Convex Edge Guide Vane Ring Element for Turbomachine Leakage

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Solution Overview

Problem

Existing guide vane ring elements in turbomachines, such as gas turbines, face issues with leakage and flow disruption due to the beveled edges of drilled holes, which affect the efficiency and performance of the machinery.

Innovation Solution

The guide vane ring element features drilled holes with a convex edge in a first circumferential portion, reducing leakage and flow disruption by merging into a radius that can be constant or varying, manufactured using milling cutters, to accommodate rotatable guide vanes effectively.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If drilled holes have beveled edges due to expansion of vane element, then the guide vane can be mounted rotatably, but leakage and flow disruption occur reducing efficiency

Engineering Contradiction:

Improvemounting of rotatable guide vaneVSAvoidleakage and flow disruption

Core Design Contradiction:

Ease of operationVSLoss of energy

Solution Approach 1:

The patent applies curvature by forming a radius at the edge of the drilled hole in the circumferential portion. This curved edge geometry replaces the conventional beveled edge, reducing flow disruption and leakage while maintaining the mounting function for the rotatable guide vane flange.

Inventive Principle:

Principle #14Spheroidality (Curvature)

2Ease of manufacture

If the edge of drilled hole is beveled, then manufacturing is simplified, but flow disruption and leakage increase

Engineering Contradiction:

Improvedrilled hole edge formationVSAvoidturbomachine efficiency

Core Design Contradiction:

Ease of manufactureVSProductivity

Solution Approach 1:

The patent introduces a curved radius at the drilled hole edge, which can be manufactured using standard milling cutters. This curved geometry improves turbomachine efficiency by reducing flow disruption and leakage compared to conventional beveled edges, while remaining compatible with existing manufacturing capabilities.

Inventive Principle:

Principle #14Spheroidality (Curvature)

3Loss of energy

If convex edge is formed in first circumferential portion, then leakage and flow disruption are reduced, but manufacturing complexity increases

Engineering Contradiction:

Improveleakage reductionVSAvoidedge geometry complexity

Core Design Contradiction:

Loss of energyVSDevice complexity

Solution Approach 1:

The patent implements a radius in the first circumferential portion of the drilled hole edge to reduce leakage and flow disruption. The second circumferential portion maintains a simpler geometry, allowing the complex curved feature to be localized only where needed for flow optimization.

Inventive Principle:

Principle #14Spheroidality (Curvature)

Solution Approach 2:

The edge of the drilled hole is divided into two distinct circumferential portions: a first portion with a radius for flow optimization and a second portion with different geometry for mounting functionality. This segmentation allows each portion to be optimized for its specific function while simplifying the overall manufacturing approach.

Inventive Principle:

Principle #1Segmentation

Data Source

PatentUS11066949B2Guide vane ring element for a turbomachine

Publication Date: 2021.07.20 MTU AERO ENGINES GMBH

AI summary

The present invention relates to a guide vane ring element for a turbomachine, such as a gas turbine, with at least one drilled hole for the at least partial uptake of a flange of a rotatable guide vane, wherein an edge of the drilled hole on the vane element side is designed convexly along the edge in a first circumferential portion and, in particular, has a radius.