Turbine Vane Impingement Plate Cooling

Solution Overview

Problem

Conventional gas turbines experience temperature gradients and thermal stress in turbine vanes due to inadequate cooling, leading to potential damage from uneven heat flux and cross-flow effects, where downstream regions are insufficiently cooled compared to upstream regions.

Innovation Solution

The gas turbine incorporates an impingement plate with injection holes of varying density and diameter along the turbine vane, with a higher density and larger diameters downstream to enhance cooling performance and prevent thermal stress, ensuring uniform air flow distribution across the vane surface.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of manufacture

If uniform injection holes are used across the impingement plate, then manufacturing is simplified, but temperature gradients and thermal stress occur in turbine vanes due to uneven cooling

Engineering Contradiction:

Improveimpingement plate manufacturingVSAvoidturbine vane thermal stress resistance

Core Design Contradiction:

Ease of manufactureVSReliability

Solution Approach 1:

The impingement plate features injection holes with varying densities and diameters distributed across different regions. Downstream regions have higher density and larger diameter holes compared to upstream regions, creating localized cooling characteristics that match the thermal load distribution on the turbine vane surface.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The injection holes are designed with changing parameters including density (holes per unit area) and diameter across the impingement plate surface. This parameter variation optimizes cooling effectiveness by providing more aggressive cooling where thermal stress is highest while maintaining uniform cooling across the entire vane surface.

Inventive Principle:

Principle #35Parameter changes

2Reliability

If downstream regions use higher density and larger diameter injection holes, then thermal stress is reduced, but device complexity increases

Engineering Contradiction:

Improveturbine vane thermal stress resistanceVSAvoidinjection hole distribution pattern

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The impingement plate features injection holes with varying densities and diameters distributed across different regions. Downstream regions have higher density and larger diameter holes compared to upstream regions, creating localized cooling characteristics that match the thermal load distribution on the turbine vane surface.

Inventive Principle:

Principle #3Local quality

3Reliability

If cross-flow effects are present in the impingement space, then downstream regions receive insufficient cooling, but increasing injection hole flow rate increases energy consumption

Engineering Contradiction:

Improvedownstream region cooling effectivenessVSAvoidcooling air energy consumption

Core Design Contradiction:

ReliabilityVSUse of energy by moving object

Solution Approach 1:

The impingement plate features injection holes with varying densities and diameters distributed across different regions. Downstream regions have higher density and larger diameter holes compared to upstream regions, creating localized cooling characteristics that match the thermal load distribution on the turbine vane surface.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The injection holes are designed with changing parameters including density (holes per unit area) and diameter across the impingement plate surface. This parameter variation optimizes cooling effectiveness by providing more aggressive cooling where thermal stress is highest while maintaining uniform cooling across the entire vane surface.

Inventive Principle:

Principle #35Parameter changes

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 configuration effectively prevents temperature gradients and thermal stress in turbine vanes, ensuring even cooling across all regions, thereby reducing the risk of damage and improving the overall efficiency and reliability of the gas turbine.

Implementation Method 1

The turbine vane cooling passage is provided with an impingement plate having a plurality of injection holes through which air is injected onto an inner wall of the turbine vane, so as to enhance the cooling performance

Methodology Applied

Scientific EffectImpingement cooling: Convection

Data Source

PatentEP3460194B1Gas turbine

Publication Date: 2020.12.16 DOOSAN HEAVY IND & CONSTR CO LTD

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AI summary

The present invention relates to a turbine vane (520) to guide a flow of the combustion gas toward a turbine blade, the turbine vane having a turbine vane cooling passage (527) for delivering cooling fluid to an inner wall of the turbine vane (520) and an impingement plate (700) installed in the turbine vane cooling passage (527), the impingement plate (700) having a plurality of injection holes (712, 714) through which the cooling fluid is injected onto the inner wall of the turbine vane (520), the injection holes (712, 714) formed at predetermined locations of the impingement plate (700). The injection holes (712, 714) are formed differently depending on locations, namely the distribution of injection holes is increased towards a downstream side of the cooling flow, such that a temperature gradient or thermal stress may be prevented from occurring in the turbine vane.