Vane With Integral Wall Passage For Thermal Growth

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Solution Overview

Problem

Legacy aerospace component designs require large racetrack orifices and high-cost seals to account for thermal growth differentials between fuel tubes and vane walls, which are inefficient and costly.

Innovation Solution

The design incorporates an integral longitudinal wall passage and apertures within the vane wall, manufactured using additive processes, eliminating the need for separate fuel tubes and seals by integrating fuel conduits directly into the component.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stability of the object's composition

If separate fuel tubes and seals are used to account for thermal growth differentials, then thermal expansion is accommodated, but device complexity and cost increase

Engineering Contradiction:

Improvethermal growth differential accommodationVSAvoidassembly complexity

Core Design Contradiction:

Stability of the object's compositionVSDevice complexity

Solution Approach 1:

The patent integrates the fuel conduit directly into the vane structure through additive manufacturing, merging what were previously separate components (fuel tube and vane) into a single monolithic structure. This eliminates the need for seals and complex assembly while accommodating thermal growth differentials through the integral design.

Inventive Principle:

Principle #5Merging (Combining)

2Stability of the object's composition

If large racetrack orifices are used for fuel injection, then thermal growth differentials are accommodated, but material usage and cooling efficiency worsen

Engineering Contradiction:

Improvethermal growth differential accommodationVSAvoidmaterial usage

Core Design Contradiction:

Stability of the object's compositionVSLoss of substance

Solution Approach 1:

The additive manufacturing process enables precise control of the fuel conduit geometry, allowing for optimized aperture sizes and shapes at specific locations rather than requiring large racetrack orifices throughout. This local optimization reduces material usage while maintaining thermal growth accommodation.

Inventive Principle:

Principle #3Local quality

3Stability of the object's composition

If large racetrack orifices and seals are used, then thermal growth differentials are accommodated, but manufacturing cost increases

Engineering Contradiction:

Improvethermal growth differential accommodationVSAvoidmanufacturing cost

Core Design Contradiction:

Stability of the object's compositionVSEase of manufacture

Solution Approach 1:

By merging the fuel conduit and vane into a single additively manufactured component, the patent eliminates the need for separate seals and complex assembly procedures. This integration significantly reduces manufacturing cost while maintaining the ability to accommodate thermal growth differentials through the optimized conduit design.

Inventive Principle:

Principle #5Merging (Combining)

4Ease of operation

If separate fuel tubes are inserted into aerospace components, then fuel injection is enabled, but assembly complexity increases

Engineering Contradiction:

Improvefuel injection capabilityVSAvoidassembly complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The patent eliminates the need for inserted fuel tubes by integrating the fuel conduit directly into the vane structure. This merging of components simplifies assembly while maintaining full fuel injection capability through the additively manufactured passages.

Inventive Principle:

Principle #5Merging (Combining)

Data Source

PatentEP3279435B1Vane with integral wall passage

Publication Date: 2024.10.02 RTX CORP

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AI summary

An aerospace component (102) includes a wall (122) with an integral longitudinal wall passage (120) formed therein, the integral longitudinal wall passage (120) including at least one entrance aperture (126) and at least one exit aperture (132), the exit aperture (132) transverse to the integral longitudinal wall passage (120). The aerospace component (102) may be additively manufactured.