Rotorcraft Engine Inlet Loss Calculation for Power Assessment
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Solution Overview
Problem
Current rotorcraft engine power calculations rely on worst-case installation losses, which do not accurately reflect real-time conditions, leading to inefficient operation and potential safety issues.
Innovation Solution
A method and system that determine current inlet losses in real-time using sensors and processing units to calculate and display the available engine power on a flight display, allowing for dynamic adjustments based on actual flight conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If worst-case installation losses are used for engine power calculations, then safety margin is improved, but operational efficiency deteriorates due to inaccurate power assessment
Solution Approach 1:
The patent applies dynamics by transitioning from static worst-case installation loss values to dynamic, real-time inlet loss calculations. Sensors continuously measure actual inlet temperature and pressure, and the processing unit dynamically adjusts the available engine power indication based on current flight conditions, allowing the system to adapt between safety-oriented and efficiency-oriented operations
Solution Approach 2:
The patent implements feedback by using sensors to continuously monitor actual inlet conditions and feeding this information back to the processing unit. The system compares real-time measurements with expected values and adjusts the available engine power indication accordingly, creating a closed-loop system that improves operational efficiency while maintaining safety through continuous verification
2Measurement precision
If real-time sensor measurements are implemented, then measurement precision of engine power is improved, but device complexity increases
Solution Approach 1:
The patent applies universality by designing a integrated processing unit that performs multiple functions: it processes sensor data from various sources, calculates inlet losses, determines available engine power, and controls display outputs. This multi-functional approach consolidates complexity into a single unit rather than distributing it across multiple separate systems
Solution Approach 2:
The patent uses an intermediary approach by introducing a processing unit that acts as a mediator between the sensors and the flight display. This intermediary processes raw sensor data, applies calculations for inlet losses, and generates the final available engine power indication, simplifying the overall system architecture while improving measurement precision
Data Source
AI summary
Systems and methods for operating a rotorcraft engine are described herein. Measurements indicative of at least one of current temperature and current pressure at an inlet of the engine are obtained from at least one sensor while the rotorcraft is in flight. At least one current inlet loss is determined from the measurements. Current available engine power of the rotorcraft engine is determined based on the at least one current inlet losses. A visual indication of the current available engine power is produced via a flight display.