Iterative Aircraft Engine Inlet Pressure Calculation

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Solution Overview

Problem

Existing methods for determining inlet total air pressure at aircraft engine inlets fail to accurately capture the effects of operational or installation-related factors such as icing, angle of attack, and bypass flow, leading to incomplete pressure measurements.

Innovation Solution

A method and system that utilize a computing device to calculate inlet total air pressure by determining mass air flow, Mach number, and static air pressure, and iteratively refine the pressure ratio to generate an accurate inlet total air pressure, using sensors and computational fluid dynamics to account for various operational conditions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Measurement precision

If ambient atmospheric pressure or aircraft total pressure (pitot) is used to determine inlet total air pressure, then the measurement is simple and direct, but it fails to capture the effects of operational or installation factors such as icing, angle of attack, bypass flow, and inertial particle separators

Engineering Contradiction:

Improveinlet total air pressure measurement accuracyVSAvoidpressure determination system complexity

Core Design Contradiction:

Measurement precisionVSDevice complexity

Solution Approach 1:

The patent introduces an intermediary computational model that acts as a mediator between the simple pitot pressure measurement and the complex physical phenomena occurring at the engine inlet. This model uses the pitot pressure as input and iteratively calculates the actual inlet total pressure by accounting for icing, angle of attack, bypass flow, and other operational factors, thereby resolving the contradiction between measurement simplicity and accuracy.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The patent replaces direct mechanical pressure measurement systems with a computational approach. Instead of using complex mechanical sensors to directly measure inlet total pressure, the system uses a computer-based model that processes simpler pitot pressure measurements along with operational parameters to calculate the inlet total pressure, reducing hardware complexity while improving measurement accuracy.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Measurement precision

If direct measurement of inlet total air pressure is implemented, then accurate pressure data is obtained, but the weight and complexity of engine components increase

Engineering Contradiction:

Improveinlet total air pressure measurement accuracyVSAvoidengine component weight

Core Design Contradiction:

Measurement precisionVSWeight of moving object

Solution Approach 1:

The computational model serves as an intermediary that derives accurate inlet total pressure information from lighter, simpler pitot pressure sensors and operational parameters, eliminating the need for heavy direct measurement equipment while maintaining measurement accuracy.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The patent substitutes heavy mechanical pressure measurement systems with a lightweight computational approach that uses existing sensors and processing power to calculate inlet total pressure, thereby reducing engine component weight while preserving measurement precision.

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

3Device complexity

If existing sensors and iterative calculations are used to determine inlet total air pressure, then the system weight and complexity are reduced, but the ability to accurately capture operational effects must be maintained

Engineering Contradiction:

Improvepressure determination system complexityVSAvoidinlet total air pressure measurement accuracy

Core Design Contradiction:

Device complexityVSMeasurement precision

Solution Approach 1:

The patent implements an iterative feedback mechanism where the computational model continuously refines the inlet total pressure calculation by comparing calculated values with measured operational parameters. The model adjusts its calculations based on feedback from sensors monitoring icing conditions, angle of attack, bypass flow, and other operational factors, ensuring measurement accuracy is maintained despite using a simpler system architecture.

Inventive Principle:

Principle #23Feedback

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 approach provides a reliable and accurate determination of inlet total air pressure without the need for direct measurement, reducing the weight and complexity of engine components and improving reliability by using existing sensors and iterative calculations.

Implementation Method 1

Methodology Applied

Scientific EffectComputational fluid dynamics:

Data Source

PatentUS12071902B2Method and system for determining aircraft engine inlet total pressure

Publication Date: 2024.08.27 PRATT & WHITNEY CANADA CORP

AI summary

A method of determining an inlet total air pressure includes determining a first parameter indicative of a first inlet total air pressure. The method includes executing a sequence that includes: determining a mass air flow passing through the air inlet based on the first parameter, determining a Mach number of air passing through the air inlet based on the mass air flow, determining a static air pressure at the air inlet, determining an air pressure ratio based on the Mach number, generating a subsequent parameter indicative of the revised inlet total air pressure based on the air pressure ratio and the static air pressure, and substituting the subsequent parameter for the first parameter. The method includes executing at least one additional instance of the sequence with the subsequent parameter, and outputting the subsequent parameter as the inlet total air pressure.