Rotor system for a turbine engine

Patent metadata

Field	Value
Publication number	US-12366176-B2
Application number	US-202318456671-A
Country	US
Kind code	B2
Filing date	Aug 28, 2023
Priority date	Aug 28, 2023
Publication date	Jul 22, 2025
Grant date	Jul 22, 2025

Abstract

A rotor system for a turbine engine. The rotor system includes a rotor assembly and a stator assembly. The rotor assembly includes a plurality of rotor blades that rotate. The stator assembly includes a plurality of stator vanes arranged circumferentially about the stator assembly and includes at least one pair of non-uniform gaps between adjacent stator vanes. The plurality of stator vanes includes a first group of stator vanes having a first non-uniform gap between adjacent stator vanes, a second group of stator vanes having a second non-uniform gap between adjacent stator vanes, and a third group of stator vanes having a uniform spacing between adjacent stator vanes. The first non-uniform gap is positioned 180° from the second non-uniform gap. The plurality of rotor blades directs air through the plurality of stator vanes.

First claim

The invention claimed is:

1. A rotor system for a turbine engine, the rotor system having a longitudinal centerline axis and comprising:
a rotor assembly including a plurality of rotor blades, the plurality of rotor blades rotating about the longitudinal centerline axis; and
a stator assembly including a plurality of stator vanes arranged circumferentially about the stator assembly and including at least one pair of non-uniform gaps between adjacent stator vanes, the plurality of stator vanes comprising:
a first group of stator vanes having a first non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the first group of stator vanes;
a second group of stator vanes having a second non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the second group of stator vanes, the first non-uniform gap being equal to, and positioned 180° from, the second non-uniform gap;
a third group of stator vanes having a uniform spacing between adjacent stator vanes of the third group of stator vanes;
a fourth group of stator vanes having a third non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the fourth group of stator vanes; and
a fifth group of stator vanes having a fourth non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the fifth group of stator vanes, the third non-uniform gap being equal to, and positioned 180° from, the fourth non-uniform gap, and the third non-uniform gap and the fourth non-uniform gap being different than the first non-uniform gap and the second non-uniform gap, wherein the plurality of rotor blades direct air through the plurality of stator vanes.

2. The rotor system of claim 1 , wherein a number of stator vanes of the stator assembly is even.

3. The rotor system of claim 1 , wherein a number of rotor blades of the plurality of rotor blades is even.

4. The rotor system of claim 1 , wherein the plurality of rotor blades is uniformly spaced circumferentially about the rotor assembly.

5. The rotor system of claim 1 , wherein the stator assembly is positioned downstream of the rotor assembly.

6. The rotor system of claim 1 , wherein the at least one pair of non-uniform gaps is sized to prevent a zero nodal diameter system response and a one nodal diameter response.

7. The rotor system of claim 1 , wherein the air directed through the plurality of stator vanes causes a vibration response on the plurality of stator vanes, and the at least one pair of non-uniform gaps balances the vibration response on the plurality of stator vanes about the stator assembly.

8. The rotor system of claim 1 , wherein the first group of stator vanes includes two stator vanes of the plurality of stator vanes, and the second group of stator vanes includes two stator vanes of the plurality of stator vanes.

9. The rotor system of claim 1 , wherein the first non-uniform gap is a function of a number of rotor blades of the plurality of rotor blades, a number of stator vanes of the plurality of stator vanes, and the uniform spacing.

10. The rotor system of claim 9 , wherein the second non-uniform gap is a function of defined by the number of stator vanes of the plurality of stator vanes, the uniform spacing, and the first non-uniform gap.

11. A turbine engine having a longitudinal centerline axis and comprising:
a rotating shaft, the rotating shaft being at least one of a fan shaft, a high-pressure shaft, or a low-pressure shaft; and
a rotor system comprising:
a rotor assembly including a plurality of rotor blades, the rotor assembly coupled to the rotating shaft and the plurality of rotor blades rotating about the longitudinal centerline axis; and
a stator assembly including a plurality of stator vanes arranged circumferentially about the stator assembly and including at least one pair of non-uniform gaps between adjacent stator vanes, the plurality of stator vanes comprising:
a first group of stator vanes having a first non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the first group of stator vanes;
a second group of stator vanes having a second non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the second group of stator vanes, the first non-uniform gap being equal to, and positioned 180° from, the second non-uniform gap;
a third group of stator vanes having a uniform spacing between adjacent stator vanes of the third group of stator vanes;
a fourth group of stator vanes having a third non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the fourth group of stator vanes; and
a fifth group of stator vanes having a fourth non-uniform gap of the at least one pair of non-uniform gaps between adjacent stator vanes of the fifth group of stator vanes, the third non-uniform gap being equal to, and positioned 180° from, the fourth non-uniform gap, and the third non-uniform gap and the fourth non-uniform gap being different than the first non-uniform gap and the second non-uniform gap, wherein the plurality of rotor blades direct air through the plurality of stator vanes.

12. The turbine engine of claim 11 , wherein a number of stator vanes of the stator assembly is even.

13. The turbine engine of claim 11 , wherein a number of rotor blades of the plurality of rotor blades is even.

14. The turbine engine of claim 11 , wherein the plurality of rotor blades is uniformly spaced circumferentially about the rotor assembly.

15. The turbine engine of claim 11 , wherein the stator assembly is positioned downstream of the rotor assembly.

16. The turbine engine of claim 11 , wherein the at least one pair of non-uniform gaps is sized to prevent a zero nodal diameter system response and a one nodal diameter response.

17. The turbine engine of claim 11 , wherein the air directed through the plurality of stator vanes causes a vibration response on the plurality of stator vanes, and the at least one pair of non-uniform gaps balances the vibration response on the plurality of stator vanes about the stator assembly.

18. The turbine engine of claim 11 , wherein the first group of stator vanes includes two stator vanes of the plurality of stator vanes, and the second group of stator vanes includes two stator vanes of the plurality of stator vanes.

19. The turbine engine of claim 11 , wherein the first non-uniform gap is a function of a number of rotor blades of the plurality of rotor blades, a number of stator vanes of the plurality of stator vanes, and the uniform spacing.

20. The turbine engine of claim 19 , wherein the second non-uniform gap is a function of the number of stator vanes of the plurality of stator vanes, the uniform spacing, and the first non-uniform gap.

Assignees

• Gen Electric

Inventors

• Capps Drew M

Classifications

• F05D2260/961

  by mistuning rotor blades or stator vanes with irregular interblade spacing, airfoil shape · CPC title

• F05D2240/24

  for turbines · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F05D2220/323

  for aircraft propulsion, e.g. jet engines · CPC title

• F01D9/04

  forming ring or sector · CPC title