Segmented Inlet Guide Vanes for Gas Turbine Rotor Tip Stalling

Solution Overview

Problem

Gas turbine engines experience non-synchronous vibration (NSV) and rotor blade stalling at partial load or speed due to insufficient airflow to the rotor tips when inlet guide vanes are closed, leading to decreased efficiency and operability issues.

Innovation Solution

Implementing inlet guide vanes with fixed and rotatable portions, where the outer radial panel remains stationary and the inner radial panel is rotatable, allowing for controlled airflow to maintain higher axial flow to the rotor tips and reduce NSV, and incorporating stator vanes with fixed and rotatable portions to enhance structural integrity.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stability of the object's composition

If inlet guide vanes are closed to increase swirl, then air swirling into rotor blades is improved, but airflow to rotor tips becomes insufficient causing non-synchronous vibration and stalling

Engineering Contradiction:

Improveair swirlVSAvoidrotor blade stalling

Core Design Contradiction:

Stability of the object's compositionVSReliability

Solution Approach 1:

The inlet guide vane is divided into three radially extending portions: a first portion, a second portion, and a third portion. The first and third portions are fixed relative to the casing, while the second portion is rotatable. This segmentation allows different portions to perform different functions - the fixed portions maintain structural stability and provide baseline swirl, while the rotatable second portion can be adjusted to control airflow distribution to prevent rotor tip stalling.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different portions of the inlet guide vane have different degrees of freedom. The first and third portions are fixed to provide stable airflow paths, while the second portion is made rotatable to locally adjust airflow distribution. This local quality differentiation allows the vane to simultaneously provide consistent swirl while preventing rotor tip stalling through localized airflow control.

Inventive Principle:

Principle #3Local quality

2Stability of the object's composition

If inlet guide vanes are closed to increase swirl, then air swirling into rotor blades is improved, but non-synchronous vibration occurs at partial load

Engineering Contradiction:

Improveair swirlVSAvoidnon-synchronous vibration

Core Design Contradiction:

Stability of the object's compositionVSObject-generated harmful factors

Solution Approach 1:

The inlet guide vane is divided into three radially extending portions: a first portion, a second portion, and a third portion. The first and third portions are fixed relative to the casing, while the second portion is rotatable. This segmentation allows different portions to perform different functions - the fixed portions maintain structural stability and provide baseline swirl, while the rotatable second portion can be adjusted to control airflow distribution to prevent rotor tip stalling.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The second portion of the inlet guide vane is made rotatable relative to the first and third portions, enabling dynamic adjustment of airflow distribution. This dynamic capability allows the system to adapt to varying operating conditions (including partial load) and adjust the swirl angle to prevent non-synchronous vibration while maintaining adequate airflow to rotor tips.

Inventive Principle:

Principle #15Dynamics

3Adaptability or versatility

If entire inlet guide vane is made rotatable, then airflow control is improved, but structural integrity and complexity increase

Engineering Contradiction:

Improveairflow controlVSAvoidvane structure

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The inlet guide vane is divided into three radially extending portions: a first portion, a second portion, and a third portion. The first and third portions are fixed relative to the casing, while the second portion is rotatable. This segmentation allows different portions to perform different functions - the fixed portions maintain structural stability and provide baseline swirl, while the rotatable second portion can be adjusted to control airflow distribution to prevent rotor tip stalling.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Different portions of the inlet guide vane have different degrees of freedom. The first and third portions are fixed to provide stable airflow paths, while the second portion is made rotatable to locally adjust airflow distribution. This local quality differentiation allows the vane to simultaneously provide consistent swirl while preventing rotor tip stalling through localized airflow control.

Inventive Principle:

Principle #3Local quality

Data Source

PatentUS20250207508A1Gas turbine engines having moveable inlet guide vanes and stator vanes

Publication Date: 2025.06.26 GENERAL ELECTRIC CO

AI summary

Gas turbine engines having moveable inlet guide vanes and stator vanes are described herein. An example gas turbine engine includes a casing defining a flow passageway to a compressor. The casing includes an outer radial wall and an inner radial wall. The compressor includes alternating stages of rotor blades and stator vanes in the flow passageway. The gas turbine engine also includes an inlet guide vane in the flow passageway upstream of a first stage of rotor blades of the compressor. The inlet guide vane extends between the outer radial wall and the inner radial wall. The inlet guide vane includes an outer radial panel coupled to the outer radial wall, an inner radial panel coupled to the inner radial wall, and a middle panel between the outer radial panel and the inner radial panel. The middle panel is rotatable relative to the outer and inner radial panels.