Gas Turbine Thrust Trim for Turbine Life Extension
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Solution Overview
Problem
Modern gas turbine engines often produce excessive thrust during takeoff and climb due to uncertainties in factors like aircraft weight, ambient temperature, and runway length, leading to premature turbine wear from operating at higher temperatures and speeds than necessary.
Innovation Solution
A method for controlling thrust in gas turbine engines by determining the required fan speed based on aircraft parameters such as gross weight, runway length, and ambient temperature, and reducing excess thrust generation through a flight control system that adjusts fan speed to match minimum operational requirements.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If fan speed is increased to guarantee thrust during takeoff and climb, then thrust reliability is improved, but turbine life is reduced due to higher temperatures and speeds
Solution Approach 1:
The patent adjusts fan speed parameters dynamically based on actual flight conditions and uncertainty assessments. By changing the operating parameters (fan speed, thrust level) according to real-time conditions rather than using fixed conservative settings, the system achieves both reliable thrust delivery and reduced turbine wear, resolving the contradiction between reliability and duration of action.
2Reliability
If thrust is increased to account for uncertainties in weight, temperature, and runway conditions, then safety is improved, but engine wear increases due to excessive thrust
Solution Approach 1:
The system incorporates feedback mechanisms that continuously monitor actual flight conditions (weight, temperature, runway length, aircraft acceleration) and adjust thrust levels accordingly. This feedback loop allows the engine to produce sufficient thrust for safety while avoiding excessive thrust that would cause premature wear, by constantly comparing actual performance against required performance and making real-time adjustments.
Solution Approach 2:
The patent applies partial action by producing only the necessary amount of thrust required for each specific flight condition rather than consistently operating at maximum or excessive thrust levels. By assessing uncertainties and applying just enough additional thrust margin to ensure safety without over-compensating, the system reduces harmful engine wear while maintaining adequate safety margins.
3Duration of action of stationary object
If conservative thrust settings are used to extend turbine life, then turbine durability is improved, but thrust margin is reduced during critical flight segments
Solution Approach 1:
The system transitions from static, conservative thrust settings to dynamic thrust management that adapts to real-time flight conditions. By making the thrust setting dynamic and responsive to actual aircraft performance, environmental conditions, and uncertainty assessments, the system maintains adequate thrust margins during critical phases while avoiding unnecessarily high thrust settings that would reduce turbine durability.
Data Source
AI summary
A method of controlling thrust for a gas turbine engine of an aircraft is provided. The method includes determining a fan speed required for minimum thrust to achieve an aircraft operation. The method also includes determining an excess amount of thrust generated by the gas turbine engine. The method also includes reducing the amount of thrust generated by the gas turbine engine.