Modal Tuning for Vanes

• US 20130195652A1
• Filed: 01/27/2012
• Published: 08/01/2013
• Est. Priority Date: 01/27/2012
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: Pratt & Whitney (Rtx Corporation)
• Inventors: Pope, Andrew
• Granted Patent: US 9,121,284 B2
• Time in Patent Office: Days
• US Class Current: 416/1
• CPC Class Codes: F01D 25/162 Bearing supports
• CPC Class Codes: F01D 5/141 Shape, i.e. outer, aerodynamic form F01D5/148 - F01D5/20 take precedence; blade construction F01D5/147
• CPC Class Codes: F01D 5/147 Construction, i.e. structural features, e.g. of weight-saving hollow blades F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18
• CPC Class Codes: F01D 5/16 for counteracting blade vibration
• CPC Class Codes: F04D 29/542 Bladed diffusers fixing blades to stators F01D9/042
• CPC Class Codes: F04D 29/544 Blade shapes
• CPC Class Codes: F04D 29/663 Sound attenuation
• CPC Class Codes: F05D 2260/961 by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape

Abstract

A vane having a cambered airfoil body is frequency-tuned via a number of cavities formed in a surface of the vane. At least some of the cavities are filled with a nonmetallic filler material, and the remainder of the cavities are left unfilled. A cover is affixed to the vane so as to cover at least the unfilled cavities. In an embodiment, the filling and covering of cavities is performed in a manner that excludes the frequency modes of the guide vane from a precluded band, e.g., an engine excitation band.

Claims

1. A set of vanes for use in a gas turbine, the set comprising:

at least a first vane having a first camber, the first vane having an airfoil-shaped body portion having a plurality of cavities on at least one surface thereof, the first vane having a first degree of coverage by a first cover portion, wherein a degree of coverage represents an extent to which cavities of a surface are covered, the first vane having a first frequency response with at least a first mode; and

at least a second vane having a second camber different from the first camber, the second vane having an airfoil-shaped body portion having a plurality of cavities on at least one surface thereof, the second vane having a second degree of coverage by a second cover portion, the second vane having a second frequency response with at least a second mode;

wherein the first camber differs from the second camber and the second degree of coverage differs from the first degree of coverage.

2. The set of vanes for use in a gas turbine in accordance with claim 1, wherein neither of the first and second modes falls within a predetermined frequency band.

3. The set of vanes for use in a gas turbine in accordance with claim 1, wherein the plurality of cavities are located at least on respective suction surfaces of the first and second vanes.

4. The set of vanes for use in a gas turbine in accordance with claim 1, wherein the plurality of cavities are located at least on respective pressure surfaces of the first and second vanes.

5. The set of vanes in accordance with claim 1, wherein each of the first and second degrees of coverage fall within a range from zero coverage to full coverage.

6. The set of vanes in accordance with claim 1, wherein at least one of the first and second cover portions comprises a plurality of covering members.

7. The set of vanes in accordance with claim 1, wherein a subset of the cavities of at least one of the first vane and the second vane is filled with a nonmetallic filler material.

8. The set of vanes in accordance with claim 7, wherein the nonmetallic filler material is a structural foam material.

9. The set of vanes in accordance with claim 7, wherein the nonmetallic filler material comprises an added constituent including at least one of a fiber material and a microsphere material.

10. The set of vanes in accordance with claim 7, wherein at least one of the subset of the cavities is both filled and covered.

11. A method for tuning modes of a set of differently cambered vanes for use in a gas turbine, the method comprising:

providing a first plurality of vanes having a first camber and having a plurality of cavities on at least one surface thereof;

providing a second plurality of vanes having a second camber and having a plurality of cavities on at least one surface thereof, wherein the second camber differs from the first camber;

tuning a frequency response of the first plurality of vanes by at least one of covering and filling of each cavity in each vane of the first plurality of vanes with a filler material such that the first plurality of vanes have a first set of frequency modes, and none of the first set of frequency modes falls within a predetermined band; and

tuning a frequency response of the second plurality of vanes by identifying a front portion of the second airfoil that is substantially the same as a front portion of the first airfoil, covering or filling each cavity in the front portion of each vane of the second plurality of vanes in the same manner as each cavity in the front portion of each vane of the first plurality of vanes, and independently tuning a remaining portion of each vane of the second plurality of vanes by at least one of covering and filling of each cavity in the remaining portion.

12. The method for tuning modes of a set of differently cambered vanes in accordance with claim 11, wherein the plurality of cavities are located on at least respective suction surfaces of the first and second pluralities of vanes.

13. The method for tuning modes of a set of differently cambered vanes in accordance with claim 11, wherein the plurality of cavities are located on at least respective pressure surfaces of the first and second pluralities of vanes.

14. The method for tuning modes of a set of differently cambered vanes in accordance with claim 11, further comprising tuning the frequency response of at least one of the first and second plurality of vanes by adjusting one or more of a depth of the cavities, a ratio of cavitated surface area to non-cavitated surface area, addition of ribs, removal of ribs, and a change in a density, strength, or resilience of the filler material.

15. The method for tuning modes of a set of differently cambered vanes in accordance with claim 11, wherein the filler material comprises a nonmetallic filler material.

16. The method for tuning modes of a set of differently cambered vanes in accordance with claim 15, wherein the nonmetallic filler material is a structural foam material.

17. The method for tuning modes of a set of differently cambered vanes in accordance with claim 15, wherein the nonmetallic filler material comprises an added constituent including at least one of a fiber material and a microsphere material.

18. The method for tuning modes of a set of differently cambered vanes in accordance with claim 11, wherein a cavity of at least one of the first plurality of vanes and the second plurality of vanes is both filled and covered.

19. A gas turbine engine comprising:

an annular passage configured to direct a flow of gaseous material; and

a vane disposed at least partially within the annular passage, the vane comprising;

a cambered airfoil body having a leading edge, trailing edge, pressure surface, and suction surface;

a plurality of cavities formed in at least one of the pressure surface and the suction surface, with at least a subset of the plurality of cavities being filled with a nonmetallic filler material and a remainder of the plurality of cavities being unfilled with the nonmetallic filler material; and

a cover affixed to the cambered airfoil body so as to cover the remainder of the plurality of cavities.

20. The gas turbine engine in accordance with claim 19, wherein the nonmetallic filler material is a structural foam material.

21. The gas turbine engine in accordance with claim 19, wherein the cover comprises a plurality of separate covering parts.

22. The gas turbine engine in accordance with claim 19, wherein the cover also covers a portion of the subset of the plurality of cavities filled with the nonmetallic filler material.

23. The gas turbine engine in accordance with claim 19, wherein the plurality of cavities are formed in one but not both of the pressure surface and the suction surface.