Morphing Compressor Vanes with Piezoelectric Actuators

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Solution Overview

Problem

Existing gas turbine engines with static compressor vanes lack independent control over the leading and trailing edge angles, which limits their ability to adapt to changing operational conditions, affecting efficiency and fuel consumption.

Innovation Solution

The use of piezoelectric actuators mounted on both the suction and pressure sides of the airfoil, allowing independent control of the leading and trailing edge positions through contraction and expansion, enabling precise adjustment of the airfoil shape to optimize performance across varying operational conditions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If variable vanes are used to change the incident angle during operation, then adaptability to changing operational conditions is improved, but device complexity increases due to actuators and control systems

Engineering Contradiction:

Improveadaptability to changing operational conditionsVSAvoiddevice complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The airfoil is divided into multiple independent morphing zones (leading edge, trailing edge, camber region) that can be controlled separately by distributed piezoelectric actuator pairs, allowing selective shape adjustment without requiring complete actuation of the entire vane

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Traditional mechanical linkages and single-axis actuators are replaced with piezoelectric materials that directly convert electrical signals to precise mechanical deformation, eliminating complex mechanical transmission systems and reducing overall device complexity

Inventive Principle:

Principle #28Mechanics substitution (Replace mechanical system)

2Device complexity

If a monolithic vane design is used where leading and trailing edges move together, then device complexity is reduced, but adaptability to different operational conditions deteriorates

Engineering Contradiction:

Improvedevice complexityVSAvoidadaptability to different operational conditions

Core Design Contradiction:

Device complexityVSAdaptability or versatility

Solution Approach 1:

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different regions of the airfoil are given different morphing capabilities and control characteristics, with the leading edge, trailing edge, and camber region each capable of independent shape adjustment to optimize local flow characteristics for specific operating conditions

Inventive Principle:

Principle #3Local quality

3Adaptability or versatility

If piezoelectric actuators are mounted on both suction and pressure sides for independent control, then adaptability and control precision are improved, but device complexity and manufacturing difficulty increase

Engineering Contradiction:

Improveindependent control capabilityVSAvoidease of manufacture

Core Design Contradiction:

Adaptability or versatilityVSEase of manufacture

Solution Approach 1:

The piezoelectric actuator pairs are integrated within recesses or pockets in the airfoil structure, with the actuators nested within the airfoil body rather than mounted on the external surface, simplifying integration and reducing manufacturing complexity

Inventive Principle:

Principle #7Nested doll (Nesting)

Solution Approach 2:

The airfoil structure is designed with localized reinforcement and mounting features at specific actuator positions, allowing complex control functionality to be achieved through strategic structural modifications rather than uniform complexity throughout the component

Inventive Principle:

Principle #3Local quality

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 solution enables independent control of the leading and trailing edge angles, enhancing compressor efficiency and fuel consumption by allowing the airfoil to maintain optimal design point efficiency even during off-design operating conditions, thereby improving overall engine performance.

Implementation Method 1

There is at least one piezoelectric actuator for changing a shape of at least one of the leading edge and the trailing edge

Methodology Applied

Scientific EffectPiezoelectric effect: Piezoelectric Effect

Data Source

PatentEP3760834B1Gas turbine engine with morphing variable compressor vanes

Publication Date: 2022.08.31 RTX CORP

Figure 1
Figure 2A~2B
Figure 3A~3B

AI summary

A stator vane for a gas turbine engine section includes a stator vane (120) having an airfoil (122, 140) extending between a leading edge (124, 146) and a trailing edge (138, 152). The airfoil (132, 140) has a suction side (126, 144) and a pressure side (128, 142). There is at least one piezoelectric actuator (130, 134, 148, 150) for changing a shape of at least one of the leading edge (124, 146) and the trailing edge (138, 152). A gas turbine engine (20) is also disclosed.