Nacelle Inlet Turbulator Segment for Downstream Heat Dissipation

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Solution Overview

Problem

Existing engine nacelle inlets experience excessively elevated temperatures due to laminar airflow that retains heat, leading to overheating of internal components.

Innovation Solution

The introduction of a turbulator segment on the inner flow surface of the nacelle inlet to transition laminar airflow to turbulent airflow, disrupting the boundary layer and enhancing heat transfer through mixing with adjacent cooler airflow.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If laminar airflow is maintained over the nacelle inlet inner flow surface, then heat transfer efficiency is improved, but excessive heat is retained and carried downstream causing overheating of components

Engineering Contradiction:

Improveheat transfer efficiencyVSAvoidexcessive temperature of downstream components

Core Design Contradiction:

TemperatureVSObject-affected harmful factors

Solution Approach 1:

The patent applies local quality by transitioning the airflow regime locally at a specific position along the inner flow surface using a turbulator element. The airflow remains laminar over the heated section to maximize heat transfer, then transitions to turbulent downstream to dissipate heat. This local modification of flow characteristics resolves the contradiction between maintaining efficient heat transfer and preventing downstream overheating.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The patent changes the flow regime parameter from laminar to turbulent at a controlled location using the turbulator element. This parameter change allows the system to optimize heat transfer in the laminar region while using the turbulent mixing downstream to carry heat away from the heated sections, thus resolving the temperature contradiction.

Inventive Principle:

Principle #35Parameter changes

2Object-affected harmful factors

If a turbulator segment is added to transition airflow from laminar to turbulent, then downstream heat dissipation is improved, but device complexity increases

Engineering Contradiction:

Improvedownstream heat dissipationVSAvoidnacelle inlet structure complexity

Core Design Contradiction:

Object-affected harmful factorsVSDevice complexity

Solution Approach 1:

The turbulator element acts as an intermediary device that facilitates the transition from laminar to turbulent flow. This simple geometric feature, when positioned at the optimal location, enables the desired flow regime change without requiring complex active control systems or multiple components, thus resolving the contradiction between improved heat dissipation and structural simplicity.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Object-affected harmful factors

If the turbulator segment is positioned upstream, then heat dissipation occurs earlier, but the heated sections cannot effectively transfer heat to the air

Engineering Contradiction:

Improveheat dissipation timingVSAvoidheat transfer to air

Core Design Contradiction:

Object-affected harmful factorsVSUse of energy by moving object

Solution Approach 1:

The turbulator element is positioned upstream of the heated sections to preliminarily transition the flow regime before the air passes over the heated surfaces. This preliminary action ensures that when the air flows over the heated sections, it can effectively absorb heat, and then the transitioned flow continues downstream to dissipate the accumulated heat, resolving the timing contradiction.

Inventive Principle:

Principle #10Preliminary action

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

The turbulator segment effectively reduces the temperature of overheated components by promoting turbulent airflow, thereby improving heat dissipation and maintaining components within safe operating limits.

Implementation Method 1

The turbulator segment is configured to transition laminar airflow along the inner flow surface upstream from the turbulator segment to turbulent airflow downstream from the turbulator segment

Methodology Applied

Scientific EffectLaminar to turbulent flow transition: Turbulence

Implementation Method 2

the boundary layer is relatively slow moving and retains the heat drawn from the heated lipskin and carries this heat downstream. Turbulent airflow disrupts this boundary layer heat transfer effect

Methodology Applied

Scientific EffectBoundary layer disruption: Boundary Layer

Implementation Method 3

Turbulent airflow disrupts this boundary layer heat transfer effect by promoting mixing with the adjacent cooler airflow, thus reducing the heat transfer into adjacent structure downstream

Methodology Applied

Scientific EffectHeat transfer through mixing: Convection

Data Source

PatentUS12397922B1Engine nacelle inlet having a turbulator segment

Publication Date: 2025.08.26 THE BOEING CO

AI summary

A nacelle inlet for an engine. The nacelle inlet includes an inner flow surface, an outer flow surface, and a turbulator segment positioned along the inner flow surface. The turbulator segment extends outward beyond the inner flow surface and is configured to transition laminar airflow along the inner flow surface upstream from the turbulator segment to turbulent airflow downstream from the turbulator segment.