Turbomachine Fan with Waveform Leading Edge
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Solution Overview
Problem
Current jet engine fan designs face inefficiencies due to excessive fan blade count, leading to increased cost and weight, which negatively impact fuel efficiency and aerodynamic stability, requiring a balance between fan blade quantity, chord width, and tip speed to optimize engine performance.
Innovation Solution
The implementation of a gas turbine engine design featuring a reduced fan blade count with increased average fan chord width and a specific fan blade configuration, utilizing polymer matrix composite materials with metal leading edges, and incorporating a waveform leading edge on airfoils to enhance aerodynamic efficiency and reduce noise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Weight of moving object
If fan blade count is reduced, then weight and cost are decreased, but aerodynamic stability and engine performance may be compromised
Solution Approach 1:
The patent changes key parameters of the fan blades: increasing average chord width, modifying tip speed, and altering blade configuration. These parameter changes allow the fan to maintain aerodynamic stability with fewer blades, resolving the contradiction between weight reduction and stability maintenance.
Solution Approach 2:
The patent employs polymer matrix composite materials with metal leading edges for the fan blades. This composite construction optimizes the strength-to-weight ratio, enabling reduced blade count while maintaining structural integrity and aerodynamic performance, thus reducing overall fan weight without compromising stability.
2Device complexity
If fan blade count is reduced, then cost and weight are decreased, but aerodynamic efficiency may deteriorate
Solution Approach 1:
By optimizing parameters such as increased average chord width and adjusted tip speed, the patent maintains aerodynamic efficiency with reduced blade count. The waveform leading edge design further enhances flow characteristics, ensuring efficient energy utilization despite simpler structure.
Solution Approach 2:
The patent introduces a waveform leading edge configuration on the airfoils, adding geometric complexity in a different dimension. This dimensional change allows the simplified blade count to compensate for reduced aerodynamic surface area through optimized flow attachment and reduced separation.
3Use of energy by moving object
If average fan chord width is increased, then aerodynamic efficiency is improved, but fan diameter and overall engine size may increase
Solution Approach 1:
The patent optimizes the relationship between chord width and fan diameter by carefully controlling the increase in chord dimensions. The waveform leading edge design enhances flow attachment, allowing efficiency improvements with more moderate diameter increases, thus balancing aerodynamic performance with engine size constraints.
Data Source
AI summary
A turbomachine includes an annular casing, a fan disposed inside the annular casing and mounted for rotation about an axial centerline, and an airfoil. The fan includes fan blades that extend radially outwardly toward the annular casing. The airfoil includes a first side and a second side coupled together at a leading edge and a trailing edge, a plurality of first chord sections defining at least one first chord length, and a plurality of second chord sections defining at least one second chord length. The plurality of first chord sections and second chord sections define a waveform along a leading edge of the airfoil. The fan has an average chord fan width according to a first performance factor. The fan has a quantity of fan blades according to a second performance factor.