Gas Turbine Blade Leading Edge Foot Alignment

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Existing blade and vane designs in gas turbine engines suffer from aerodynamic losses due to the interaction of main working gas flow and secondary or leakage flow, leading to the formation of horseshoe vortices and inefficient gas flow streamlines, which increase surface temperatures and reduce engine efficiency.

Innovation Solution

A blade or vane arrangement featuring aerofoils with a leading edge foot and a platform channel configuration, where the leading edge foot and channel surfaces are smoothly blended, with the ridge line aligned with the working gas flow and the channel's minimum radial height aligned with the secondary flow, reducing cross-passage secondary flow and enhancing coolant attachment to the platform.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of energy

If conventional blade or vane designs are used, then the structure is simple and easy to manufacture, but aerodynamic losses occur due to interaction of main working gas flow and secondary flow, forming horseshoe vortices and reducing engine efficiency

Engineering Contradiction:

Improveaerodynamic lossesVSAvoidblade or vane structure complexity

Core Design Contradiction:

Loss of energyVSDevice complexity

Solution Approach 1:

The platform leading edge is segmented into multiple functional zones: a first region with a first platform surface, a second region with a second platform surface, and a third region with a third platform surface. Each region has different orientations and functions for managing specific flow components, allowing targeted control of secondary flow while maintaining structural integrity

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different regions of the platform leading edge are given different surface orientations and geometries tailored to local flow requirements. The first region handles main working gas flow, the second region manages secondary flow, and the third region provides transition and attachment functions, optimizing local flow control without requiring complete redesign of the entire blade structure

Inventive Principle:

Principle #3Local quality

2Productivity

If the platform leading edge is designed to redirect secondary flow, then cross-passage secondary flow is reduced, but the platform structure becomes more complex

Engineering Contradiction:

Improveengine efficiencyVSAvoidplatform structure complexity

Core Design Contradiction:

ProductivityVSDevice complexity

Solution Approach 1:

The platform leading edge utilizes three-dimensional surface orientation with regions inclined at different angles relative to the axial direction. This multi-dimensional geometric configuration enables effective redirection of secondary flow in the radial direction while maintaining compatibility with the overall blade structure and manufacturing processes

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

3Reliability

If the ridge line is aligned with the working gas flow, then gas flow streamlines become more linear and smoother, but the manufacturing precision requirements increase

Engineering Contradiction:

Improvegas flow streamline qualityVSAvoidridge line alignment precision

Core Design Contradiction:

ReliabilityVSManufacturing precision

Solution Approach 1:

The platform surfaces in different regions are designed with curved transitions rather than sharp angles, creating smooth flow paths that guide the working gas flow linearly through the passage. The curved geometries naturally accommodate manufacturing tolerances while maintaining effective flow control

Inventive Principle:

Principle #14Spheroidality (Curvature)

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 reduces aerodynamic losses, improves gas flow streamlines, decreases surface temperatures, and increases engine efficiency by minimizing cross-passage secondary flow and enhancing coolant retention, leading to better blade platform cooling and reduced heat input.

Implementation Method 1

the ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow

Methodology Applied

Scientific EffectFlow alignment:

Implementation Method 2

the leading edge foot and channel surfaces are smoothly blended

Methodology Applied

Scientific EffectFlow attachment:

Implementation Method 3

enhancing coolant attachment to the platform

Methodology Applied

Scientific EffectCoolant retention:

Data Source

PatentUS10294796B2Blade or vane arrangement for a gas turbine engine

Publication Date: 2019.05.21 SIEMENS ENERGY GLOBAL GMBH & CO KG

AI summary

A blade or vane arrangement for a gas turbine engine has an array of aerofoils mounted to respective platforms about an axis and defining a passage through which a working gas flow passes. The arrangement has a datum and the aerofoil has a radial span. Each aerofoil has pressure side, a suction side, a leading edge region and a leading edge foot extending from the leading edge region, the leading edge foot has a ridge line. The platform defines a channel and a platform leading edge, the channel has a minimum radial height line, and the platform leading edge partly defines an outlet through which a secondary flow passes. The ridge line is aligned generally in the direction of the working gas flow and the minimum radial height line is aligned generally in the direction of the secondary flow.