Acoustic Treatment on Turbine Vane Ring Shrouds
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Solution Overview
Problem
In aircraft turbine engines, the limited space within narrow and short nacelles and the absence of acoustic treatment on ring vanes lead to reduced noise reduction effectiveness, as conventional acoustic panels cannot cover sufficient surface area without compromising structural integrity.
Innovation Solution
A ring of vanes with integrated acoustic treatment panels featuring resonant cavities and a sandwich structure, combining acoustic and aerodynamic functions, which extends treatment area and enhances mechanical strength while minimizing weight and complexity.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If acoustic treatment panels are installed in conventional locations (inside nacelle and primary cover), then noise reduction is achieved, but the available surface area for treatment is limited due to narrow and short nacelle dimensions
Solution Approach 1:
The invention extends acoustic treatment from the conventional two-dimensional surfaces (inside nacelle and primary cover) to the three-dimensional surface of the outlet guide vane ring itself. By treating the inner and outer shrouds of the OGV ring, the treatment area is expanded into a new spatial dimension that was previously unused for acoustic purposes.
Solution Approach 2:
The outlet guide vane ring is given a dual function: it maintains its aerodynamic role while simultaneously serving as a mounting structure for acoustic treatment panels. The inner and outer shrouds of the ring become both structural aerodynamic components and acoustic treatment carriers.
2Area of stationary object
If acoustic treatment panels are installed on the ring of outlet guide vanes, then the acoustic treatment area is increased, but the structural integrity of the ring may be compromised
Solution Approach 1:
The acoustic treatment on the ring is implemented in segmented form through discrete panels mounted on the inner and outer shrouds. These panels are attached at specific locations rather than covering the entire surface continuously, allowing the ring structure to maintain its structural integrity while still providing effective acoustic treatment at critical areas.
Solution Approach 2:
Acoustic treatment panels are applied selectively to specific regions of the inner and outer shrouds where acoustic treatment is most beneficial, rather than uniformly across the entire ring. This localized approach maximizes acoustic effectiveness while minimizing impact on structural integrity.
3Strength
If rigid platforms with ribbing are used to strengthen the ring structure, then structural integrity is improved, but acoustic leakage zones are created and design constraints increase
Solution Approach 1:
The invention merges the structural reinforcement function with the acoustic treatment function by integrating acoustic panels directly onto the inner and outer shrouds of the ring. This combination eliminates the need for separate rigid platforms with ribbing, as the acoustic panels themselves provide the necessary structural support while preventing acoustic leakage.
Solution Approach 2:
The acoustic treatment panels serve multiple functions simultaneously: they provide acoustic treatment, reinforce the ring structure, and eliminate acoustic leakage zones. This multi-functionality replaces the need for dedicated rigid platforms that would otherwise be required for structural support.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The solution achieves a 35% gain in acoustic treatment area and increases treated area downstream from the fan by 20-40%, effectively reducing sound propagation while maintaining structural integrity and aerodynamic performance.
Implementation Method 1
acoustic treatment panels including resonant cavities
Implementation Method 2
passive acoustic treatment panel is generally made up of a structure forming resonant cavities that is covered by a thin porous layer
Data Source
AI summary
A ring of vanes for an aircraft turbine engine, the ring presenting an axial direction and a radial direction and including a first annular sheath presenting an inside surface and a second annular sheath presenting an inside surface facing the first inside surface of the first annular sheath, the first and second sheaths being coaxial and defining between them a flow passage for a gas stream. The ring further includes both partially annular acoustic treatment panels including resonant cavities and also vanes extending in the radial direction between the first and second sheaths. Each vane includes a radial airfoil with at least two attachment tabs at each radial end of the airfoil fastened to the first or second sheath, and the inside surface of at least one of the first and second annular sheaths and the corresponding attachment tabs are covered by acoustic treatment panels arranged between the airfoils.