Gas Turbine Rotor Disk Heat Barrier Design

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Solution Overview

Problem

Gas turbine engine rotor disks experience thermal gradients due to coolant contact, which can reduce their lifespan and efficiency.

Innovation Solution

A heat barrier, such as a heat shield or heat-resistant coating, is introduced between the rotor blade and rotor disk to minimize the cooling effect of the coolant, reducing thermal gradients and extending the rotor assembly's lifespan.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If coolant is delivered to the rotor blade through a radially inward facing opening in the root of each rotor blade, then the rotor blade is cooled effectively, but the coolant causes a cooling effect on the outer periphery of the rotor disk which creates or exacerbates thermal gradients

Engineering Contradiction:

Improverotor blade temperatureVSAvoidrotor disk thermal gradient

Core Design Contradiction:

TemperatureVSReliability

Solution Approach 1:

A heat barrier component is introduced as an intermediary element positioned between the rotor blade root and the rotor disk outer periphery. This heat barrier intercepts the coolant flow before it can directly contact the rotor disk, allowing the coolant to cool the rotor blade while preventing the harmful cooling effect on the rotor disk that would create thermal gradients.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The cooling function is segmented into two separate zones: one for the rotor blade and one for the rotor disk. The heat barrier creates a physical separation that directs coolant flow specifically to the rotor blade cooling passages while blocking access to the rotor disk outer periphery, thereby independentizing the thermal management of these two components.

Inventive Principle:

Principle #1Segmentation

2Use of energy by moving object

If coolant flows freely to cool the rotor blade, then cooling efficiency is improved, but the lifespan of the rotor assembly is reduced due to thermal gradients in the rotor disk

Engineering Contradiction:

Improvecooling efficiencyVSAvoidrotor disk lifespan

Core Design Contradiction:

Use of energy by moving objectVSDuration of action of stationary object

Solution Approach 1:

The heat barrier serves as a mediator that preserves coolant flow to the rotor blade for effective cooling while simultaneously protecting the rotor disk from the harmful cooling effect. This allows high cooling efficiency to be maintained without the penalty of reduced rotor disk lifespan from thermal gradients.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The heat barrier converts the potentially harmful coolant flow that would otherwise create thermal gradients and reduce rotor disk lifespan into a beneficial cooling effect solely on the rotor blade. By redirecting and containing the coolant flow, the same coolant that could be harmful becomes exclusively beneficial.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

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

The heat barrier effectively reduces thermal gradients on the rotor disk, enhancing the rotor assembly's durability and operational efficiency by preventing coolant from directly cooling the disk, thus prolonging its lifespan.

Implementation Method 1

A heat barrier, such as a heat shield or heat-resistant coating, is introduced between the rotor blade and rotor disk to minimize the cooling effect of the coolant, reducing thermal gradients

Methodology Applied

Scientific EffectThermal insulation: Thermal Insulation

Data Source

PatentEP3000968B1Rotor disk assembly for a gas turbine engine and method

Publication Date: 2020.10.28 RTX CORP

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AI summary

A rotor assembly for a gas turbine engine includes a rotor disk (210). The rotor disk (210) includes a heat barrier feature (270) radially inward of a rotor blade (230) and radially outward of a rotor disk (210).