Turbine Engine Flameout Resistance Test Method
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Solution Overview
Problem
Aeronautical turbomachines face the risk of engine flameout during emergency maneuvers due to sudden changes in fuel flow, which can occur due to faulty regulation or aging engine components, making it difficult to assess the engine's ability to withstand rapid deceleration without a test bench diagnosis, and this risk goes unnoticed until a general overhaul.
Innovation Solution
A method is implemented to simulate a rapid deceleration maneuver on the ground, where the engine computer controls a programmed reduction in fuel flow to test the engine's ability to maintain flame stability, with the fuel flow setpoint being modulated based on temperature and pressure conditions to replicate emergency maneuver conditions, allowing for regular checks and maintenance before flight.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Measurement precision
If a test bench diagnosis is used to check engine flameout resistance, then measurement precision is improved, but loss of time increases and productivity decreases
Solution Approach 1:
The patent replaces the mechanical test bench diagnosis system with an on-board electronic testing system. The engine computer executes a non-flame-out test by automatically controlling fuel flow reduction and monitoring combustion stability during simulated rapid deceleration, eliminating the need for external test bench equipment while maintaining diagnostic accuracy.
Solution Approach 2:
The engine performs self-diagnosis of its flameout resistance capability through an automated test routine executed by its own control system. The engine computer independently manages the test procedure, including fuel flow modulation and combustion monitoring, allowing the system to assess its own reliability without external intervention.
2Reliability
If regular on-ground checks are implemented, then reliability is improved, but device complexity increases
Solution Approach 1:
The engine computer is designed to perform multiple functions: normal operation control, fuel flow management during flight, and execution of the non-flame-out test procedure. This multi-functionality allows the same hardware to serve both operational and diagnostic purposes, avoiding the need for separate dedicated testing equipment.
Solution Approach 2:
The test procedure utilizes changes in existing operational parameters (fuel flow rate, engine speed, combustion chamber pressure) to assess flameout resistance. By manipulating parameters the system already controls during normal operation, the patent avoids introducing additional sensors or actuators that would increase complexity.
3Speed
If fuel flow is reduced rapidly during emergency maneuver, then speed response is improved, but stability of combustion deteriorates
Solution Approach 1:
The system performs preliminary assessment of flameout resistance by simulating the fuel flow reduction scenario before actual emergency maneuvers are needed. The non-flame-out test pre-identifies vulnerable conditions by gradually reducing fuel flow and monitoring combustion stability, allowing preventive maintenance or adjustment before critical failures occur during real emergencies.
Solution Approach 2:
The engine computer continuously monitors combustion chamber parameters during the test and uses this feedback to determine whether flameout occurs at the simulated fuel flow reduction rate. This feedback mechanism allows the system to assess its margin of safety and adjust operations or trigger maintenance alerts based on the test results.
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 method ensures the engine's reliability for emergency maneuvers by identifying potential flameout risks during routine checks, allowing for timely maintenance and preventing unexpected engine failures during critical flight situations.
Implementation Method 1
a combustion chamber where fuel mixed with air is burned
Data Source
Figure 1
AI summary
The invention relates to a method for the ground control of the proper operation of an aeronautical turbine engine for a plane. Accordingly, the test comprises carrying out, on the operating turbine engine and from a predetermined speed, a quick reduction in the fuel flow according to a programmed decrease in order to evaluate the flame-out resistance of the combustion chamber of said turbine engine during a quick inflight deceleration manoeuver of the speed thereof.