EP-4737310-A1 - SWIRL RECOVERY VANE WITH ACOUSTIC TREATMENT, GAS TURBINE ENGINE AND PROCESS FOR FORMING A SWIRL RECOVERY VANE

EP4737310A1EP 4737310 A1EP4737310 A1EP 4737310A1EP-4737310-A1

Abstract

A swirl recovery vane with acoustic treatment including a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone integrally formed within the swirl recovery vane. A gas turbine engine includes the swirl recovery vane with acoustic treatment. A process forms the swirl recovery 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)

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

Description

The present disclosure is directed to the improved acoustic zone integrally formed in a swirl recovery vane structure. The swirl recovery vane pattern is defined to meet structural, performance and acoustic requirements across a wide range of operating conditions. Engine noise is challenging for open rotor architectures. Engine and airframe makers are looking for more opportunities for noise reduction. At the engine side, acoustic treatable areas are limited. Swirl recovery vanes are an area for noise reduction opportunities. In accordance with the present disclosure, there is provided a swirl recovery vane with acoustic treatment comprising a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone formed within the swirl recovery 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 swirl recovery vane at predetermined locations along the span of the swirl recovery 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. 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 swirl recovery vane between the attachment region and the tip 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 swirl recovery 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 swirl recovery 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 swirl recovery vane with acoustic treatment comprising a propulsor rotor located within an open environment; an array of swirl recovery vanes supported downstream from the propulsor rotor, the array of swirl recovery vanes attached to a nacelle flow surface; a leading edge and a trailing edge opposite chordwise from the leading edge; an attachment region opposite spanwise from a tip region; a span dimension extending between the attachment region and the tip region; a chord dimension extending between the leading edge and the trailing edge; a pressure side opposite a suction side of the swirl recovery vane; an acoustic zone integrally formed within the swirl recovery vane; and a structural region adjacent the acoustic zone. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic zone is formed in the swirl recovery vane at predetermined locations along the span of the swirl recovery 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 includethe gas turbine engine with a swirl recovery 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 located on the pressure side. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the gas turbine engine with a swirl recovery vane with acoustic treatment further comprising a surface skin in operative communication with the acoustic zone and the acoustic treatment. 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 swirl recovery vane between the attachment region and the tip region or chordwise between the leading edge and the trailing edge. In accordance with the present disclosure, there is provided a process for gas turbine engine with a swirl recovery vane with acoustic treatment comprising locating a propulsor rotor within an open environment; supporti