Mistuned concentric airfoil assembly and method of mistuning same

Patent metadata

Field	Value
Publication number	US-10767486-B2
Application number	US-201816106221-A
Country	US
Kind code	B2
Filing date	Aug 21, 2018
Priority date	Feb 13, 2014
Publication date	Sep 8, 2020
Grant date	Sep 8, 2020

Abstract

An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an annular shroud having a radially inner face and a radially outer face opposing the radially inner face, a radially inner array of airfoils extending from the radially inner face, and a radially outer array of airfoils extending from the radially outer face. The radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section. At least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils. A method of reducing a vibratory response of airfoils is also disclosed.

First claim

We claim:

1. An airfoil assembly for a gas turbine engine, comprising:
an annular shroud having a radially inner face and a radially outer face opposing the radially inner face;
a radially inner array of airfoils extending from the radially inner face;
a radially outer array of airfoils extending from the radially outer face;
wherein the radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section; and
wherein at least one, but fewer than each, airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil of the radially outer array of airfoils, the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils, and fewer than each airfoil of the radially outer array of airfoils is circumferentially aligned with a corresponding airfoil of the radially inner array of airfoils.

2. The assembly of claim 1 , wherein one airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, the remaining airfoils in the radially inner array of airfoils are misaligned with the airfoils of the radially outer array of airfoils, the radially outer array of airfoils are configured to guide flow within a radially outer bypass flow passage, and the radially inner bypass flow passage and the radially outer bypass flow passage are both radially outside a core flow passage.

3. The assembly of claim 2 , wherein:
a distance varies between circumferentially adjacent airfoils in the radially outer array of airfoils.

4. The assembly of claim 2 , wherein:
a distance varies between circumferentially adjacent airfoils of the radially inner array of airfoils or between circumferentially adjacent airfoils in the radially outer array of airfoils; and
the core flow passage extends through the compressor section, a combustor section and a turbine section.

5. The assembly of claim 4 , wherein each of the radially inner and radially outer bypass flow passages is free of any rotatable airfoils downstream of the radially inner array of airfoils and downstream of the radially outer array of airfoils.

6. The assembly of claim 2 , wherein the shroud, the radially inner array of airfoils and the radially outer array of airfoils are cast together as a single unitary structure.

7. An airfoil assembly for a gas turbine engine, comprising:
an annular shroud having a radially inner face and a radially outer face opposing the radially inner face;
a radially inner array of airfoils extending from the radially inner face;
a radially outer array of airfoils extending from the radially outer face;
wherein the radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, the radially inner bypass flow passage bypassing and being radially outward of a compressor section;
wherein a plurality of airfoils of the radially inner array of airfoils on a first side of a horizontal midline of the assembly are circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils; and
wherein at least one airfoil of the radially inner array is circumferentially misaligned with the airfoils of the radially outer array.

8. The assembly of claim 7 , wherein each airfoil of the radially inner array of airfoils on the first side of the horizontal midline of the assembly is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils.

9. The assembly of claim 8 , wherein the radially inner bypass flow passage and the radially outer bypass flow passage are both radially outside a core flow passage extending through the compressor section.

10. An airfoil assembly for a gas turbine engine, comprising:
a shroud having a radially inner face and a radially outer face opposing the inner face;
a radially inner array of airfoils extending from the radially inner face; and
a radially outer array of airfoils extending from the radially outer face, wherein a distance varies between circumferentially adjacent airfoils of the radially inner array of airfoils or between circumferentially adjacent airfoils in the radially outer array of airfoils;
wherein a total number of airfoils in the radially inner array of airfoils is greater than a total number of airfoils in the radially outer array of airfoils; and
wherein one airfoil of the radially inner array of airfoils is circumferentially aligned with a corresponding airfoil in the radially outer array of airfoils, and the remaining airfoils of the radially inner array of airfoils are circumferentially misaligned with all airfoils in the radially outer array of airfoils.

11. The assembly of claim 10 , wherein the shroud is an annular shroud, and wherein the shroud, the radially inner array of airfoils and the radially outer array of airfoils are cast together as a single unitary structure.

12. The assembly of claim 10 , wherein the shroud is a middle shroud and further comprising a radially inner shroud and a radially outer shroud, the radially inner array of airfoils extending from the middle shroud to the radially inner shroud, the radially outer array of airfoils extending from the middle shroud to the radially outer shroud.

13. The assembly of claim 10 , wherein the radially inner array of airfoils are configured to guide flow within a radially inner bypass flow passage, and wherein the radially outer array of airfoils are configured to guide flow within a radially outer bypass flow passage.

14. The assembly of claim 13 , wherein the radially inner bypass flow passage and the radially outer bypass flow passage both bypass and are radially outward of a core flow passage, and wherein the core flow passage extends through a compressor section, a combustor section and a turbine section.

15. The assembly of claim 14 , wherein the shroud, the radially inner array of airfoils, and the radially outer array of airfoils are cast together as a single unitary structure.

16. The assembly of claim 15 , wherein each of the radially inner and radially outer bypass flow passages is free of any rotatable airfoils downstream of the radially inner array of airfoils and downstream of the radially outer array of airfoils.

17. A method of reducing a vibratory response of airfoils that support a shroud for a gas turbine engine, comprising:
circumferentially aligning at least one airfoil in a radially inner array of airfoils with a corresponding airfoil of a radially outer array of airfoils;
circumferentially misaligning the remaining airfoils in the radially inner array of airfoils with all airfoils of the radially outer array of airfoils; and
guiding flow through a radially inner bypass flow passage using the radially inner array of airfoils, the radially inner bypass flow passage bypassing and being radially outward of a core flow passage; and
wherein a distance varies between circumferentially adjacent airfoils of the radially inner array of airfoils or between circumferentially adjacent airfoils in the radially outer array of airfoils.

18. The method of claim 17 , further comprising guiding flow through a radially outer bypass flow passage using the radially outer array of airfoils.

19. The method of claim 17 , further comprising moving core flow through the core flow passage that is radially inside the radially inner bypass flow pas

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Hayford Richard K
• Ford Steven J

Classifications

• F01D5/146 Primary

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F01D5/022

  with concentric rows of axial blades · CPC title

• F01D25/06

  for preventing blade vibration (means on blade-carrying members or blades F01D5/00) · CPC title

• F01D5/225

  by shrouding · CPC title

• Y02T50/60

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