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EP-4265887-B1 - ROTOR ASSEMBLY WITH ACTIVE DAMPING FOR GAS TURBINE ENGINES

EP4265887B1EP 4265887 B1EP4265887 B1EP 4265887B1EP-4265887-B1

Inventors

  • HUSBAND, JASON
  • Glaspey, James
  • WELCH, DAVID A.

Dates

Publication Date
20260513
Application Date
20191016

Claims (11)

  1. An airfoil (66, 166, 266, 366, 466, 566, 566', 666, 766) for a gas turbine engine (20) comprising: an airfoil section (66A, 166A, 266A, 366A, 466A, 566A, 666A, 766A) extending from a root section (66B, 266B, 366B, 466B, 566B, 666B, 766B), wherein the airfoil section (66A...766A) extends between a leading edge (LE) and a trailing edge (TE) in a chordwise direction (C) and extends between a tip portion (66C, 266C, 466C, 766C) and the root section (66B...766B) in a radial direction (R), the airfoil section (66A...766A) defines a pressure side (P) and a suction side (S) separated in a thickness direction (T), and the airfoil section (66A...766A) includes a metallic sheath (72, 172, 272, 372, 472, 572, 672) that defines an internal cavity receiving a composite core (74, 174, 274, 474, 574, 774), and the root section (66B...766B) defines at least one bore (85, 485) dimensioned to receive a retention pin (68, 168, 368, 468, 568, 668); and at least one damping element (487, 487', 587, 587', 687, 787) received in the internal cavity and that selectively applies a compressive load to the airfoil section (66A...766A) to cause the airfoil section (66A...766A) to stiffen.
  2. The airfoil as recited in claim 1, wherein the at least one damping element (487...787) comprises a piezoelectric material.
  3. The airfoil as recited in claim 1, wherein the at least one damping element (487...787) abuts against the core (74...774).
  4. The airfoil as recited in claim 2 or 3, further comprising at least one sensor (495, 695, 795) received in the internal cavity, wherein the at least one damping element (487...787) is responsive to a control signal based on information from the at least one sensor (495, 695, 795).
  5. The airfoil as recited in any preceding claim, wherein: the sheath (72...672) includes a first skin (72A, 172A, 272A, 472A, 572A, 772A) and a second skin (72B, 272B, 472B, 572B, 772B) joined together to define the pressure and suction sides (P, S) of the airfoil section (66A...766A); the core (74...774) includes first and second ligaments (76A, 76B, 476A, 476B) received in respective internal channels defined by the first skin (72A... 772A) such that the first and second ligaments (76A, 76B, 476A, 476B) are spaced apart along the root section (66B... 766B) with respect to the chordwise direction (C); and the first and second ligaments (76A, 76B, 476A, 476B) define respective bores (85, 485) of the at least one bore (85, 485), and the respective bores (85, 485) are aligned to receive a common retention pin (68...668),
  6. The airfoil as recited in claim 5, wherein each one of the ligaments (76A, 76B, 476A, 476B) includes at least one interface portion (78, 178, 278, 478, 578, 778) in the root section (66B...766B), and each one of the ligaments (76A, 76B, 476A, 476B) includes at least one composite layer (80, 580, 580') that loops around the at least one interface portion (78...778) such that opposed end portions (80A, 80B) of the at least one composite layer (80, 580, 580') are joined together along the airfoil section (66A... 766A).
  7. The airfoil as recited in claim 5 or 6, wherein the at least one damping element (487...787) includes first and second damping elements (487-1, 487-2, 587-1, 587-2) adjacent respective ones of the first and second ligaments (76A, 76B, 476A, 476B).
  8. The airfoil as recited in claim 7, wherein the at least one composite layer (80, 580, 580') includes a first layer (80C) and a second layer (80D), the first layer (80C) between the second layer (80D) and one of the internal channels, the first layer (80C) defining a first fiber construction including at least one ply of unidirectional fibers, and the second layer (80D) defining a second fiber construction that differs from the first fiber construction and including at least one ply of a three dimensional weave of fibers.
  9. The airfoil as recited in claim 6 or 7, wherein the first and second damping elements (487-1, 487-2, 587-1, 587-2) are independently adjustable in response to separate and distinct control signals.
  10. The airfoil as recited in any of claims 7 to 9, wherein the first and second damping elements (487-1, 487-2, 587-1, 587-2) each comprise at least one layer of piezoelectric material that extends in a radial direction (R) between the root section (66B...766B) and the tip portion (66C, 266C, 466C, 766C).
  11. The airfoil as recited in any of claims 7 to 10, wherein the first (72A...772A) and second skins (72B...772B) comprise titanium, and the composite core (74...774) comprises carbon.

