Annular Dividing Guide Body in Gas Turbine Diffuser

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Solution Overview

Problem

In gas turbine engines, the configuration of a diffuser divided in the radial direction, supported by struts, limits the flexibility in arranging the division body and support body, making it difficult to sufficiently reduce pressure loss while maintaining a compact engine size.

Innovation Solution

A gas turbine engine design where the dividing guide body is supported by the inner diameter side wall, allowing greater freedom in arrangement and reducing pressure loss, with guide support bodies disposed radially inward of the transition duct to ensure uniform gas supply and minimize size increase.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Adaptability or versatility

If the division body is supported by struts, then the structure is stable, but the arrangement flexibility is limited

Engineering Contradiction:

Improvearrangement flexibilityVSAvoidsupport structure complexity

Core Design Contradiction:

Adaptability or versatilityVSDevice complexity

Solution Approach 1:

The invention extracts the support function from the strut structure and relocates it to the inner diameter side wall. The division body is now supported directly by the inner diameter side wall of the compressed gas supply portion, eliminating the need for separate strut supports and thereby increasing arrangement flexibility while reducing structural complexity.

Inventive Principle:

Principle #2Taking out (Extraction)

Solution Approach 2:

The support position is moved from a radial support (struts) to an axial support (inner diameter side wall). This dimensional change in support orientation allows the division body to be positioned more freely in the radial direction without being constrained by strut locations, thus improving arrangement flexibility.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Loss of energy

If the axial distance of the air flow path is increased, then the static pressure recovery is improved, but the engine size increases

Engineering Contradiction:

Improvepressure lossVSAvoidaxial size

Core Design Contradiction:

Loss of energyVSLength of moving object

Solution Approach 1:

The air flow path is divided into multiple segments by the division body, creating several parallel flow channels. This segmentation allows the total flow path area to be increased without proportionally increasing the axial length, as the flow is distributed across multiple channels that can be arranged in a more compact axial configuration.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Instead of extending the flow path primarily in the axial direction, the invention utilizes the radial dimension by dividing the flow path radially. This allows the flow path area to be enlarged in the radial direction while keeping the axial length compact, thereby reducing pressure loss without increasing engine size.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

3Loss of energy

If the flow-path area is enlarged, then the static pressure recovery ratio increases, but the flow-path enlargement rate increases causing separation

Engineering Contradiction:

Improvestatic pressure recovery ratioVSAvoidflow separation

Core Design Contradiction:

Loss of energyVSObject-affected harmful factors

Solution Approach 1:

By dividing the flow path into multiple channels, the flow-path enlargement rate in each individual channel is reduced compared to a single large channel. This segmentation allows the total flow area to be enlarged while maintaining a manageable enlargement rate in each segment, preventing flow separation.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

Each divided flow channel has optimized local geometry with controlled enlargement rates suitable for its specific flow conditions. This local optimization ensures that each channel maintains attached flow while collectively providing a large total flow area for high static pressure recovery ratio.

Inventive Principle:

Principle #3Local quality

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 loss while allowing for flexible arrangement of components, ensuring efficient gas supply and maintaining a compact engine size.

Implementation Method 1

a diffuser is provided at an outlet of a compressor, whereby static pressure of compressed air is recovered

Methodology Applied

Scientific EffectDiffusion: Diffusion

Implementation Method 2

static pressure of compressed air is recovered, and pressure loss (mainly, dynamic pressure loss) until the compressed air flows into a combustor is reduced

Methodology Applied

Scientific EffectPressure gradient: Pressure Gradient

Implementation Method 3

the flow-path enlargement rate is reduced if the flow-path length is the same. Consequently, separation of air flow is not likely to occur

Methodology Applied

Scientific EffectFlow separation control: Flow Separation

Data Source

PatentUS11009041B2Gas turbine engine with diffuser having an annular dividing guide body

Publication Date: 2021.05.18 KAWASAKI JUKOGYO KK

AI summary

A gas turbine engine, in which a compressed gas from a compressor is burned in a combustor and obtained combustion gas drives a turbine, includes: a compressed gas supply portion configured to supply the compressed gas obtained from the compressor to the combustor; an annular dividing guide body disposed in a diffuser that forms an upstream-side portion of the compressed gas supply portion, the dividing guide body being configured to divide the compressed gas in a radial direction; and a guide support body that supports the dividing guide body on an inner diameter side wall of the compressed gas supply portion.