EP-4737309-A1 - SWIRL RECOVERY VANE WITH ACOUSTIC TREATMENT, GAS TURBINE ENGINE AND PROCESS FOR FORMING A SWIRL RECOVERY VANE

EP4737309A1EP 4737309 A1EP4737309 A1EP 4737309A1EP-4737309-A1

Abstract

A swirl recovery vane with acoustic treatment includes 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 panel receiver formed within the swirl recovery vane extending 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; and an acoustic panel inserted into the acoustic panel receiver. 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 panel receiver formed within the swirl recovery vane extending 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; and an acoustic panel inserted into the acoustic panel receiver.
The swirl recovery vane according to claim 1, wherein the acoustic panel receiver is one of at least two acoustic panel receivers formed in the swirl recovery vane at predetermined locations along the span of the swirl recovery vane.
The swirl recovery vane according to claim 1 or 2, wherein the acoustic panel receiver is located on the pressure side.
The swirl recovery vane according to any of claims 1 to 3, wherein the acoustic panel receiver comprises at least one of a rectangular cross section, an oval cross section, or a tee shaped cross section.
The swirl recovery vane according to any of claims 1 to 4, further comprising: the acoustic treatment formed within the acoustic panel, the acoustic treatment configured to dissipate sound energy.
The swirl recovery vane according to any of claims 1 to 5, wherein the acoustic panel is configured slidable into the acoustic panel receiver.
The swirl recovery vane according to any of claims 1 to 6, wherein the acoustic panel is configured interchangeable to accommodate design changes and/or damage to the acoustic panel.
A gas turbine engine with a swirl recovery vane with acoustic treatment comprising: a propulsor rotor located within an open environment; and an array of swirl recovery vanes downstream from the propulsor rotor, the array of swirl recovery vanes attached to a nacelle flow surface; wherein each swirl recovery vane of the array of swirl recovery vanes comprising a configuration as claimed in any of claims 1 to 7.
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 panel receiver within the swirl recovery vane 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; and inserting an acoustic panel into the acoustic panel receiver.
The process according to claim 9, further comprising: forming the acoustic panel receiver in the swirl recovery vane at predetermined locations along the span of the swirl recovery vane.
The process according to claim 9 or 10, further comprising: forming the acoustic treatment within the acoustic panel; and configuring the acoustic treatment to dissipate sound energy.
The process according to any of claims 9 to 11, further comprising: locating the acoustic panel receiver on the pressure side of the swirl recovery vane.
The process according to any of claims 9 to 12, further comprising: configuring the acoustic panel slidable into the acoustic panel receiver.
The process according to any of claims 9 to 13, further comprising: configuring the acoustic panel interchangeable to accommodate design changes and/or damage to the acoustic panel.
The process according to any of claims 9 to 14, further comprising: shaping the acoustic panel to influence acoustic dampening capability in the proximity of the swirl recovery vane.

Description

The present disclosure is directed to the improved interchangeable acoustic strips and panels for 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 panel receiver formed within the swirl recovery vane extending 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; and an acoustic panel inserted into the acoustic panel receiver. 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 panel receiver 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 panel receiver is located on the pressure side of the swirl recovery vane. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic panel receiver comprises at least one of a rectangular cross section, an oval cross section, or a tee shaped cross section. 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 panel, 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 panel is configured slidable into the acoustic panel receiver. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic panel is configured interchangeable to accommodate design changes and/or damage to the acoustic panel. 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 downstream from the propulsor rotor, the array of swirl recovery vanes attached to a nacelle flow surface; wherein each swirl recovery vane of the array of swirl recovery vanes comprises 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 panel receiver formed within the swirl recovery vane 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; and an acoustic panel inserted into the acoustic panel receiver. 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 panel receiver is one of at least two acoustic panel receivers 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 gas turbine engine with a swirl recovery vane with acoustic treatment further comprising the acoustic treatment formed within the acoustic panel, 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 panel receiver is located on the pressure side of the swirl recovery vane. A further embodiment of any of the foregoing embodiments may additionally and/or alternatively include the acoustic panel receiver comprises at least one of a re