Embedded Optical Probe in Thickened Gas Turbine Vane Airfoil
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Solution Overview
Problem
The presence of penetrating optical probes in gas turbine engines disrupts the gas path flow, leading to reduced engine efficiency due to separated flows, aeroacoustic vibrations, and measurement errors, particularly when evaluating engine performance using infrared imaging sensors.
Innovation Solution
The implementation of a vane assembly with thickened and thinned airfoils, where the probe is embedded within a thickened region of the airfoil, allowing the gas path flow to be turned to an identical trailing edge exit angle as the nominal airfoil, thereby minimizing flow disruption and maintaining efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a penetrating optical probe is inserted through the engine case into the engine gas path, then engine performance evaluation is enabled, but gas path flow is disrupted and engine operating efficiency is reduced
Solution Approach 1:
The probe is embedded within a thickened region of the airfoil structure, nesting the measurement device inside the airfoil rather than having it penetrate through the gas path. This allows the probe to be housed within the airfoil's internal volume, eliminating flow disruption while maintaining measurement capability
Solution Approach 2:
The airfoil is designed with a thickened region at a specific location to accommodate the probe, while the rest of the airfoil maintains its nominal thickness and aerodynamic properties. This localized modification allows probe integration without significantly affecting overall flow characteristics
2Measurement precision
If a penetrating optical probe is inserted through the engine case into the engine gas path, then engine performance evaluation is enabled, but separated flows and aeroacoustic vibrations occur
Solution Approach 1:
The probe is nested within the thickened airfoil region, eliminating its protrusion into the gas path. This prevents the probe from acting as a flow obstacle that would cause separation and vibrations
Solution Approach 2:
The thickened airfoil region, which could potentially be seen as a structural modification or imperfection, is converted into a beneficial feature by providing a housing for the probe. This transforms what might be considered a deviation from the nominal airfoil design into an advantage that enables measurement while maintaining clean flow
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
This configuration reduces pressure loss and aeroacoustic vibrations, enhancing measurement accuracy and engine efficiency by maintaining the flow characteristics similar to the nominal airfoil, thus addressing the flow disruption caused by traditional probes.
Implementation Method 1
the gas path flow to be turned to an identical trailing edge exit angle as the nominal airfoil, thereby minimizing flow disruption
Data Source
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AI summary
A vane assembly (200) may comprise a plurality of airfoils (208) each extending between an inner platform (210) and an outer platform (212), the plurality of airfoils (208) comprising a nominal airfoil (300), a thickened airfoil (400; 416; 428), and a first thinned airfoil (406, 422) circumferentially adjacent to the thickened airfoil (400; 416; 428), wherein, the nominal airfoil (300) has a first chord thickness (W1), the thickened airfoil has a second chord thickness (W2), and the thinned airfoil has a third chord thickness (W3), wherein the second chord thickness (W2) is greater than the first chord thickness (W1) and the third chord thickness (W3) is less than the first chord thickness (W1), and a member disposed within the thickened airfoil (400; 416; 428).