Turbine Nozzle Vane Cooling for Trailing Edge Thermal Stress

Solution Overview

Problem

Turbine nozzles in gas turbine engines experience stresses due to thermal gradients and non-uniform airfoil loads, leading to reduced durability and increased costs when traditional solutions like stronger materials or larger sizes are employed.

Innovation Solution

Incorporating cooling features such as trailing edge slots and baffle inserts in the vanes of the nozzle assembly to manage thermal gradients and reduce local stresses.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If stronger materials are used to reduce thermal stresses, then nozzle durability is improved, but cost and weight increase

Engineering Contradiction:

Improvenozzle durabilityVSAvoidnozzle weight

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The patent applies local quality by implementing cooling holes specifically at the trailing edge of the airfoil where thermal stresses are highest. This localized cooling approach addresses the thermal stress problem at the critical location without requiring stronger materials throughout the entire nozzle structure, thereby avoiding unnecessary weight increase.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The cooling air acts as an intermediary substance that transfers heat away from the trailing edge. By introducing this cooling medium through cooling holes, the patent mediates the thermal stress problem without changing the base material properties, avoiding the need for heavier stronger materials.

Inventive Principle:

Principle #24Intermediary (Mediator)

2Reliability

If stronger materials are used to reduce thermal stresses, then nozzle durability is improved, but cost increases

Engineering Contradiction:

Improvenozzle durabilityVSAvoidmanufacturing cost

Core Design Contradiction:

ReliabilityVSEase of manufacture

Solution Approach 1:

The patent applies local quality by implementing cooling holes specifically at the trailing edge of the airfoil where thermal stresses are highest. This localized cooling approach addresses the thermal stress problem at the critical location without requiring stronger materials throughout the entire nozzle structure, thereby avoiding unnecessary weight increase.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The cooling air acts as an intermediary substance that transfers heat away from the trailing edge. By introducing this cooling medium through cooling holes, the patent mediates the thermal stress problem without changing the base material properties, avoiding the need for heavier stronger materials.

Inventive Principle:

Principle #24Intermediary (Mediator)

3Reliability

If larger nozzle size is used to reduce thermal gradients, then durability is improved, but weight and complexity increase

Engineering Contradiction:

Improvenozzle durabilityVSAvoidnozzle structure complexity

Core Design Contradiction:

ReliabilityVSDevice complexity

Solution Approach 1:

The patent applies local quality by implementing cooling holes specifically at the trailing edge of the airfoil where thermal stresses are highest. This localized cooling approach addresses the thermal stress problem at the critical location without requiring stronger materials throughout the entire nozzle structure, thereby avoiding unnecessary weight increase.

Inventive Principle:

Principle #3Local quality

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 solution enhances nozzle durability and reduces stresses, maintaining performance without increasing weight or cost, and allows for high-performance turbine engines.

Implementation Method 1

The individual vanes of the plurality of vanes include: an airfoil including an outer surface defining a leading edge, a trailing edge, a suction side, and a pressure side, the outer surface forming an internal cavity of the airfoil. The airfoil further includes slots extending along the trailing edge in a generally radial direction, the slots defining a total slot flow area (SFA)... Individual vanes of the plurality of vanes further include a baffle insert extending within the internal cavity, the baffle insert including baffle walls and cooling holes formed in the baffle walls, the cooling holes defining a total cooling hole area (CHA)... wherein the slots and cooling holes work together to reduce thermal gradients and local stresses in the nozzle vanes.

Methodology Applied

Scientific EffectThermal gradient management: Temperature Gradient

Data Source

PatentUS20260098478A1Turbine engine with a nozzle having cooling features

Publication Date: 2026.04.09 GENERAL ELECTRIC CO

AI summary

A turbine engine includes an engine core extending along an engine centerline and includes a compressor section, a combustor, and a turbine section in serial flow arrangement. A turbine nozzle is arranged in the turbine section. Vanes of the turbine nozzle include a vane airfoil having cooling features formed in a trailing edge of the vane airfoil. Vanes of the turbine nozzle further include a baffle insert in a cavity of the vane airfoil. The baffle insert includes cooling holes.