Self retained linkage and system including the self retained linkage for a gas turbine engine
A variable vane assembly for a gas turbine engine, the variable vane assembly including: a plurality of vanes arranged into a plurality of stages, each one of the plurality of vanes being configured for rotation about an axis through movement of a vane arm secured to each one of the plurality of vanes at one end and a sync ring of each one of the plurality of stages at another end; and a plurality of bell cranks operably coupling the sync ring of each one of the plurality of stages to a self-retained linkage via a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.
1. A variable vane assembly for a gas turbine engine, comprising:
a plurality of vanes arranged into a plurality of stages, each one of the plurality of vanes being configured for rotation about an axis through movement of a vane arm secured to each one of the plurality of vanes at one end and a sync ring of each one of the plurality of stages at another end; and
a plurality of bell cranks operably coupling the sync ring of each one of the plurality of stages to a self-retained linkage via a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.
2. The variable vane assembly as in claim 1 , wherein each one of the plurality of bell cranks are also pivotally secured to a bracket.
3. The variable vane assembly as in claim 2 , wherein each one of the plurality of bell cranks are operably coupled to the sync ring of each one of the plurality of stages via a link.
4. The variable vane assembly as in claim 1 , wherein each one of the plurality of bell cranks are operably coupled to the sync ring of each one of the plurality of stages via a link.
5. The variable vane assembly as in claim 1 , wherein an even number of the plurality of bell cranks are secured to the self-retained linkage.
6. The variable vane assembly as in claim 3 , wherein an odd number of the plurality of bell cranks are secured to the self-retained linkage.
7. A gas turbine engine, comprising:
a fan section;
a compressor section;
a combustor section;
a turbine section; and
a variable vane assembly, the variable vane assembly, comprising:
a plurality of vanes arranged into a plurality of stages, each one of the plurality of vanes being configured for rotation about an axis through movement of a vane arm secured to each one of the plurality of vanes at one end and a sync ring of each one of the plurality of stages at another end; and
a plurality of bell cranks operably coupling the sync ring of each one of the plurality of stages to a self-retained linkage via a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.
8. The gas turbine engine of claim 7 , wherein each one of the plurality of bell cranks are also pivotally secured to a bracket.
9. The gas turbine engine of claim 8 , wherein each one of the plurality of bell cranks are operably coupled to the sync ring of each one of the plurality of stages via a link.
10. The gas turbine engine of claim 7 , wherein each one of the plurality of bell cranks are operably coupled to the sync ring of each one of the plurality of stages via a link.
11. The gas turbine engine of claim 9 , wherein an even number of the plurality of bell cranks are secured to the self-retained linkage.
12. The gas turbine engine of claim 7 , wherein an odd number of the plurality of bell cranks are secured to the self-retained linkage.
13. The gas turbine engine of claim 12 , wherein each one of the plurality of bell cranks are also pivotally secured to a bracket.
14. The gas turbine engine of claim 7 , wherein the variable vane assembly is located in a low pressure compressor of the compressor section of the gas turbine engine.
15. The gas turbine engine of claim 7 , wherein the variable vane assembly is located in a high pressure compressor of the compressor section of the gas turbine engine.
16. A method of rotating a plurality of vanes of a variable vane assembly of a gas turbine, comprising:
coupling a plurality of bell cranks to a plurality of stages of the variable vane assembly via a self-retained linkage, the self-retained linkage interfacing with a stud of each one of the plurality of bell cranks, the stud of each one of the plurality of bell cranks being rotatably received in a corresponding opening of the self-retained linkage in an alternating fashion such that only a single shear interface is provided between each one of the plurality of bell cranks and the self-retained linkage.
17. The method of claim 16 , further comprising pivotally securing each one of the plurality of bell cranks to a bracket.
18. The method of claim 16 , wherein each one of the plurality of bell cranks are operably coupled to a sync ring of each one of the plurality of stages via a link.
19. The method as in claim 18 , wherein an even number of the plurality of bell cranks are secured to the self-retained linkage.
20. The method as in claim 16 , wherein an odd number of the plurality of bell cranks are secured to the self-retained linkage.