CMC Vane Trailing Edge Radial Cooling Passage

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Solution Overview

Problem

Design and manufacture of high-temperature resistant aerofoils for gas turbine engines using composite materials are challenging due to geometric and strength requirements, particularly in cooling and heat transfer at the trailing edge.

Innovation Solution

A ceramic matrix composite aerofoil with a radially extending trailing-edge passage for cooling, which is separate from the aerofoil-shaped passage, reduces design constraints by allowing radial fluid flow and eliminating axial holes, thereby improving heat transfer and structural integrity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If axial cooling holes are used in the trailing edge, then cooling function is provided, but design constraints and geometric complexity increase

Engineering Contradiction:

Improvetrailing edge coolingVSAvoidpassage geometry complexity

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

The patent inverts the conventional axial cooling approach by implementing radial cooling holes that extend from the radial outer surface to the radial inner surface of the trailing edge. This inversion simplifies the passage geometry from complex axial paths to straightforward radial paths, reducing manufacturing difficulty while maintaining effective cooling of the trailing edge region.

Inventive Principle:

Principle #13The other way round (Inversion)

Solution Approach 2:

The patent transitions from axial cooling (one-dimensional along the blade axis) to radial cooling (one-dimensional along the radial direction). This dimensional change simplifies the cooling passage geometry and allows for more straightforward manufacturing of the ceramic matrix composite structure while effectively cooling the trailing edge.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Temperature

If ceramic matrix composite materials are used, then high-temperature resistance is improved, but manufacturing difficulty increases

Engineering Contradiction:

Improvehigh-temperature resistanceVSAvoidmanufacturing difficulty

Core Design Contradiction:

TemperatureVSEase of manufacture

Solution Approach 1:

The patent segments the cooling system into distinct radial cooling holes that are independently formed within the ceramic matrix composite structure. This segmentation allows for simplified manufacturing of the cooling passages compared to integrated axial paths, reducing overall manufacturing difficulty while maintaining the high-temperature resistance benefits of CMC materials.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The patent utilizes the porous structure inherent in ceramic matrix composites to form radial cooling holes. The manufacturing process leverages the material's ability to form controlled porosity, allowing cooling passages to be created during the CMC fabrication process itself, thereby reducing post-manufacturing complexity.

Inventive Principle:

Principle #31Porous materials

3Use of energy by moving object

If radial cooling passages are implemented, then heat transfer efficiency is improved, but structural integrity may be compromised

Engineering Contradiction:

Improveheat transfer efficiencyVSAvoidstructural integrity

Core Design Contradiction:

Use of energy by moving objectVSStrength

Solution Approach 1:

The patent implements cooling holes specifically at the trailing edge region where heat accumulation is most severe, rather than distributing cooling passages throughout the entire blade structure. This localized approach maximizes heat transfer efficiency at the critical trailing edge while minimizing the impact on overall structural integrity of the ceramic matrix composite aerofoil.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The patent utilizes the thin-walled structure of the ceramic matrix composite trailing edge to accommodate radial cooling holes. The CMC material's inherent flexibility and toughness allow for the incorporation of these cooling passages without significantly compromising the structural integrity of the trailing edge region.

Inventive Principle:

Principle #30Flexible shells and thin films

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 thermal efficiency and reduces design complexities, allowing for more efficient cooling and improved structural support, while maintaining high-temperature resistance.

Implementation Method 1

The trailing-edge passage may extend radially through the ceramic matrix composite aerofoil to conduct cooling fluid radially through the trailing edge of the ceramic matrix composite aerofoil

Methodology Applied

Scientific EffectRadial fluid flow cooling: Convection

Implementation Method 2

The ceramic matrix composite aerofoil is adapted to withstand very high temperatures

Methodology Applied

Scientific EffectThermal insulation: Thermal Insulation

Data Source

PatentUS10883371B1Ceramic matrix composite vane with trailing edge radial cooling

Publication Date: 2021.01.05 ROLLS ROYCE PLC

AI summary

A component adapted for use in a gas turbine engine includes an aerofoil configured to interact with gases flowing through the gas turbine engine along a gas path. The aerofoil is formed to include a first passage that extends radially at least partway into the aerofoil and a second passage that extends radially into the aerofoil at a trailing edge of the aerofoil.