Self crystalline orientation for increased compliance
Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation.
1. A seal for a rotary component of a gas turbine engine, the seal comprising:
plural members, including a first member defining a first beam, a second member defining a second beam, and a third member defining a shoe,
the plural members being spaced in a radial direction, the first member being disposed at a radial outer end of the seal, the second member being disposed on a radial middle of the seal, and the third member being disposed at a radial inner end of the seal;
the plural members extending in a lengthwise direction, the first member and second member being connected at a lengthwise inner end of the seal, and the plural members being connected at a lengthwise outer end of the seal;
wherein the seal comprises a single crystalline structure that is oriented such that a natural frequency for at least two of the plural members differs;
wherein the orientation of the single crystalline structure provides for the natural frequency being greater than a frequency associated with a speed of the rotary component in an amount greater than a threshold.
2. The seal of claim 1 , wherein the single crystalline structure is a nickel-based alloy.
3. The seal of claim 1 , wherein the orientation of the single crystalline structure accommodates a requirement associated with at least a geometrical profile of the seal.
4. The seal of claim 3 , wherein the geometrical profile is specified in terms of at least a radius of the seal.
5. The seal of claim 3 , wherein the geometrical profile is specified in terms of at least a length of at least one of the first beam or the second beam.
6. The seal of claim 1 , wherein the orientation of the single crystalline structure accommodates a requirement associated with at least a range of deflection associated with the seal.
7. The seal of claim 1 , wherein the seal is included in the engine.
8. The seal of claim 1 , wherein the seal is included in the engine of an aircraft.
9. The seal of claim 8 , wherein the seal is associated with one of a fan section of the engine, a compressor section of the engine, or a turbine section of the engine.
10. The seal of claim 1 , wherein the seal is configured as an aerodynamic seal and is coupled to a first structure that is fixed and a second structure that rotates relative to the first structure, the second structure including the rotary component.
11. The seal of claim 1 , wherein the crystalline orientation is specified by the triple <111>.
12. The seal of claim 1 , wherein the seal includes a first tab at the lengthwise inner end of the seal, the first tab extending in the radial outer direction from the radial outer end of the seal for mounting to a ground.
13. The seal of claim 12 , wherein the seal includes a second tab at the lengthwise outer end of the seal, the second tab extending in the lengthwise outer direction from the radial inner end of the seal.
14. A method for designing a seal, comprising:
obtaining a requirement associated with at least:
a natural frequency associated with the seal;
selecting a crystalline orientation for a single crystal material of the seal based on the requirement; and
fabricating the seal based on the selected crystalline orientation,
wherein the crystalline orientation provides for the natural frequency being greater than a frequency associated with a speed of a rotating component in an amount that is greater than a threshold.
15. The method of claim 14 , wherein the requirement is associated with at least a geometrical profile of the seal.
16. The method of claim 15 , wherein the geometrical profile is specified in terms of at least a radius of the seal.
17. The method of claim 15 , wherein the geometrical profile is specified in terms of at least a length of at least one beam of the seal.
18. The method of claim 14 , wherein the requirement is associated with at least a range of deflection associated with the seal.
19. The method of claim 14 , wherein the requirement is associated with at least a temperature range over which the seal is to operate.
20. The method of claim 14 , wherein the crystalline orientation is specified by the triple <111>.
21. A gas turbine engine including a rotating component, the rotating component including a fluid seal, the seal comprising:
plural members, including a first member defining a first beam, a second member defining a second beam, and a third member defining a shoe,
the plural members being spaced in a radial direction, the first member being disposed at a radial outer end of the seal, the second member being disposed on a radial middle of the seal, and the third member being disposed at a radial inner end of the seal;
the plural members extending in a lengthwise direction, the first member and second member being connected at a lengthwise inner end of the seal, and the plural members being connected at a lengthwise outer end of the seal;
wherein the seal comprises a single crystalline structure that is oriented such that a natural frequency for at least two of the plural members differs.