Gas Turbine Probe for Sand Blockage Detection in Cooling Flow
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Solution Overview
Problem
Gas turbine engines face challenges in detecting blockages caused by ingested particulates, particularly sand, which can lead to thermal insulation and reduced coolant flow, potentially causing localized hot spots and component failure, due to the complexity of airflow physics and the hostile environment within the turbine section.
Innovation Solution
A probe system with sensors located in the coolant and main flow paths, capable of detecting blockages by measuring static pressure and temperature, and providing removable and interchangeable instrumentation configurations to minimize disruption and extend service life, while allowing for laboratory testing and visual inspection.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If pressure and temperature readings are obtained from the turbine section itself, then an indication of turbine section blockage condition can be obtained, but the hostile environment with gas temperatures exceeding common material limits and the disruption to aerothermal performance reduce component life
Solution Approach 1:
A probe is introduced as an intermediary device that can be inserted into the turbine section through a borescope port. The probe contains sensors that measure pressure and temperature readings indirectly from the turbine environment without requiring permanent instrumentation of the turbine components themselves. This mediator approach allows blockage detection while protecting the actual turbine components from the harsh measurement environment.
Solution Approach 2:
The measurement function is extracted from the turbine components themselves and placed into a separate, removable probe. By taking out the instrumentation from the turbine blades and passages and placing it in an external probe that can be inserted through a borescope port, the system enables measurements without modifying or permanently instrumenting the turbine components, thus preserving their life and performance.
2Measurement precision
If instrumentation is added to turbine components, then blockage detection capability is improved, but the instrumentation disrupts aerothermal performance and introduces local vulnerability that reduces component life
Solution Approach 1:
The instrumentation is extracted from the turbine components and placed in a separate probe. This extraction eliminates the need to drill holes, attach sensors, or modify turbine blades, thereby preserving the aerothermal performance and eliminating local vulnerabilities that would otherwise be introduced by permanent instrumentation.
Solution Approach 2:
The probe serves as an intermediary measurement device that does not become part of the turbine's aerothermal path. By positioning the probe in the borescope port and using it to take measurements of the flowing gas without being in the direct flow path, the system maintains uninterrupted aerothermal performance while still enabling blockage detection.
3Loss of information
If a dedicated off-line engine with probes and specialized sensors is used, then engine models can be developed to predict operational conditions, but the physics of airflow with entrained particles is so complex that predictions are only approximate and may not match real-world conditions
Solution Approach 1:
The system enables measurements to be taken during actual working operations on-wing, which is a preliminary action that captures real-world data before failures occur. By measuring pressure and temperature ratios during actual flight operations with real airflow and particle conditions, the system obtains accurate baseline data that reflects true operating conditions, improving the accuracy of blockage detection algorithms.
Solution Approach 2:
The system provides real-time feedback through the calculation of pressure and temperature ratios that indicate blockage conditions. This feedback mechanism allows operators to monitor engine health continuously and take corrective action based on actual measured conditions rather than relying on approximate model predictions, thereby improving detection precision.
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
Enables early detection of blockages in high-pressure turbines during operation, minimizing flow disruption and extending service life by providing accurate readings and allowing for quick testing of different instrumentation configurations without exposing the engine to risk.
Implementation Method 1
A probe system with sensors located in the coolant and main flow paths, capable of detecting blockages by measuring static pressure and temperature
Implementation Method 2
A probe system with sensors located in the coolant and main flow paths, capable of detecting blockages by measuring static pressure and temperature
Implementation Method 3
cooling air is routed from the compressor section through combustor bypass passages to inside passages of vanes and blades for convective cooling
Implementation Method 4
The cooling air is then directed through holes in the airfoil surfaces for film cooling
Data Source
Figure 1
Figure 2
Figure 3A~3B
AI summary
A gas turbine engine probe (90) comprises a housing (92) mounted in a borescope port (30) of a gas turbine engine (10). The housing (92) includes at least one coolant passage (108, 110) that conducts a coolant through the housing (92). The gas turbine engine probe (90) develops an indication of an engine condition, such as blockage in the gas turbine engine (10) due to sand and/or other debris.