Blade Tip Clearance Sensing for Turbomachinery Rotor Orbit Extraction
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Solution Overview
Problem
Current methods for measuring rotor dynamic orbits in turbomachinery are limited by the need for special test instrumentation and are costly and time-consuming, restricting measurements to a single shaft axial location.
Innovation Solution
A system utilizing blade tip clearance and time of arrival measurements, comprising blade tip sensors, compensation sensors, and an orbit controller, to determine rotor-dynamic orbit information without additional cost or instrumentation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If proximity probes are located deep in the engine to measure rotor dynamic orbits, then measurement accuracy is improved, but device complexity and cost increase
Solution Approach 1:
The patent uses blade tip clearance measurements as an intermediary to indirectly determine rotor dynamic orbits. Instead of placing probes deep in the engine to directly measure shaft movement, the system measures the clearance between blade tips and the engine case, which reflects the rotor's dynamic position. This intermediary measurement approach achieves orbit information without requiring complex deep-engine instrumentation.
Solution Approach 2:
The patent replaces mechanical proximity probes with blade tip clearance measurement systems. By using the existing blade tips as measurement references and measuring their clearance with the engine case, the system substitutes complex mechanical probing systems with a simpler optical or capacitive clearance measurement approach that leverages the engine's existing rotating components.
2Measurement precision
If special test instrumentation is used to measure rotor dynamic orbits, then measurement capability is improved, but ease of manufacture and installation deteriorate
Solution Approach 1:
The patent makes the blade tip clearance measurement system serve multiple functions: it simultaneously provides engine performance monitoring data and rotor dynamic orbit information. The same clearance measurements used for general engine health monitoring are reprocessed to extract orbit data, eliminating the need for separate specialized instrumentation and simplifying both manufacturing and installation.
Solution Approach 2:
The patent uses the engine's own rotating blades as the measurement reference instead of requiring external test instrumentation. The blade tips themselves serve as the measuring elements by providing a consistent reference geometry against which clearance measurements are taken, allowing the engine to monitor its own dynamic behavior without external辅助设备.
3Loss of information
If measurements are taken at multiple shaft axial locations, then comprehensive rotor dynamic information is improved, but loss of time and productivity deteriorate
Solution Approach 1:
The patent transitions from measuring at multiple axial locations (spatial dimension approach) to measuring at a single location but capturing multi-dimensional orbit information (x, y, z coordinates) through the blade tip clearance measurements. By measuring clearance in multiple directions at one axial position, the system obtains comprehensive three-dimensional rotor dynamic information without the time penalty of multiple axial measurements.
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
Generates new information from existing data, providing a unique estimate of the 3D dynamic response of a shaft by synthesizing and aligning orbits from multiple rotor stages, validating engine models for health and safety monitoring.
Implementation Method 1
a blade tip sensor, such as a capacitance sensor
Data Source
AI summary
A system for determining rotor-dynamic orbit information including an engine case supporting at least one engine stage, each at least one engine stage including a rotor having blades; at least one blade tip sensor operatively coupled to the engine case and in operative communication with the blades; at least one compensation sensor in operative communication with the at least one blade tip sensor; and an orbit controller in operative communication with the at least one blade tip sensor and the at least one compensation sensor.