Morphing Fan Inlet Guide Vanes for Non-Uniform Airflow Control
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing gas turbine engines with fan inlet variable vanes lack the ability to dynamically adjust the shape of the vanes to accommodate varying operating conditions, leading to suboptimal airflow direction and efficiency.
Innovation Solution
The implementation of a mechanism in the gas turbine engine that allows the trailing edge of the fan inlet vanes to morph by pivoting radial segments through a control rod and deformable supports, enabling independent or synchronized shape changes in response to operating conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Adaptability or versatility
If a monolithic flap is used to change the trailing edge angle, then the structure is simple, but the ability to adapt to non-axisymmetric conditions is limited
Solution Approach 1:
The trailing edge is divided into multiple independent radial segments that can pivot relative to each other, allowing non-uniform angle adjustments across the span. This segmentation enables the vane to adapt to non-axisymmetric conditions by varying the incident angle at different radial positions, while still maintaining a relatively simple overall structure through the use of flexible supports and a single control rod.
2Productivity
If the trailing edge angle is changed uniformly across the span, then the control mechanism is simple, but the airflow conditioning for non-axisymmetric conditions is suboptimal
Solution Approach 1:
Each radial segment can be positioned at a different angle relative to the leading edge, allowing local optimization of the incident angle at different spanwise locations. This local quality variation enables superior airflow conditioning for non-axisymmetric conditions, while the control mechanism remains relatively simple through the use of a single control rod with protrusions that interact with angled slots in each segment.
Solution Approach 2:
The radial segments are made dynamically adjustable through the control rod mechanism, allowing the trailing edge geometry to change in response to varying operating conditions. The flexible supports enable the segments to pivot and maintain their positions dynamically, providing adaptive airflow conditioning rather than a fixed geometry.
3Adaptability or versatility
If multiple independent actuators are used for each vane assembly, then independent control is achieved, but the device complexity increases
Solution Approach 1:
Multiple control functions are merged into a single control rod for each airfoil. The control rod incorporates multiple protrusions that interact with angled slots in different radial segments, allowing one actuator to independently control the positioning of multiple segments. This merging approach achieves independent control capability while significantly reducing the number of actuators required.
Solution Approach 2:
The control rod serves multiple functions simultaneously: it acts as a structural support, a control mechanism, and a synchronization element for the radial segments. The angled slots in the rod provide universal control capability for different segment configurations, allowing the same component to handle various control requirements without additional specialized parts.
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
Enhances airflow conditioning and efficiency by allowing the vanes to adapt to non-axisymmetric conditions, improving stability and performance across different engine operations.
Implementation Method 1
The deformable supports are one of polyurethane, isoprene, silicone, and fluoroelastomer
Implementation Method 2
The deformable supports are one of polyurethane, isoprene, silicone, and fluoroelastomer
Implementation Method 3
the control rod translates radially within the airfoil such that the protrusions slide within the angled slots driving the radial segments to pivot into the morphed position
Implementation Method 4
the flexible skin on the pressure side slides relative to the flexible skin on the suction side when the airfoil changes shape
Data Source
Figure 1
Figure 2
Figure 3
AI summary
A gas turbine engine (10) includes a fan section (12), a compressor section (14), and a turbine section (18). The fan section (12) has a plurality of vane assemblies (64) spaced circumferentially about an engine axis (A) and each including an airfoil (66) extending between a leading edge (66a) and a trailing edge (66b), a control rod (68) extending through the airfoil (66), and a mechanism driven by the control rod (68) to change the shape of the airfoil (66).