Gas Turbine Blade Chamfer for Cooling Air Reuse

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Solution Overview

Problem

Gas turbine blades experience mechanical and thermal stresses at the transition region where the airfoil meets the platform, leading to potential mechanical fatigue and failure, and existing cooling methods are inefficient in reusing cooling air for enhanced cooling of this critical area.

Innovation Solution

The design incorporates a chamfer part on the blade's platform, which facilitates the flow of reused cooling air to the transition region and adjoining areas, enhancing cooling efficiency by directing the air flow through the chamfered edge and fillet regions, and includes cooling channels with outlets strategically positioned to optimize air flow and pressure distribution.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Temperature

If cooling air is withdrawn from the compressor section to cool the transition region, then the cooling effect is improved, but the loss of energy increases

Engineering Contradiction:

Improvecooling effectVSAvoidenergy loss

Core Design Contradiction:

TemperatureVSLoss of energy

Solution Approach 1:

The patent recovers cooling air from the turbine exhaust side and reuses it to cool the transition region. Instead of continuously withdrawing fresh cooling air from the compressor section, the system captures and reutilizes exhaust air that would otherwise be discarded, thereby improving cooling efficiency while reducing energy loss.

Inventive Principle:

Principle #34Discarding and recovering

Solution Approach 2:

The cooling air serves multiple functions: it cools the transition region, seals the gap between adjacent blades, and prevents hot gas ingress. By making the cooling air system multi-functional, the patent reduces the total amount of cooling air needed from the compressor section, thereby reducing energy loss while maintaining effective cooling.

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Reliability

If the transition region is cooled to prevent mechanical fatigue, then the reliability is improved, but the device complexity increases

Engineering Contradiction:

Improveblade durabilityVSAvoidcooling system complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The chamfer part on the suction side of the platform passively directs cooling air flow toward the transition region without requiring additional active components. The geometric feature itself serves the cooling function, simplifying the overall system while maintaining reliable cooling of the critical transition region.

Inventive Principle:

Principle #25Self-service

Solution Approach 2:

The cooling air acts as an intermediary substance that transfers thermal energy away from the transition region. By utilizing the cooling air flow path and the chamfer geometry as intermediaries, the system achieves reliable cooling without complex mechanical cooling devices.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Productivity

If cooling air flow path is directed through the chamfer part, then the cooling efficiency is improved, but the manufacturing precision requirements increase

Engineering Contradiction:

Improvecooling efficiencyVSAvoidchamfer geometry precision

Core Design Contradiction:

ProductivityVSManufacturing precision

Solution Approach 1:

The patent specifies a chamfer angle within the range of 45-60 degrees, providing flexibility in the manufacturing process. This parameter range allows for effective cooling air direction while accommodating normal manufacturing tolerances, balancing cooling efficiency with manufacturability.

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 chamfered edge and cooling channel design effectively directs cooling air to critical regions, improving the durability of the blades by increasing the cooling effect and reusing cooling air, thus extending the operational life of the gas turbine blades.

Implementation Method 1

facilitates the flow of reused cooling air to the transition region and adjoining areas, enhancing cooling efficiency by directing the air flow through the chamfered edge

Methodology Applied

Scientific EffectFluid flow:

Implementation Method 2

cooling of the transition region, i.e., the region where the airfoil meets/joins the upper surface of the platform, to enhance operation life

Methodology Applied

Scientific EffectConvection cooling: Convection

Data Source

PatentUS11668195B2Gas turbine blade for re-using cooling air and turbomachine assembly and gas turbine comprising the same

Publication Date: 2023.06.06 DOOSAN HEAVY IND & CONSTR CO LTD

AI summary

The present technique presents a gas turbine blade for re-using cooling air, a turbomachine assembly having the blade, and a gas turbine having the turbomachine assembly. The blade includes a platform and an airfoil extending from the platform. The airfoil includes a pressure surface, a suction surface, a leading edge and a trailing edge. The platform includes a pressure side, a suction side, a leading-edge side and a trailing-edge side, disposed towards the pressure surface, the suction surface, the leading edge and the trailing edge of the airfoil, respectively. The suction side of the platform includes a part of the upper surface and a suction-side lateral surface of the platform. At least a part of an edge between the suction-side lateral surface and the upper surface of the platform comprises a chamfer part.