Gas Turbine Blade Damper Deposition

Solution Overview

Problem

Current gas turbine engine components, particularly in the turbine section, face challenges in surviving high temperatures, and there is a need for improved ceramic matrix composite (CMC) materials that can be effectively adapted and manufactured for such extreme conditions without increasing complexity or cost.

Innovation Solution

A gas turbine engine blade design featuring a damper made from machinable materials like rare earth silicates and ceramic matrix composites, deposited directly onto the blade without fasteners, using methods such as plasma spray or chemical vapor deposition, which can be machined to precise dimensions for optimal mass and geometry, thereby providing damping without additional structural attachments.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If a damper is attached to the blade using fasteners, then the damping function is achieved, but the structural complexity and manufacturing cost increase

Engineering Contradiction:

Improvedamping functionVSAvoidstructural complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The damper is merged with the blade by depositing damping material directly onto the blade surface, eliminating the need for separate damper components and fasteners. This integration reduces structural complexity while maintaining the damping function, as the damping layer becomes an integral part of the blade structure.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The blade structure is given multi-functionality by incorporating damping capability directly into the blade through deposited material. The blade simultaneously serves its primary function of directing gas flow and its secondary function of damping vibrations, eliminating the need for separate damping components.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If a damper is attached to the blade using fasteners, then the damping function is achieved, but the manufacturing cost increases

Engineering Contradiction:

Improvedamping functionVSAvoidmanufacturing cost

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The damper is merged with the blade by depositing damping material directly onto the blade surface, eliminating the need for separate damper components and fasteners. This integration reduces structural complexity while maintaining the damping function, as the damping layer becomes an integral part of the blade structure.

Inventive Principle:

Principle #5Merging (Combining)

Solution Approach 2:

The blade structure is given multi-functionality by incorporating damping capability directly into the blade through deposited material. The blade simultaneously serves its primary function of directing gas flow and its secondary function of damping vibrations, eliminating the need for separate damping components.

Inventive Principle:

Principle #6Universality (Multi-functionality)

3Temperature

If CMC materials are used for turbine components, then high temperature survival is improved, but the adaptability and manufacturing flexibility decrease

Engineering Contradiction:

Improvehigh temperature survivalVSAvoidadaptability of CMCs

Core Design Contradiction:

TemperatureVSAdaptability or versatility

Solution Approach 1:

The blade is segmented into different material zones: the base blade structure made of CMC for high temperature survival, and a deposited damping layer on the surface for vibration control. This segmentation allows each zone to be optimized for its specific function while maintaining overall blade performance.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The blade employs a composite structure combining CMC base material with deposited damping material layers. This composite approach allows the blade to benefit from the high temperature resistance of CMCs while adding the vibration damping capabilities of the deposited material, achieving both high temperature survival and adaptability.

Inventive Principle:

Principle #40Composite materials

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 allows for effective damping of vibratory forces in gas turbine blades at high temperatures, reducing manufacturing complexity and cost by integrating the damper directly onto the blade, ensuring efficient operation and longevity.

Implementation Method 1

deposited by at least one of plasma spray, slurry coating, chemical vapor deposition (CVD), physical vapor deposition, and electron beam physical deposition

Methodology Applied

Scientific EffectPlasma spray: Plasma Spray

Implementation Method 2

deposited by at least one of plasma spray, slurry coating, chemical vapor deposition (CVD), physical vapor deposition, and electron beam physical deposition

Methodology Applied

Scientific EffectChemical vapor deposition: Chemical Vapour Deposition

Implementation Method 3

effective damping of vibratory forces in gas turbine blades

Methodology Applied

Scientific EffectDamping: Damping

Data Source

PatentEP4417788A1Gas turbine engine blade and method of sizing a damper for a gas turbine engine blade

Publication Date: 2024.08.21 RTX CORP

Figure 1
Figure 2A~2C
Figure 3

AI summary

A gas turbine engine blade (100) includes a platform (104), an airfoil section (102) extending from the platform (104) in a first direction, a mount (106) extending from the platform (104) in a second direction opposite the first direction, and a damper (108) deposited on one of the platform (104), the airfoil section (102), and the mount (106). A method of sizing a damper (108) for a gas turbine engine blade (100)is also disclosed.