Gas Turbine Inlet Guide Vane Spoke Integration

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Solution Overview

Problem

Gas turbine engines face challenges in efficiently guiding flow and providing structural support while minimizing axial length and complexity, particularly in the inlet section where bifurcations and rotatable airfoils can complicate the design.

Innovation Solution

The guide vane assembly in the inlet section features a shroud mechanically attached to spokes, with a split annular hoop arrangement supporting radially inward ends of the spokes, allowing each guide vane to rotate about a respective spoke for varying flow, and includes a bearing carrier trapped between the shroud and rotor, with fluid passages for lubricant communication, eliminating bifurcations and optimizing structural support.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Ease of operation

If traditional inlet sections with bifurcations and rotatable airfoils are used, then flow guidance capability is improved, but device complexity and axial length increase

Engineering Contradiction:

Improveflow guidance capabilityVSAvoidinlet section complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The patent removes bifurcations and rotatable airfoils from the inlet section, extracting the problematic elements that caused complexity while maintaining flow guidance through a simplified guide vane assembly with fixed vanes attached directly to the inlet case

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The guide vanes serve multiple functions: they guide flow into the compressor and provide structural support for the inlet section, eliminating the need for separate bifurcation structures and rotatable airfoil mechanisms

Inventive Principle:

Principle #6Universality (Multi-functionality)

2Strength

If traditional inlet sections with bifurcations are used, then structural support is provided, but axial length increases

Engineering Contradiction:

Improvestructural supportVSAvoidaxial length

Core Design Contradiction:

StrengthVSLength of moving object

Solution Approach 1:

The patent combines structural support and flow guidance functions into a single integrated guide vane assembly, where the guide vanes are directly attached to the inlet case, eliminating the need for separate bifurcation structures that would increase axial length

Inventive Principle:

Principle #5Merging (Combining)

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 flow control, reduces axial length, and simplifies the engine design by providing structural support and lubrication while minimizing bifurcations, resulting in a more efficient and compact gas turbine engine.

Implementation Method 1

the fluid passage is operable to communicate lubricant between the bearing assembly and a lubrication source

Methodology Applied

Scientific EffectLubrication: Lubrication

Data Source

PatentEP3388638B1Guide vane arrangement for gas turbine engine

Publication Date: 2019.12.04 UNITED TECH CORP

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AI summary

An inlet section (12) for a gas turbine engine (10) includes an outer case (34) extending about a rotor (42) that is rotatable about an engine axis (A). The rotor (42) carries a plurality of airfoils (44). A plurality of guide vanes (46) are operable to guide flow from an engine inlet (32) toward the plurality of airfoils (44) relative to the engine axis (A). A plurality of spokes (48) are mechanically attached to the outer case (34). Each of the plurality of spokes (42) is received in a respective one of the plurality of guide vanes (46), and at least one of the plurality of spokes (48) define a fluid passage (50) in flow communication with a bearing assembly (51).