Turbine Blade Tip Winglet for Vortex Control

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Solution Overview

Problem

Gas turbine engines experience efficiency and performance reductions due to tip vortex formation between rotating blades and stationary shrouds, which existing geometrical features fail to adequately address, particularly on the suction side of the blade.

Innovation Solution

The implementation of a winglet on the turbine blade, positioned at the vortex onset point, guides leakage air to compact the vortex, reducing pressure loss by optimizing its configuration to start aft of the leading edge and terminate forward of the trailing edge, thereby minimizing weight and enhancing performance.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If tip flares or other geometrical features are used to enhance tip sealing characteristics, then pressure side sealing is improved, but suction side vortex losses are not addressed

Engineering Contradiction:

Improvetip sealing characteristicsVSAvoidvortex roll-up pressure loss

Core Design Contradiction:

ReliabilityVSLoss of energy

Solution Approach 1:

The patent applies different geometrical features to different locations on the blade tip: tip flares address the pressure side sealing, while suction side winglets specifically address the suction side vortex losses. This localized application of different features to different problem areas resolves the contradiction by treating each side's unique requirements separately rather than using a uniform approach.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The blade tip is segmented into functionally distinct features: tip flares for pressure side sealing and separate suction side winglets for vortex control. This segmentation allows each feature to be optimized for its specific function without interfering with the other, enabling simultaneous improvement of both pressure side sealing and suction side vortex loss reduction.

Inventive Principle:

Principle #1Segmentation

2Loss of substance

If existing tip sealing features are applied, then pressure side leakage is reduced, but vortex development and associated pressure loss on suction side are not inhibited

Engineering Contradiction:

Improveleakage airVSAvoidpressure loss

Core Design Contradiction:

Loss of substanceVSLoss of energy

Solution Approach 1:

The patent implements location-specific solutions: tip flares at the pressure side to control leakage air, and suction side winglets positioned at the vortex onset point to control vortex development. Each feature addresses the specific flow conditions and loss mechanisms present at its location, resolving the contradiction between leakage reduction and vortex loss prevention.

Inventive Principle:

Principle #3Local quality

Solution Approach 2:

The suction side winglets are positioned to interact with the vortex flow in a way that converts the harmful vortex roll-up into a more controlled flow pattern. By placing the winglet at the vortex onset point, the design captures the vortex formation process and redirects it, transforming the energy loss mechanism into a more efficient flow configuration that reduces overall pressure loss.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

3Loss of energy

If a winglet extends from leading edge to trailing edge, then vortex guidance is maximized, but blade weight increases

Engineering Contradiction:

Improvepressure loss reductionVSAvoidblade weight

Core Design Contradiction:

Loss of energyVSWeight of moving object

Solution Approach 1:

Instead of extending the winglet across the entire chord from leading edge to trailing edge, the patent positions it partially on the suction side starting from the vortex onset point (which is aft of the leading edge) and extending only to a point forward of the trailing edge. This partial action provides sufficient vortex guidance functionality while minimizing the added weight and material requirements.

Inventive Principle:

Principle #16Partial or excessive action

Solution Approach 2:

The winglet's position and extent are optimized by changing the parameters of its location: starting point aft of the leading edge at the vortex onset point, and ending point forward of the trailing edge. This parameter optimization achieves the necessary vortex control function with minimal material, resolving the contradiction between effectiveness and weight.

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

This configuration effectively reduces pressure losses and increases turbine efficiency by compacting the vortex, leading to a 0.10-point increase in turbine efficiency and a 0.05-0.10% decrease in specific fuel consumption.

Implementation Method 1

Combustion gas leaks over the blade tips from a pressure side of each blade to a suction side of the blade. This leakage rolls up into a vortex on the suction side

Methodology Applied

Scientific EffectVortex: Vortex Ring

Implementation Method 2

Combustion gas leaks over the blade tips from a pressure side of each blade to a suction side of the blade

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Data Source

PatentUS10934858B2Method and system for improving turbine blade performance

Publication Date: 2021.03.02 GENERAL ELECTRIC CO

AI summary

A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.