Actuatable Airflow Splitter for Variable Core-Bypass Flow Split

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Solution Overview

Problem

Existing turbofan engine arrangements for aircraft propulsion systems face limitations in optimizing the split of incoming air between the core and bypass flowpaths, necessitating improved airflow management for enhanced performance across various operating conditions.

Innovation Solution

An assembly comprising an inner and outer wall structure, a deformable airflow splitter, and an actuation system that adjusts the leading edge of the splitter radially to optimize the airflow distribution between the core and bypass flowpaths, utilizing a rocker arm and cam mechanism for controlled deformation.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If a fixed splitter configuration is used, then the structure is simple and reliable, but the airflow split cannot be optimized for different operating conditions

Engineering Contradiction:

Improveairflow split optimizationVSAvoidsplitter structure

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The patent applies the dynamics principle by making the splitter leading edge movable rather than fixed. The actuation system enables the splitter to dynamically adjust its radial position based on operating conditions, transforming a static structure into a dynamic one that can optimize airflow distribution for different engine operating modes while managing the added complexity through integrated actuation mechanisms

Inventive Principle:

Principle #15Dynamics

2Productivity

If the leading edge is moved radially to optimize airflow split, then airflow management is improved, but the device complexity increases due to actuation system

Engineering Contradiction:

Improveengine performanceVSAvoidactuation system

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The actuation system is designed with multi-functionality to justify its complexity. It not only moves the splitter leading edge for airflow optimization but also integrates rockers and cams that can serve multiple purposes in the engine system, allowing a single actuation mechanism to perform several functions and thereby reducing the overall system complexity burden

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Adaptability or versatility

If a deformable material is used for the splitter, then the leading edge can be moved radially, but the structural strength may be compromised

Engineering Contradiction:

Improveconfiguration adjustabilityVSAvoidsplitter structural strength

Core Design Contradiction:

Adaptability or versatilityVSStrength

Solution Approach 1:

The patent applies parameter changes by selecting materials and designing the splitter structure to exhibit different mechanical properties under different conditions. The deformable material is chosen and configured to provide sufficient flexibility for radial movement while maintaining adequate structural strength through controlled changes in material parameters such as elasticity, thickness distribution, and structural geometry that allow the splitter to deform elastically without compromising strength

Inventive Principle:

Principle #35Parameter changes

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

Enhances airflow management by allowing dynamic adjustment of the airflow split based on operating modes, improving engine performance and efficiency by optimizing the radial location of the leading edge.

Implementation Method 1

The splitter is configured from or otherwise includes a deformable material

Methodology Applied

Scientific EffectElasticity: Elasticity

Implementation Method 2

The splitter is configured from or otherwise includes a deformable material

Methodology Applied

Scientific EffectViscoelasticity: Viscoelasticity

Implementation Method 3

The actuation system is mechanically coupled to the splitter and is configured to move the leading edge radially relative to the first axis

Methodology Applied

Scientific EffectMechanical Force: Mechanical Force

Implementation Method 4

The actuation system includes a rocker arm operatively coupled to the splitter. The actuation system is configured to move the leading edge radially relative to the first axis by pivoting the rocker arm about a rocker axis

Methodology Applied

Scientific EffectLever: Lever

Implementation Method 5

Methodology Applied

Scientific EffectMechanical Advantage: Mechanical Advantage

Data Source

PatentEP4647584A1Actuatable airflow splitter for an aircraft powerplant

Publication Date: 2025.11.12 RTX CORP

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AI summary

An assembly is provided for an aircraft propulsion system. This assembly includes an inner wall structure (84), an outer wall structure (86), a splitter (88) and an actuation system (118). The inner wall structure (84) extends axially along a first axis (24) to an inner wall upstream end (90). The outer wall structure (86) extends axially along the first axis (24) to an outer wall upstream end (94). The splitter (88) extends axially along the first axis (24) to a leading edge (98). An inner section (100) of the splitter (88) is connected to the inner wall structure (84) at the inner wall upstream end (90). An outer section (102) of the splitter (88) is connected to the outer wall structure (86) at the outer wall upstream end (94) and meets the inner section (100) of the splitter (88) at the leading edge (98). The actuation system (118) is mechanically coupled to the splitter (88) and is configured to move the leading edge (98) radially relative to the first axis (24).