Aircraft Climb Thrust Control for Lower Engine Temperature
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Solution Overview
Problem
Aircraft engines face increased maintenance costs and reduced lifespan due to high thrust levels during takeoff and climb phases, leading to elevated core temperatures and premature wear.
Innovation Solution
Implementing a method to vary climb thrust during the climb flight phase, using a flight management computer to determine a desired airspeed and climb trajectory, and adjust engine thrust accordingly, allowing for derated thrust levels and tapering back to maximum thrust at higher altitudes, thereby reducing engine stress and extending engine life.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If maximum thrust is used during takeoff and climb phases, then aircraft performance targets are met, but engine core temperatures increase and engine life decreases
Solution Approach 1:
The patent applies dynamics by transitioning from static maximum thrust to dynamic thrust adjustment. The system continuously varies climb thrust based on real-time conditions, allowing the aircraft to meet performance targets while optimizing engine temperatures. This dynamic approach enables thrust to be reduced when performance margins exist and increased when needed, resolving the contradiction between climb rate and temperature.
Solution Approach 2:
The patent changes the thrust parameter from a fixed maximum value to a variable value that adjusts based on aircraft weight, altitude, and performance requirements. By modifying this key parameter dynamically, the system achieves both adequate climb performance and reduced engine temperatures, directly addressing the technical contradiction.
2Loss of time
If maximum thrust is used during climb phase, then climb time is reduced, but engine damage increases and maintenance costs increase
Solution Approach 1:
The patent applies partial action by using less than maximum thrust during portions of the climb phase when performance targets can still be met. This partial thrust application reduces engine stress and damage while maintaining adequate climb performance, directly resolving the contradiction between climb time and engine reliability.
Solution Approach 2:
The dynamic thrust adjustment system allows the aircraft to optimize the balance between climb time and engine life. By continuously adapting thrust levels to actual conditions, the system minimizes unnecessary high-thrust operation that causes engine damage while ensuring performance targets are achieved, thereby improving both climb efficiency and engine reliability.
3Duration of action of stationary object
If reduced thrust is used during climb phase, then engine life is extended, but climb distance increases
Solution Approach 1:
The dynamic thrust management system resolves this contradiction by adjusting thrust levels based on real-time performance assessment. When the aircraft is ahead of the climb trajectory or has performance margins, thrust is reduced to extend engine life. When approaching performance limits or trajectory constraints, thrust is increased to maintain climb distance targets. This dynamic balancing act simultaneously optimizes engine life and climb distance.
Solution Approach 2:
The system employs feedback mechanisms to monitor climb progress, aircraft weight, and environmental conditions. This feedback enables continuous adjustment of thrust levels to achieve the optimal balance between engine life extension and climb distance requirements, ensuring that reduced thrust does not compromise performance targets.
Data Source
AI summary
An example method includes: receiving information indicative of a desired aircraft cruise insertion point comprising achieving a desired cruise altitude for an aircraft within a predetermined period of time from departure, or within a predetermined distance from departure; determining a desired airspeed for the aircraft; prior to a flight of the aircraft, determining, based on the desired airspeed and the desired aircraft cruise insertion point, a climb trajectory for the aircraft; and during a climb flight phase of the aircraft, varying climb thrust of an engine of the aircraft to follow the climb trajectory and achieve the desired aircraft cruise insertion point.