Aft Pylon Fairing Thermal Expansion Management

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Solution Overview

Problem

The existing aft pylon fairing systems experience high thermomechanical stresses due to thermal expansion of the heat protection deck, leading to aerodynamic degradation and increased parasite drag, which necessitates the use of expensive materials and oversized components to manage heat resistance.

Innovation Solution

The aft pylon fairing design incorporates longitudinal connecting walls that offset the heat protection deck from the inner cross stiffening ribs, allowing for free thermal expansion and reducing thermomechanical stresses, while eliminating direct mechanical links between the deck and side panels to minimize heat transfer and aerodynamic disturbances.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Strength

If the heat protection deck is rigidly mounted on the inner cross ribs and side panels, then the structural strength and rigidity are improved, but high thermomechanical stresses are generated due to thermal expansion, leading to aerodynamic degradation and increased parasite drag

Engineering Contradiction:
Improvestructural strengthVSAvoidthermomechanical stresses
Core Design Contradiction:
StrengthVSObject-generated harmful factors

Solution Approach 1:

The heat protection deck is segmented into multiple independent sections along its length, with expansion joints between them. This allows each segment to expand and contract independently in response to thermal changes, reducing the accumulation of thermomechanical stresses while maintaining overall structural integrity. The segmentation principle directly addresses the contradiction by enabling the deck to maintain strength through modular construction while accommodating thermal expansion without generating excessive stresses.

Inventive Principle:
Principle #1Segmentation

Solution Approach 2:

The material properties of the heat protection deck are modified to change its thermal expansion characteristics. Specifically, materials with lower thermal expansion coefficients are selected, or the deck is designed with variable thickness and stiffness along its length to control expansion behavior. This parameter change allows the deck to withstand high temperatures while minimizing the thermomechanical stresses that would otherwise degrade aerodynamic quality and increase drag.

Inventive Principle:
Principle #35Parameter changes

2Shape

If the heat protection deck is rigidly connected to the side panels, then the aerodynamic continuity is improved, but the thermal expansion of the deck causes significant deformation of the side panels, degrading aerodynamic quality and increasing parasite drag

Engineering Contradiction:
Improveaerodynamic continuityVSAvoidaerodynamic quality
Core Design Contradiction:
ShapeVSManufacturing precision

Solution Approach 1:

Flexible thermal barriers or expansion joints are introduced between the heat protection deck and the side panels. These flexible elements maintain aerodynamic continuity by filling gaps and smoothing transitions, while simultaneously allowing the deck to expand and contract without transmitting significant deformation forces to the side panels. This resolves the contradiction by preserving the aerodynamic shape while isolating the side panels from thermal expansion-induced deformations.

Inventive Principle:
Principle #30Flexible shells and thin films

Solution Approach 2:

An intermediary layer or structure is introduced between the heat protection deck and the side panels. This intermediary element acts as a buffer that absorbs thermal expansion movements, maintaining aerodynamic continuity while preventing direct transmission of expansion forces to the side panels. The mediator allows both aerodynamic quality and thermal expansion accommodation to coexist.

Inventive Principle:
Principle #24Intermediary (Mediator)

3Reliability

If expensive heat-resistant materials and oversized components are used to manage heat resistance, then the thermomechanical stress resistance is improved, but the weight of the fairing increases, reducing the performance/consumption ratio

Engineering Contradiction:
Improveheat resistanceVSAvoidfairing weight
Core Design Contradiction:
ReliabilityVSWeight of moving object

Solution Approach 1:

The heat protection deck is constructed using composite materials that combine lightweight structures with high-temperature resistance. These composites provide adequate thermal protection and mechanical strength without the excessive weight of traditional monolithic heat-resistant materials. The composite structure allows the fairing to maintain reliability under thermal loads while significantly reducing overall weight, thereby improving the performance/consumption ratio.

Inventive Principle:
Principle #40Composite materials

Solution Approach 2:

Instead of using expensive heat-resistant materials throughout the entire fairing structure, heat protection is applied only where absolutely necessary - specifically to the heat protection deck that directly interfaces with high-temperature exhaust gases. Other portions of the fairing use lighter, conventional materials. This partial application of heat-resistant materials maintains adequate thermal protection while minimizing weight, resolving the contradiction between reliability and weight.

Inventive Principle:
Principle #16Partial or excessive 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

This configuration significantly reduces thermomechanical stresses, improves aerodynamic quality, decreases parasite drag, and enables the use of lighter materials, resulting in mass and cost savings while enhancing the performance/consumption ratio of the aircraft.

Implementation Method 1

the heat protection deck is in contact with the very hot core engine flow, which means that it deforms strongly due to thermal expansion

Methodology Applied
Scientific EffectThermal expansion: Thermal Expansion

Data Source

PatentUS8662440B2AFT pylon fairing for an aircraft engine suspension system
Publication Date: 2014.03.04 AIRBUS OPERATIONS INC AS A
  • US8662440B2 patent drawing
  • US8662440B2 patent drawing
  • US8662440B2 patent drawing

AI summary

This invention relates to an aft pylon fairing (30) for a suspension system of an aircraft engine, comprising two side panels (44) assembled to each other by inner cross stiffening ribs (46) spaced at intervals from each other along a longitudinal direction (X) of the fairing, and also comprising a heat protection deck (32) designed to delimit an engine core flow (36). According to the invention, it also comprises two longitudinal connecting walls (58) offsetting the deck (32) from the ribs (46), each of these two longitudinal walls (58) being provided with a first side end (62) fixed to one or the other of the two side ends (60, 60) of the deck (32), and a second side end (64) rigidly fixed to the ribs (46).