EP-4737686-A1 - FAN EXIT GUIDE VANE WITH ACOUSTIC TREATMENT, FAN EXIT GUIDE VANE SYSTEM, GAS TURBINE ENGINE AND PROCESS FOR FORMING A FAN EXIT GUIDE VANE WITH ACOUSTIC TREATMENT

EP4737686A1EP 4737686 A1EP4737686 A1EP 4737686A1EP-4737686-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; an acoustic panel receiver formed within the fan exit guide vane 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 the leading edge and the trailing edge; and an acoustic panel inserted into the acoustic panel receiver. A fan exit guide vane system with acoustic treatment for a gas turbine engine includes fan exit guide vane with acoustic treatment. A gas turbine engine includes the fan exit guide vane system with acoustic treatment for a gas turbine engine. 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)

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 panel receiver formed within the fan exit guide vane extendable 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; and an acoustic panel inserted into the acoustic panel receiver.
The fan exit guide vane with acoustic treatment according to claim 1, wherein the acoustic panel receiver is one of at least two acoustic panel receivers formed in the fan exit guide vane at predetermined locations along the span of the fan exit guide vane.
The fan exit guide vane with acoustic treatment according to claim 1 or 2, wherein the acoustic panel receiver is located on the pressure side of the fan exit guide vane.
The fan exit guide vane with acoustic treatment 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 fan exit guide vane with acoustic treatment 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 fan exit guide vane with acoustic treatment according to any of claims 1 to 5, wherein the acoustic panel is configured slidable into the acoustic panel receiver.
The fan exit guide vane with acoustic treatment 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 fan exit guide vane system with acoustic treatment for a gas turbine engine, the FEGV system 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 each fan exit guide vane of the array of fan exit guide vanes comprises a configuration as claimed in any of claims 1 to 7.
A gas turbine engine comprising an fan exit guide vane system 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 each fan exit guide vane of the array of fan exit guide vanes comprises a configuration as claimed in any of claims 1 to 7.
A process for a fan exit guide vane with acoustic treatment comprising: locating a fan within a fan duct; supporting an array of fan exit guide vanes within the fan duct downstream from the 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; coupling a radially inner attachment region of each fan exit guide vane of the array of fan exit guide vanes in operative communication with the radially inner surface of the fan duct; coupling a radially outer attachment region of each 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 panel receiver within each fan exit guide vane 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 of each fan exit guide vane; and inserting an acoustic panel into the acoustic panel receiver.
The process according to claim 10, further comprising: forming the acoustic panel receiver in each of the fan exit guide vanes at predetermined locations along a span of the fan exit guide vanes.
The process according to claim 10 or 11, 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 10 to 12, further comprising: locating the acoustic panel receiver on the pressure side of each fan exit guide vane.
The process according to any of claims 10 to 13, further comprising: configuring the acoustic panel slidable into the acoustic panel receiver.
The process according to any of claims 10 to 14, further comprising: configuring the acoustic panel interchangeable to accommodate design changes and/or damage to the acoustic panel; and/or further comprising: shaping the acoustic panel to influence acoustic dampening capability in the proximity of the fan exit guide vane.

Description

The present disclosure is directed to the improved interchangeable acoustic strips and panels for 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 panel receiver formed within the fan exit guide vane extendable 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; 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 one of at least two acoustic panel receivers 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 panel receiver is located on the pressure side. 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, a tee shaped cross section. 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 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 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; 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 panel receiver form