c.

11. The method as in claim 10 , wherein the wake parameter comprises a circumferential wake width of the gas flow.

12. The method as in claim 11 , wherein the wake width is determined by analyzing circumferential entropy distribution.

13. The method as in claim 10 , wherein the wake parameter comprises a radial height of the gas flow wake as measured between a root portion and a radial tip portion of the rotor blades of the second row of rotor blades.

14. The method as in claim 10 , wherein the wake parameter of the gas flow wake is determined at multiple radial positions within the gas flow volume so as to identify a radial and circumferential shape of the wake.

15. The method as in claim 10 , wherein determining the wake parameter of the gas flow wake at one or more radial positions within the gas flow volume comprises defining the wake parameter at an axial position which is proximate to leading edges of the rotor blades of the second row of rotor blades.

16. The method as in claim 10 , further comprising utilizing an unsteady Navier-Stokes computational fluid dynamics computer model to determine the wake parameter.

17. The method as in claim 10 , wherein the first row of rotor blades, the row of stator blades and the second row of rotor blades are modeled from a compressor of the gas turbine or a turbine of the gas turbine.

18. The method as in claims 10 , wherein modifying at least one stator blade design parameter for the stator blades in the unsteady computational fluid dynamics model comprises modifying at least one of stagger angle, curvature, lean, tilt, number of stator blades, stator blade platform shape and span height of the stator blades.

Assignees

• Smith Paul Kendall
• Pierre Sylvain
• Holloway Dennis Scott
• Gen Electric

Inventors

• Smith Paul Kendall
• Pierre Sylvain
• Holloway Dennis Scott

Classifications

• F05D2220/321

  for a special turbine stage · CPC title

• F01D5/142 Primary

  of the blades of successive rotor or stator blade-rows · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2220/3216

  for a special compressor stage · CPC title

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title