Fan Exit Guide Vane Tension Structure With Bypass Cooling Cavities

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Solution Overview

Problem

Current gas turbine engine designs face challenges in managing structural loads and cooling requirements due to increased operating temperatures and decreased core sizes, particularly in fan exit guide vanes, which are affected by downstream nacelle elements and require improved airflow management.

Innovation Solution

The introduction of a fan exit guide vane with a load member and cooling cavity design that supports structural loads in tension and includes bypass cooling cavities, allowing for heat transfer and thermal management of working fluids and electronics, decoupling aerodynamic and structural load capacities.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If cooling cavities are added to the fan exit guide vane, then heat transfer capability is improved, but structural strength is worsened

Engineering Contradiction:

Improveheat transfer capabilityVSAvoidstructural strength

Core Design Contradiction:

TemperatureVSStrength

Solution Approach 1:

The fan exit guide vane is segmented into functional zones: a load-bearing region with monolithic structure for strength, and a cooling region with cavities for heat transfer. This segmentation allows each zone to be optimized for its specific function without compromising the other.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The vane employs composite construction combining monolithic load-bearing sections with cavity-containing cooling sections. This composite approach enables the structure to simultaneously achieve high strength where needed and effective cooling where thermal management is critical.

Inventive Principle:

Principle #40Composite materials

2Temperature

If material is removed to form cooling cavities, then cooling efficiency is improved, but structural integrity is worsened

Engineering Contradiction:

Improvecooling efficiencyVSAvoidstructural integrity

Core Design Contradiction:

TemperatureVSStrength

Solution Approach 1:

The vane structure is divided into intact load-bearing portions and modified cooling portions. The load-bearing portions maintain full material integrity while the cooling portions contain cavities for thermal management, with transition zones ensuring smooth load transfer.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different regions of the vane have different structural qualities: high-density monolithic material in load-critical areas and cavity-containing material in cooling-critical areas. This local differentiation optimizes both structural integrity and cooling efficiency in their respective zones.

Inventive Principle:

Principle #3Local quality

3Volume of moving object

If core size is decreased, then engine compactness is improved, but cooling challenges are worsened

Engineering Contradiction:

Improvecore sizeVSAvoidcooling challenges

Core Design Contradiction:

Volume of moving objectVSTemperature

Solution Approach 1:

The cooling strategy moves from relying on core size to utilizing dimensional features within the vane structure itself. Spanwise extending cavities create internal cooling pathways that are effective regardless of core dimensions, addressing cooling needs in compact engine configurations.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

Solution Approach 2:

The cooling cavities are designed to work with fluid flow (bypass air or cooling media) to remove heat. This pneumatic/hydraulic cooling approach provides effective thermal management independent of core size, enabling compact engine design.

Inventive Principle:

Principle #29Pneumatics and hydraulics

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 enhances structural support while providing additional space for heat exchangers and thermal management, improving airflow efficiency and reducing material requirements, thus optimizing engine performance and acoustic characteristics.

Implementation Method 1

the cooling cavity being configured to support heat transfer from a working fluid to a fan bypass flow

Methodology Applied

Scientific EffectHeat transfer: Convection

Implementation Method 2

a heat exchanger thermally coupled to the cooling cavity

Methodology Applied

Scientific EffectThermal conduction: Conduction (thermal)

Data Source

PatentUS20260009333A1Fan load tension structural guide vane with bypass cooling cavities

Publication Date: 2026.01.08 RTX CORP

AI summary

A fan exit guide vane with a load member and cooling cavity including an inner attachment region opposite an outer attachment region; a load member cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane from the inner attachment region to the outer attachment region; the load member extending through the load member cavity beyond each of the inner attachment region and the outer attachment region of the fan exit guide vane; and a cooling cavity formed within the fan exit guide vane extending spanwise through the fan exit guide vane between the inner attachment region and the outer attachment region.