Turbine Engine Power Verification via Parallel Control

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Solution Overview

Problem

Current methods for checking the maximum available power of a helicopter's turbine engines, particularly in One Engine Inoperative (OEI) mode, are inadequate as they either risk damaging the engines or provide insufficient power assurance, due to the inability to test engines at high power levels and reliance on uncertain EPC checks.

Innovation Solution

A method involving placing one turbine engine at maximum take-off power and adjusting the other engine's power to maintain necessary flight power, while determining and processing the supplied power to deduce maximum available power, including threshold comparisons for temperature and rotation speed, to ensure safe operation without damaging the engines.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If the turbine engine is tested at OEI engine speed to verify maximum power availability, then the power supply capability is improved, but the turbine engine may be damaged due to excessive power levels

Engineering Contradiction:

Improvepower supply capabilityVSAvoidengine damage risk

Core Design Contradiction:

ReliabilityVSObject-affected harmful factors

Solution Approach 1:

The patent applies partial action by testing the turbine engine at PMD (maximum take-off power) rather than full OEI power levels. This partial testing approach verifies sufficient power availability for critical phases like take-off and landing while avoiding the excessive action that would cause engine damage. The test is designed to be sufficient for safety verification but not excessive enough to harm the engine.

Inventive Principle:

Principle #16Partial or excessive action

Solution Approach 2:

The patent implements preliminary action by conducting the power availability check before actual OEI operation is required. The system performs the PMD power test in advance during normal dual-engine operation, allowing the engine to be verified as capable of providing sufficient power for future OEI scenarios without actually putting the engine through damaging high-stress OEI testing.

Inventive Principle:

Principle #10Preliminary action

2Reliability

If the maximum rotation speed check is performed during technical flight every 500 hours, then the engine power availability is improved, but the operational complexity and accessibility are worsened due to requirement of dedicated test areas

Engineering Contradiction:

Improveengine power availabilityVSAvoidtesting procedure complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent applies universality by making the power availability check applicable to all flight operations, not just dedicated technical flights. The system can perform the PMD power test during any flight phase when both engines are operational, eliminating the need for separate dedicated test areas and procedures. This multi-functional approach integrates the check into regular operational workflows.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent implements self-service by enabling the turbine engine to be tested while remaining in its normal operational position during flight. The system uses the engine's own operational parameters and the aircraft's existing flight conditions to perform the test, eliminating the need for external test facilities, specialized locations, or complex external testing equipment.

Inventive Principle:

Principle #25Self-service

3Object-affected harmful factors

If the EPC check is performed at lower power levels to avoid engine damage, then the engine safety is improved, but the measurement precision of maximum power capability is worsened

Engineering Contradiction:

Improveengine safetyVSAvoidmaximum power capability verification

Core Design Contradiction:

Object-affected harmful factorsVSMeasurement precision

Solution Approach 1:

The patent applies parameter changes by systematically varying the power level parameter during the test. Instead of conducting the test at a single fixed power level, the system adjusts the power parameter to reach PMD (maximum take-off power) to verify the engine's true capability. This dynamic parameter adjustment allows the system to measure maximum power capability while maintaining safety through controlled, progressive power increase rather than static low-power testing.

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS11459960B2Method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines

Publication Date: 2022.10.04 SAFRAN HELICOPTER ENGINES

AI summary

A method for checking the maximum available power of a turbine engine of an aircraft equipped with two turbine engines configured to operate in parallel and together to supply a necessary power to the aircraft during a flight phase includes: placing one of the turbine engines in a maximum take-off power regime, and adjusting a power supplied by the other turbine engine, such that the turbine engines continue to supply the necessary power to the aircraft during the flight phase; determining a power supplied by the turbine engine placed in the maximum take-off power regime, and processing the supplied power determined in this way, in order to deduce a piece of information relating to the maximum available power.