Variable Guide Vanes for Gas Turbine Compressor Strut Wake Control

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Solution Overview

Problem

The presence of load-bearing struts in the gas path of gas turbine engines induces undesirable flow conditions and energy losses due to their interaction with air flow, which existing technologies have not adequately addressed.

Innovation Solution

The implementation of a compressor section assembly with an outer and inner shroud defining a substantially annular gas path, featuring radially extending struts and uniformly angularly spaced variable orientation guide vanes that overlap the strut passages, allowing for the partial confinement and modification of strut wakes to improve flow conditions and reduce energy losses.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Strength

If struts are disposed in the gas path to provide structural support, then structural strength is improved, but flow conditions deteriorate and energy losses increase

Engineering Contradiction:
Improvestructural strengthVSAvoidenergy losses
Core Design Contradiction:
StrengthVSLoss of energy

Solution Approach 1:

Guide vanes are introduced as intermediary elements between the struts and the rotor. These vanes modify the flow patterns generated by the struts, confining and redirecting the flow to reduce energy losses while maintaining the structural support function of the struts

Inventive Principle:
Principle #24Intermediary (Mediator)

Solution Approach 2:

The invention changes the flow parameters (velocity distribution, flow direction) by positioning guide vanes at specific angular spacings relative to the struts. This modifies the flow conditions downstream of the struts to reduce turbulence and energy losses

Inventive Principle:
Principle #35Parameter changes

2Strength

If struts are disposed in the gas path to provide structural support, then structural strength is improved, but flow conditions deteriorate

Engineering Contradiction:
Improvestructural strengthVSAvoidflow conditions
Core Design Contradiction:
StrengthVSObject-affected harmful factors

Solution Approach 1:

Guide vanes serve as intermediary elements that mediate between the harmful flow disturbances created by struts and the downstream flow. The vanes reconfigure the flow patterns to reduce harmful effects such as turbulence and flow separation

Inventive Principle:
Principle #24Intermediary (Mediator)

Solution Approach 2:

The invention converts the harmful flow disturbances generated by struts into beneficial patterns by using guide vanes to organize and redirect the flow. The wake regions behind struts are transformed into controlled flow paths that reduce overall energy losses

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

3Loss of energy

If variable orientation guide vanes are added to modify strut wakes, then energy losses are reduced, but device complexity increases

Engineering Contradiction:
Improveenergy lossesVSAvoiddevice complexity
Core Design Contradiction:
Loss of energyVSDevice complexity

Solution Approach 1:

The guide vanes are designed with variable orientation capability, allowing them to be rotated to different angular positions. This dynamic adjustment enables optimization of flow modification under varying operating conditions, reducing energy losses across different ranges

Inventive Principle:
Principle #15Dynamics

Solution Approach 2:

The compressor section is segmented into distinct functional elements: struts for structural support, guide vanes for flow modification, and rotors for compression. This segmentation allows each component to be optimized independently while working together to reduce overall energy losses

Inventive Principle:
Principle #1Segmentation

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 enhances the performance of gas turbine engines by improving flow conditions, expanding the operable range of the compressor, and reducing energy losses and aerodynamic loading on rotors.

Implementation Method 1

a plurality of variable orientation guide vanes extending radially in the gas path, the variable orientation guide vanes uniformly angularly spaced-apart around the central axis, one or more of the variable orientation guide vanes having a leading edge axially overlapping the strut passage

Methodology Applied
Scientific EffectAerodynamic interaction: Aerofoil

Data Source

PatentUS11952943B2Assembly for a compressor section of a gas turbine engine
Publication Date: 2024.04.09 PRATT & WHITNEY CANADA CORP
  • US11952943B2 patent drawing
  • US11952943B2 patent drawing
  • US11952943B2 patent drawing

AI summary

Assemblies and methods for directing a flow of air through a compressor section of a gas turbine engine are disclosed. A method includes receiving the flow of air over a strut extending radially across a substantially annular gas path of the gas turbine engine, and at least partially confining and modifying a strut wake generated in the flow of air by the strut using one or more variable orientation guide vanes.