Composite Straightening Vanes Angular Offset Turbine Engine

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Solution Overview

Problem

Dual-flow turbine engines face challenges in reducing vane cross-section mass without increasing debonding risks and vortice formation, leading to suboptimal aerodynamic efficiency and mechanical strength, especially due to torsional forces and structural arms disrupting airflow.

Innovation Solution

The design features composite vanes with an angular offset (0°<α≤30°) between the vane junctions and shell radii, reducing vortice formation, and eliminating structural arms to allow vanes to perform structuring functions, enhancing mechanical strength and aerodynamics while using composite materials for reduced mass.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Weight of moving object

If the vane cross-section is reduced to gain mass, then the mass of the straightening assembly is reduced, but the mechanical strength decreases and the risk of debonding fibre layers increases

Engineering Contradiction:

Improvemass of straightening assemblyVSAvoidmechanical strength of vanes

Core Design Contradiction:

Weight of moving objectVSStrength

Solution Approach 1:

The patent applies composite materials (fibre-reinforced plastic) for the vanes, allowing optimization of the fibre orientation and layer structure to achieve both mass reduction and maintained mechanical strength through proper material composition and structural design

Inventive Principle:

Principle #40Composite materials

2Reliability

If the vanes are fastened to the radially inner shell, then the straightening assembly structure is completed, but vortices form at the fastening location reducing aerodynamic efficiency

Engineering Contradiction:

Improvestructural integrity of assemblyVSAvoidvortex formation and turbulence

Core Design Contradiction:

ReliabilityVSObject-generated harmful factors

Solution Approach 1:

The patent introduces a curvature radius R at the fastening location of the vanes to the radially inner shell. This curved transition zone replaces sharp corners with smooth contours, reducing flow separation and vortex formation while maintaining structural integrity

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The patent modifies the geometric parameters of the vane fastening region by introducing specific curvature radius R values, changing the shape parameters to optimize aerodynamic flow and reduce harmful vortices at the junction between vanes and radially inner shell

Inventive Principle:

Principle #35Parameter changes

3Strength

If structural arms are added to ensure rigidity and transfer loads, then the mechanical strength and load transfer capability are improved, but the mass increases and airflow is disrupted

Engineering Contradiction:

Improverigidity and load transfer capabilityVSAvoidmass of turbine engine

Core Design Contradiction:

StrengthVSWeight of moving object

Solution Approach 1:

The patent makes the radially inner shell perform multiple functions: it serves as the structural support for fastening vanes, provides the reference surface for angular offset measurement, and acts as the load-bearing component. This eliminates the need for separate structural arms by integrating structural functions into the shell itself

Inventive Principle:

Principle #6Universality (Multi-functionality)

Solution Approach 2:

The patent merges the structural support function and the aerodynamic reference surface function into a single component (the radially inner shell), eliminating redundant structural elements and reducing overall mass while maintaining both structural integrity and aerodynamic performance

Inventive Principle:

Principle #5Merging (Combining)

4Object-generated harmful factors

If the angle of inclination is increased to reduce air vortices, then aerodynamic efficiency is improved, but the mechanical strength of the assembly deteriorates

Engineering Contradiction:

Improvevortex reduction and aerodynamic efficiencyVSAvoidmechanical strength under torsional force

Core Design Contradiction:

Object-generated harmful factorsVSStrength

Solution Approach 1:

The patent optimizes the angular offset parameter α within a specific range (0° < α ≤ 30°) to achieve the best compromise between aerodynamic performance (vortex reduction) and mechanical strength, preventing excessive inclination that would weaken the structure under torsional loads

Inventive Principle:

Principle #35Parameter changes

Data Source

PatentUS11814987B2Turbine engine comprising a straightening assembly

Publication Date: 2023.11.14 SAFRAN AIRCRAFT ENGINES SAS

AI summary

The invention relates to a straightening assembly (28) comprising two radially inner and outer coaxial shells (34) between which extend vanes (36) made of composite material, fixed to a first end portion on the radially inner shell and to a second end portion on the radially outer shell, characterized in that:for each vane (36), in a plane perpendicular to the axis of the radially inner and outer shells (34), a straight line passing through a junction between said first and second end portions and the useful part forms an angle α with a radius of the radially inner shell, passing through the junction between said first end portion and the useful part of said vane (36), such that 0°<α≤30°;the radially inner shell has a diameter ranging from 1,000 mm to 1,600 mm; and in thatthe radially outer shell has a diameter ranging from 2,000 to 2,800 mm;the number of vanes (36) ranges from twenty-five to forty-five.