Turbomachine Vane Antivortex Fin Design

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Solution Overview

Problem

In turbomachine high pressure turbines, the formation of vortices at the radial clearance between the vane and the fixed casing due to pressure differences leads to aerodynamic losses and increased stress on the blades, which existing fin designs exacerbate by increasing the blade's weight and risk of contact with the casing.

Innovation Solution

A turbomachine vane with a radially inwardly offset fin that blocks the formation of vortices at the top of the blade, minimizing its weight impact and incorporating cooling features like bores and grooves to manage heat, while being designed to avoid contact with the casing through a hollow recess and optimized dimensions.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Loss of energy

If a fin is added to the top of the blade to restrict vortex formation, then aerodynamic losses are reduced, but the weight of the vane increases causing higher stresses and potential contact with the casing

Engineering Contradiction:

Improveaerodynamic lossesVSAvoidvane weight

Core Design Contradiction:

Loss of energyVSWeight of moving object

Solution Approach 1:

The fin is positioned locally at the top of the blade where vortex formation occurs, rather than adding weight throughout the entire blade structure. This localized approach restricts vortex formation and aerodynamic losses while minimizing the overall weight increase and associated stresses on the vane

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The fin extends in a direction perpendicular to the main blade axis, utilizing the radial dimension to block vortex formation at the blade top. This dimensional approach allows the fin to perform its aerodynamic function without requiring increased blade length or cross-sectional area, thereby limiting weight increase

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Productivity

If a fin is added to prevent vortices, then turbine efficiency is improved, but the risk of fin contact with the fixed casing increases

Engineering Contradiction:

Improveturbine efficiencyVSAvoidcontact risk

Core Design Contradiction:

ProductivityVSReliability

Solution Approach 1:

The fin is designed with predetermined dimensions and positioning that account for thermal expansion and centrifugal forces during operation. By pre-calculating and incorporating appropriate clearances and structural characteristics, the design prevents contact with the fixed casing while maintaining the vortex-restricting function that improves turbine efficiency

Inventive Principle:

Principle #10Preliminary action

3Object-generated harmful factors

If the fin is positioned at the top of the blade, then vortex formation is restricted, but the fin weight increases the inertia and stresses on the blade

Engineering Contradiction:

Improvevortex formationVSAvoidcentrifugal stress

Core Design Contradiction:

Object-generated harmful factorsVSForce

Solution Approach 1:

The fin is designed as a localized structure at the blade top with optimized dimensions that provide sufficient vortex restriction while minimizing mass. This local approach reduces the moment of inertia and centrifugal forces compared to alternative designs that would distribute weight differently throughout the blade

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The fin's dimensions, thickness, and material properties are optimized to achieve the minimum necessary mass for effective vortex restriction. By carefully controlling these parameters, the design balances the need to prevent vortex formation with the need to minimize inertial and centrifugal stresses on the rotating blade

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 solution effectively prevents vortex formation and reduces the risk of fin contact with the casing, enhancing turbine efficiency and reducing stress on the blades by minimizing the weight and optimizing the fin's dimensions and cooling mechanisms.

Implementation Method 1

Because of the pressure difference between the lower surface and the upper surface of each blade, a vortex is formed at this radial clearance

Methodology Applied

Scientific EffectVortex formation: Vortex Ring

Implementation Method 2

the presence of the fin increases the general moveable weight of the vane, which induces further stresses on the blade when the turbomachine rotates

Methodology Applied

Scientific EffectTurbulence: Turbulence

Implementation Method 3

incorporating cooling features like bores and grooves to manage heat

Methodology Applied

Scientific EffectHeat transfer: Conduction (thermal)

Data Source

PatentUS10260361B2Turbomachine vane including an antivortex fin

Publication Date: 2019.04.16 SAFRAN AIRCRAFT ENGINES SAS

AI summary

The invention relates to a turbomachine vane comprising a root and a blade including a median main plane having a longitudinal and radial main orientation, which is carried by the root, the blade including a leading edge located at an upstream longitudinal end, a trailing edge located at a longitudinal end downstream of the leading edge with respect to a gas stream flowing around the blade, a lower surface wall and an upper surface wall which are located laterally remote from each other and each connecting the leading edge to the trailing edge, and a top located at the free outer radial end of the blade, the blade further including a fin having a longitudinal main orientation which is carried by the lower surface side, which is located at the top of the blade, wherein the fin is radially inwardly offset with respect to the top of the blade.