Aircraft Engine Probe Leakage Flow Control
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Solution Overview
Problem
Aircraft engine sensors face challenges in accurately measuring internal parameters due to leakage flows of gas or air, which distort measurement values and complicate Engine Health Management by creating pressure imbalances between measuring spaces and cavities.
Innovation Solution
A measuring device with an air-conducting device that establishes a fluidic coupling between cavities and a pressure sink, allowing leakage flows to be redirected away from measuring spaces, maintaining an equal pressure gradient and preventing distortion of measurement values.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If sensors are installed in measuring spaces within aircraft engine cavities, then measurement capability is enabled, but leakage flows distort measurement values
Solution Approach 1:
The harmful leakage flow is extracted and redirected away from the measuring space through a separate air-conducting device. The device creates a dedicated flow path that removes gas or air from the cavity before it can enter and distort the measurement environment, effectively separating the harmful flow from the sensitive measurement zone.
Solution Approach 2:
An air-conducting device acts as an intermediary between the cavity and the measuring space. This intermediate structure controls and directs the leakage flow through a defined path, preventing direct contamination of the measurement environment while maintaining the necessary pressure gradients for proper sensor operation.
2Ease of manufacture
If cavities are designed for engine structure, then structural requirements are met, but leakage flows enter measuring spaces
Solution Approach 1:
The cavity system is segmented into distinct functional zones: the structural cavity for engine support, the measuring space for accurate sensor operation, and a controlled air-conducting pathway for managing leakage flows. This segmentation allows each zone to fulfill its specific function without interfering with the others, maintaining both structural integrity and measurement precision.
Solution Approach 2:
The air-conducting device serves as an intermediary structure that bridges the structural cavity and the measuring space while controlling the interaction between them. It manages the leakage flow in a way that preserves the structural design requirements while preventing measurement distortion.
3Stress or pressure
If leakage flows are allowed to balance pressure, then pressure equilibrium is achieved, but measurement values become distorted
Solution Approach 1:
The excessive or harmful leakage flow is extracted and redirected through the air-conducting device to a discharge location away from the measuring space. This selective removal of flow maintains necessary pressure balances in the engine structure while preventing distortion of the measurement environment's pressure conditions.
Solution Approach 2:
The system establishes a controlled feedback loop where the air-conducting device continuously monitors and adjusts the leakage flow to maintain optimal pressure conditions. By creating a regulated pressure gradient and controlling the flow path, the system ensures stable pressure in the measuring space while still allowing pressure balancing in the broader engine structure.
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
The solution effectively minimizes leakage flows, ensuring accurate sensor readings and improved Engine Health Management by maintaining a stable pressure environment within the aircraft engine, enhancing the reliability of temperature, pressure, and chemical composition monitoring.
Implementation Method 1
A pressure sink here is a region in or else outside the aircraft engine, in which a lower pressure prevails at the respective point in time than in the cavity. This pressure difference permits air to be sucked out of the cavity.
Implementation Method 2
The suction here should as far as possible be undertaken in such a manner that there is an at least sufficient equal pressure gradient between the measuring space and the cavity such that the leakage flow does not flow to the measuring space, but rather to the pressure sink.
Data Source
AI summary
The invention relates to a measuring device for an aircraft engine, characterized by at least one probe device for measuring a physical and/or chemical state in at least one measuring space within the aircraft engine, wherein the at least one measuring space is fluidically connected to a cavity, and at least one air-conducting device, which is fluidically coupled to the cavity in such a manner that a fluid flow, in particular a gas flow, can be removed from the at least one cavity to a pressure sink. The invention also relates to an aircraft engine and to a measuring method.