Turbine Airfoil Leading-Edge Cooling With Plenum-Fed Film Holes

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Solution Overview

Problem

Existing turbine airfoil cooling systems require excessive coolant volumes to effectively cool the leading edge, impacting gas turbine efficiency and output.

Innovation Solution

A turbine airfoil design featuring dual cooling circuits with alternating suction side to pressure side and pressure side to suction side cooling passages, coupled with plenums and film cooling holes, reduces coolant requirements by enhancing heat absorption and film coverage.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Quantity of substance

If traditional outwardly directed cooling holes are used in the leading edge, then cooling coverage is provided, but excessive coolant volume is required

Engineering Contradiction:

Improvecoolant volumeVSAvoidcooling effectiveness

Core Design Contradiction:

Quantity of substanceVSReliability

Solution Approach 1:

The cooling system is divided into multiple alternating sub-circuits (first cooling passages from suction side to pressure side, second cooling passages from pressure side to suction side) that are distributed around the leading edge. This segmentation allows each sub-circuit to independently deliver coolant to specific zones, improving overall cooling efficiency while reducing total coolant requirements.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different regions of the leading edge are served by different cooling sub-circuits with optimized passage configurations. The first and second cooling passages are positioned to provide localized cooling where heat flux is highest, ensuring effective cooling with minimal coolant volume by targeting critical thermal zones rather than uniform cooling.

Inventive Principle:

Principle #3Local quality

2Temperature

If cooling passages extend around the leading edge, then heat absorption is improved, but passage complexity increases

Engineering Contradiction:

Improveheat absorption capabilityVSAvoidcooling circuit configuration

Core Design Contradiction:

TemperatureVSDevice complexity

Solution Approach 1:

Multiple cooling passages are merged into alternating sub-circuits that share common structural features and cooling objectives. The first and second cooling passages are integrated into a unified leading edge cooling system where adjacent passages work together to distribute coolant efficiently around the leading edge, reducing overall system complexity while maintaining enhanced heat absorption.

Inventive Principle:

Principle #5Merging (Combining)

3Productivity

If film cooling holes are used to deliver coolant, then cooling efficiency increases, but precision in hole positioning and sizing is required

Engineering Contradiction:

Improvecooling efficiencyVSAvoidfilm cooling hole specifications

Core Design Contradiction:

ProductivityVSManufacturing precision

Solution Approach 1:

The film cooling holes are designed with optimized parameters including cross-sectional area (0.03-0.8 square millimeters) and positioning that balance cooling efficiency with manufacturability. By carefully selecting these parameters within specified ranges, the system achieves high cooling efficiency while accommodating standard manufacturing capabilities and tolerances.

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

The dual cooling circuit design minimizes coolant volume while maintaining effective cooling, preventing working fluid ingestion, and improving gas turbine efficiency and output.

Implementation Method 1

at least one first cooling passage extending inside the wall of the body from the suction side to the pressure side around the leading edge

Methodology Applied

Scientific EffectConvection: Convection

Implementation Method 2

coolant volume to effectively cool the leading edge

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Implementation Method 3

plurality of first film cooling holes in fluid communication with the plenum and extending through the wall on the pressure side

Methodology Applied

Scientific EffectFilm cooling: Boundary Layer

Implementation Method 4

enhancing heat absorption and film coverage

Methodology Applied

Scientific EffectHeat transfer: Convection

Data Source

PatentEP4317649B1Turbine airfoil with leading edge cooling passages coupled via a plenum to film cooling holes

Publication Date: 2026.02.25 GENERAL ELECTRIC TECH GMBH

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AI summary

A turbine airfoil (152, 162) includes a body (148, 164) including a wall (150, 166) defining pressure (154, 168) and suction (156, 170) sides, and a leading edge (158, 172) extending between the pressure and suction sides. A cooling circuit (180) inside the wall (150, 166) of the body (148, 164) includes at least one of: a) a suction side to pressure side cooling sub-circuit (182) including a first cooling passage(s) (200) extending from the suction side (156, 170) to the pressure side (154, 168) around the leading edge (158, 172) to a first plenum (186), and a plurality of first film cooling holes (214) communicating with the first plenum (186) and extending through the wall (150, 166) on the pressure side (154, 168); and b) a pressure side to suction side cooling sub-circuit (184) including second cooling passage(s) (202) extending from the pressure side (154, 168) to the suction side (156, 170) around the leading edge (158, 172) to a second plenum (188), and a plurality of second film cooling holes (234) communicating with the second plenum (188) and extending through the wall (150, 166) on the suction side (156, 170).