Description

BACKGROUND This disclosure relates to a gas turbine engine, and more particularly to a rotor assembly including a hub that carries an array of airfoils. Gas turbine engines can include a fan for propulsion air and to cool components. The fan also delivers air into a core engine where it is compressed. The compressed air is then delivered into a combustion section, where it is mixed with fuel and ignited. The combustion gas expands downstream over and drives turbine blades. Static vanes are positioned adjacent to the turbine blades to control the flow of the products of combustion. The fan typically includes an array of fan blades having dovetails that are mounted in slots of a fan hub. US 8,569,928 discloses a method for influencing, damping, or suppressing mechanical vibrations occurring during operation in a turbomachine blade. FR 2,951,223 discloses a part for a turbomachine of an aircraft. SUMMARY An airfoil for a gas turbine engine according to an aspect of the present invention is provided in accordance with claim 1. In a further embodiment of any of the foregoing embodiments, the at least one damping element comprises a piezoelectic material. In a further embodiment of any of the foregoing embodiments, the at least one damping element abuts against the core. A further embodiment of any of the foregoing embodiments includes at least one sensor received in the internal cavity. The at least one damping element is responsive to a control signal based on information from the at least one sensor. In a further embodiment of any of the foregoing embodiments, the sheath includes a first skin and a second skin joined together to define the pressure and suction sides of the airfoil section. The core includes first and second ligaments received in respective internal channels defined by the first skin such that the first and second ligaments are spaced apart along the root section with respect to the chordwise direction. The first and second ligaments define respective bores of the at least one bore, and the respective bores are aligned to receive a common retention pin. In a further embodiment of any of the foregoing embodiments, each one of the ligaments includes at least one interface portion in the root section, and each one of the ligaments includes at least one composite layer that loops around the at least one interface portion such that opposed end portions of the at least one composite layer are joined together along the airfoil section. In a further embodiment of any of the foregoing embodiments, the at least one damping element includes first and second damping element adjacent respective ones of the first and second ligaments. In a further embodiment of any of the foregoing embodiments, the at least one composite layer includes a first layer and a second layer. The first layer is between the second layer and one of the internal channels. The first layer defines a first fiber construction including at least one ply of unidirectional fibers, and the second layer defining a second fiber construction that differs from the first fiber construction and including at least one ply of a three dimensional weave of fibers. In a further embodiment of any of the foregoing embodiments, the at least one damping element includes first and second damping element adjacent respective ones of the first and second ligaments. In a further embodiment of any of the foregoing embodiments, the first and second damping element are independently adjustable in response to separate and distinct control signals. In a further embodiment of any of the foregoing embodiments, the first and second damping element each comprise at least one layer of piezeoelectic material that extends in a radial direction between the root section and the tip portion. In a further embodiment of any of the foregoing embodiments, the first and second skins comprise titanium, and the core comprises carbon. The various features and advantages of this disclosure will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows. BRIEF DESCRIPTION OF THE DRAWINGS Figure 1 illustrates an example turbine engine.Figure 2 illustrates a perspective view of an example rotor assembly including an array of airfoils.Figure 3 illustrates a perspective view of one of the airfoils of Figure 2 secured to a hub.Figure 4 illustrates adjacent airfoils of the rotor assembly of Figure 2.Figure 5A illustrates an exploded view of portions of the rotor assembly of Figure 2.Figure 5B illustrates a side view of the rotor assembly of Figure 2 with the hub illustrated in cross-section.Figure 6 illustrates an end view of an airfoil section of one of the airfoils of Figure 2.Figure 7 illustrates an exploded view of the airfoil section of Figure 6.Figure 8 illustrates an exploded perspective view of an airfoil including the airfoil section of Figure 6.Figure 9 illustrates a se