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EP-4737685-A1 - FAN EXIT GUIDE VANE WITH ACOUSTIC TREATMENT, GAS TURBINE ENGINE AND PROCESS FOR FORMING A FAN EXIT GUIDE VANE WITH ACOUSTIC TREATMENT

EP4737685A1EP 4737685 A1EP4737685 A1EP 4737685A1EP-4737685-A1

Abstract

A fan exit guide vane with acoustic treatment includes a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; and an acoustic zone integrally formed within the fan exit guide vane. A gas turbine engine includes the fan exit guide vane with acoustic treatment. A process forms the fan exit guide vane with acoustic treatment.

Inventors

  • YAZICI, Murat
  • BREAULT, ANDREW E.
  • MORTON, JEFFREY T.

Assignees

  • RTX Corporation

Dates

Publication Date
20260506
Application Date
20251029

Claims (15)

  1. A fan exit guide vane comprising: a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; an acoustic zone formed within the fan exit guide vane.
  2. The fan exit guide vane according to claim 1, wherein the acoustic zone is formed in the fan exit guide vane at a predetermined location along the span of the fan exit guide vane.
  3. The fan exit guide vane according to claim 1 or 2, wherein the acoustic zone is located on the pressure side of the fan exit guide vane.
  4. The fan exit guide vane according to any of claims 1 to 3, wherein the acoustic zone extends at least one of spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region or chordwise between the leading edge and the trailing edge.
  5. The fan exit guide vane according to any of claims 1 to 4, further comprising: an acoustic treatment formed within the acoustic zone, the acoustic treatment configured to dissipate sound energy.
  6. The fan exit guide vane according to any of claims 1 to 5, wherein the acoustic zone is configured integral with the material of the fan exit guide vane.
  7. The fan exit guide vane according to any of claims 1 to 6, wherein the acoustic zone is located adjacent a structural region.
  8. The fan exit guide vane with acoustic treatment according to any of claims 1 to 7, wherein the acoustic zone is located on the pressure side of the fan exit guide vane.
  9. A gas turbine engine with a fan exit guide vane with acoustic treatment comprising: a fan located within a fan duct; and an array of fan exit guide vanes supported within the fan duct downstream from the fan, the array of fan exit guide vanes span across the fan duct attached to a radially inner surface of the fan duct and a radially outer surface of the fan duct; wherein a fan exit guide vane of the array of fan exit guide vanes comprises the configuration of the fan exit guide vane according to any of claims 1 to 8 and a structural region adjacent the acoustic zone.
  10. A process for creating a fan exit guide vane with acoustic treatment comprising: supporting an array of fan exit guide vanes within a fan duct downstream from a location associated with a fan; attaching the array of fan exit guide vanes spanned across the fan duct to a radially inner surface of the fan duct and a radially outer surface of the fan duct by; coupling a radially inner attachment region of the fan exit guide vane of the array of fan exit guide vanes in operative communication with the radially inner surface of the fan duct; and coupling a radially outer attachment region of the fan exit guide vane of the array of fan exit guide vanes in operative communication with the radially outer surface of the fan duct; forming an acoustic zone integral with the fan exit guide vane; and forming a structural region adjacent the acoustic zone.
  11. The process according to claim 10, further comprising: forming the acoustic zone in the fan exit guide vane at a predetermined location of the fan exit guide vane.
  12. The process according to claim 10 or 11, further comprising: forming the acoustic treatment within the acoustic zone; and configuring the acoustic treatment to dissipate sound energy.
  13. The process according to claim any of claims 10 to 12, further comprising: locating the acoustic zone on the pressure side of the fan exit guide vane.
  14. The process according to any of claims 10 to 13, further comprising: configuring the acoustic zone extending at least one of spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region or chordwise between a leading edge and a trailing edge.
  15. The process according to any of claims 10 to 14, further comprising: forming a surface skin in operative communication with an exterior of the fan exit guide vane proximate the acoustic treatment; and/or further comprising: shaping the acoustic zone to influence acoustic dampening capability in the proximity of the fan exit guide vane.

Description

The present disclosure is directed to the improved acoustic zone integrally formed in a fan exit guide vane structure. Current gas turbine engine design, as seen in Fig. 1 through Fig. 4a, includes a design with variable or non-variable fan exit guide vanes (FEGV). The fan F is positioned within the fan duct FD proximate the engine inlet EI. The fan exit guide vanes (FEGV) are downstream from the fan F and located forward of the bypass duct BD. A current FEGV pattern is created to minimize airflow back pressure adverse effect on fan blades F caused by the downstream presence of nacelle N bypass duct BD elements (Fig. 2), such as the upper and lower bifurcation BiFi, air-to-oil cooler (AOC), and environmental control system inlet ECS. As seen in Fig. 3, the FEGV has a circumferential pattern CP made up of vanes V that can translate the structural load path LP shown as arrows in Fig. 4. All vane types are designed with the same cross sectional monolithic load carrying features (Fig. 4a). Additionally, the FEGV pattern aims to optimize the fan duct performance and acoustic characteristics of the gas turbine engine. The FEGV pattern is defined to meet structural, performance and acoustic requirements across a wide range of operating conditions. It is therefore not optimized at any single mission condition, like cruise condition or climb condition. Engine noise targets are getting more challenging for future programs. Engine and airframe makers are looking for more opportunities for noise reduction. At the engine side, acoustic treatable areas are limited. Fan exit guide vanes are an area for noise reduction opportunities. In accordance with the present disclosure, there is provided a fan exit guide vane with acoustic treatment comprising a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; an acoustic zone formed within the fan exit guide vane. Particular embodiments further may include at least one, or a plurality of, the following optional features, alone or in combination with each other: A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone is formed in the fan exit guide vane at predetermined locations along the span of the fan exit guide vane. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone is located on the pressure side of the fan exit guide vane. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone extends at least one of spanwise through the fan exit guide vane between the radially inner attachment region and the radially outer attachment region or chordwise between the leading edge and the trailing edge. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the fan exit guide vane with acoustic treatment further comprising the acoustic treatment formed within the acoustic zone, the acoustic treatment configured to dissipate sound energy. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone is configured integral with the material of the fan exit guide vane. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone is located adjacent a structural region. In accordance with the present disclosure, there is provided a gas turbine engine with a fan exit guide vane with acoustic treatment comprising a fan located within a fan duct; an array of fan exit guide vanes supported within the fan duct downstream from the fan, the array of fan exit guide vanes span across the fan duct attached to a radially inner surface of the fan duct and a radially outer surface of the fan duct; wherein a fan exit guide vane of the array of fan exit guide vanes comprising a leading edge and a trailing edge opposite chordwise from the leading edge; a radially inner attachment region opposite spanwise from a radially outer attachment region; a span dimension extending between the radially inner attachment region and the radially outer attachment region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the fan exit guide vane; an acoustic zone integrally formed within the fan exit guide vane; and a structural region adjacent the acoustic zone. Particular embodiments further may include at least one, or a plurality of, the following optional features, alone or in combination with each other: A further embodiment