Stator Diffusion Channels for Compact Turbine Engine Heat Exchange

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Solution Overview

Problem

Existing turbomachine designs face a challenge in balancing the need to efficiently dissipate heat from hydraulic circuits while maintaining a compact axial dimension, as traditional methods for airflow deceleration before heat exchangers require a significant axial length, incompatible with compact architectures.

Innovation Solution

The turbomachine incorporates a plurality of diffusion channels upstream of the heat exchanger, each channel circumferentially delimited by stator blades, allowing stable airflow deceleration over a shorter axial distance, with fins radially delimiting the channels to minimize aerodynamic pressure loss and axial footprint.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Length of moving object

If a single diffusion channel is used to decelerate airflow before the heat exchanger, then the axial length required for stable flow diffusion is reduced, but the duct height must be increased which increases the radial footprint

Engineering Contradiction:

Improveaxial lengthVSAvoidradial footprint

Core Design Contradiction:

Length of moving objectVSArea of moving object

Solution Approach 1:

The single diffusion channel is segmented into multiple parallel diffusion channels formed between adjacent stator blades. This segmentation allows the airflow to be divided into multiple streams, each undergoing diffusion over a shorter axial distance while maintaining stable flow conditions. The multiple channels collectively achieve the required deceleration without requiring excessive axial length or radial height.

Inventive Principle:

Principle #1Segmentation

2Length of moving object

If the number of diffusion channels is increased, then the axial length for stable diffusion is reduced, but the complexity of the blade structure increases

Engineering Contradiction:

Improveaxial lengthVSAvoidblade structure complexity

Core Design Contradiction:

Length of moving objectVSDevice complexity

Solution Approach 1:

The stator blades serve multiple functions: they guide the airflow, provide structural support, and create the diffusion channels through their circumferential arrangement. By making the blades multi-functional, the design achieves complex flow control without proportionally increasing structural complexity. The same blade elements that define the aerodynamic path also establish the diffusion channels.

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The diffusion channel structure is merged with the stator blade assembly rather than being a separate component. The channels are formed by the spatial arrangement of adjacent blades, combining the flow guidance function and the channel structure into a unified design. This integration reduces overall complexity compared to having separate diffusion channels and blade structures.

Inventive Principle:

Principle #5Merging (Combining)

3Loss of energy

If fins are added to radially delimit the diffusion channels, then aerodynamic pressure loss is minimized, but the manufacturing complexity increases

Engineering Contradiction:

Improveaerodynamic pressure lossVSAvoidmanufacturing complexity

Core Design Contradiction:

Loss of energyVSEase of manufacture

Solution Approach 1:

The fins are merged with the stator blade structure, forming an integrated component rather than separate attachments. The fin structures are incorporated into the blade geometry during manufacturing, allowing the aerodynamic flow control features to be produced alongside the main blade structure in a single manufacturing process, thereby minimizing additional manufacturing complexity.

Inventive Principle:

Principle #5Merging (Combining)

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 design achieves efficient airflow deceleration and heat dissipation with a reduced axial footprint, maintaining airflow stability and minimizing pressure losses, while allowing for a compact turbomachine architecture.

Implementation Method 1

a plurality of diffusion channels upstream of the at least one exchanger, each channel being circumferentially delimited by an intrados and by an extrados of two circumferentially adjacent blades

Methodology Applied

Scientific EffectDiffusion: Diffusion

Implementation Method 2

slow down the airflow stably over a shorter axial distance

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Implementation Method 3

at least one heat exchanger disposed in the passage downstream of the row of blades

Methodology Applied

Scientific EffectHeat exchange: Heat Exchanger

Implementation Method 4

exchanges heat with the hot oil

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Implementation Method 5

dissipate the heat stored in the oil

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 6

each channel being radially delimited by at least one fin carried by at least one of the two circumferentially adjacent blades

Methodology Applied

Scientific EffectAerodynamic flow guidance: Aerofoil

Data Source

PatentEP4374047B1Turbine engine for an aircraft with heat exchanger

Publication Date: 2026.02.18 SAFRAN AERO BOOSTERS SA

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Figure 5~6

AI summary

The invention relates to a turbine engine comprising a stator blade (22) having a vane (28) extending circumferentially from the pressure face (22.3) and/or from the suction face (22.4). The blade (22) is intended to be positioned downstream of a rotor and in a diffusion channel in order to slow an air flow upstream of a heat exchanger.