Aircraft Engine Pylon Mounting With Rear Vibration Damper
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Solution Overview
Problem
The current mounting configuration of aircraft turbine engines, which involves a cantilevered attachment to the pylon, leads to issues such as lack of support for the rear portion of the engine, potential for low-frequency bending modes to be excited by unbalanced loads, and significant loads and vibrations at the base of the cantilever.
Innovation Solution
Incorporating a damper that connects the turbine engine to the pylon in a plane perpendicular to the engine's axis, located downstream of the combustion chamber, to limit relative displacements and vibrations without transmitting stresses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If the turbine engine is attached in a cantilever manner to the pylon, then the stress transmission between upstream and downstream attachment points is reduced, but the rear portion of the engine lacks support and experiences excessive displacements and vibrations
Solution Approach 1:
The attachment system is segmented into multiple functional zones: upstream suspension members for primary support, downstream suspension members for stress distribution, and a damper for vibration control. This segmentation allows each component to address specific aspects of the contradiction independently.
Solution Approach 2:
A damper is introduced as an intermediary component between the turbine engine and the pylon at the downstream location. This damper mediates the contradiction by providing support and limiting displacements without transmitting full stresses, thus supporting the rear portion while maintaining the stress-reduction benefit of cantilever attachment.
2Device complexity
If the turbine engine is attached in a cantilever manner to the pylon, then the structural complexity is reduced, but low-frequency bending modes are excited by unbalanced loads
Solution Approach 1:
The attachment system transitions from a static rigid structure to a dynamic system with controlled flexibility. The damper introduces dynamic damping characteristics that actively suppress bending mode vibrations while maintaining structural integrity, allowing the system to adapt to varying operational conditions.
Solution Approach 2:
The solution directly addresses the vibration problem by incorporating a damper specifically designed to suppress low-frequency bending modes. The damper utilizes mechanical vibration damping principles to dissipate energy from unbalanced loads, preventing resonance and excessive vibrations.
3Manufacturing precision
If the turbine engine is attached in a cantilever manner to the pylon, then the manufacturing precision requirements are reduced, but significant loads and vibrations occur at the base of the cantilever
Solution Approach 1:
The damper serves as an intermediary that decouples the vibration transmission path from the pylon base. By absorbing and dissipating vibrational energy at the downstream location, the damper prevents these forces from propagating to the base, reducing the loads experienced by the pylon structure.
Solution Approach 2:
The system changes the mechanical parameters of the attachment by introducing damping characteristics. This transforms the purely rigid or flexible connection into a viscoelastic system that can dissipate energy, thereby reducing the magnitude of forces transmitted to the pylon base during operational disturbances.
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 damper effectively dampens the rear portion of the turbine engine, preventing excessive displacements and vibrations, while ensuring stress transmission only when necessary, thus enhancing the structural integrity and operational stability of the turbine engine.
Implementation Method 1
at least one damper which connects the turbine engine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, this damper being configured to limit the relative displacements between the turbine engine and the pylon without transmitting stresses
Data Source
AI summary
Assembly including an aircraft turbine engine and a pylon for mounting the turbine engine to an element of the aircraft. The pylon includes members for suspending the turbine engine, the members being connected to the turbine engine in at least one plane which is perpendicular to the axis and which is located upstream of the combustion chamber of the turbine engine, such that the turbomachine is cantilevered to the pylon, The assembly further includes at least one damper which connects the turbomachine to the pylon and which is located in a plane perpendicular to the axis located downstream of the combustion chamber, the damper being configured to limit the relative movements between the turbine engine and the pylon without transmitting force.