Centrifugal Compressor to Axial Combustor Flow Coupling

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Solution Overview

Problem

The aerodynamic coupling of a centrifugal compressor and an axial through-flow combustor in gas turbine engines often results in misalignment, leading to suboptimal performance due to flow direction and area changes, which complicates achieving efficient static pressure recovery and minimal losses.

Innovation Solution

A system utilizing a vectored deswirl assembly in conjunction with a dome shroud attachment, including a diffuser, deswirl assembly, combustor inner and outer annular liners, a combustor dome, and a curved annular plate, to redirect and condition airflow from the centrifugal compressor for optimal alignment and performance with the axial combustor.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Stress or pressure

If a centrifugal compressor is used to compress air, then high pressure is achieved, but flow misalignment occurs when connecting to an axial combustor

Engineering Contradiction:

Improvestatic pressureVSAvoidflow alignment

Core Design Contradiction:

Stress or pressureVSEase of operation

Solution Approach 1:

A deswirl assembly is introduced as an intermediary component between the centrifugal compressor and axial combustor. This assembly includes guide vanes that actively redirect the radially outward flowing air from the centrifugal compressor into an axial flow direction, mediating the transition and eliminating flow misalignment while preserving the high pressure characteristics.

Inventive Principle:

Principle #24Intermediary (Mediator)

Solution Approach 2:

The system transitions the flow from a radial dimension (characteristic of centrifugal compressor discharge) to an axial dimension (required by the combustor) through the deswirl assembly. This dimensional transformation is achieved through carefully angled guide vanes that redirect the flow vector, enabling proper alignment between the two components.

Inventive Principle:

Principle #17Another dimension (Dimensionality change)

2Adaptability or versatility

If the flow direction changes from radial to axial, then compatibility with axial combustor is improved, but static pressure recovery is reduced

Engineering Contradiction:

Improvecombustor compatibilityVSAvoidstatic pressure recovery

Core Design Contradiction:

Adaptability or versatilityVSStress or pressure

Solution Approach 1:

The deswirl assembly modifies flow parameters (direction and velocity distribution) through its guide vanes while minimizing energy losses. The vanes are specifically designed to redirect flow at optimal angles that achieve axial alignment with the combustor while maintaining static pressure recovery, thus changing flow parameters in a controlled manner to satisfy both requirements.

Inventive Principle:

Principle #35Parameter changes

3Ease of operation

If a deswirl assembly is added to redirect flow, then flow alignment is improved, but device complexity increases

Engineering Contradiction:

Improveflow direction controlVSAvoidcompressor system complexity

Core Design Contradiction:

Ease of operationVSDevice complexity

Solution Approach 1:

The deswirl assembly is segmented into discrete guide vane elements arranged in a circumferential pattern. This segmentation allows the complex flow redirection function to be achieved through multiple simple, identical components rather than a single complex mechanism, making the system more manageable and easier to manufacture while maintaining effective flow control.

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 effectively conditions the airflow, minimizing losses and maximizing static pressure recovery, thereby enhancing the overall performance and efficiency of the gas turbine engine by ensuring proper alignment and flow directionality.

Implementation Method 1

The diffuser decreases the velocity and increases the static pressure of the air

Methodology Applied

Scientific EffectDiffusion: Diffusion

Implementation Method 2

the shroud directs the air radially outward into a diffuser. The diffuser decreases the velocity and increases the static pressure of the air and directs the air into a deswirl assembly, which straightens the flow of the air

Methodology Applied

Scientific EffectFlow straightening:

Data Source

PatentUS7500364B2System for coupling flow from a centrifugal compressor to an axial combustor for gas turbines

Publication Date: 2009.03.10 HONEYWELL INTERNATIONAL INC

AI summary

A system is provided for aerodynamically coupling air flow from a centrifugal compressor to an axial combustor. The system includes a diffuser, a deswirl assembly, combustor inner and outer annular liners, a combustor dome, and a curved annular plate. The diffuser has an inlet that communicates with the centrifugal compressor, an outlet, and a flow path that extends radially outward. The deswirl assembly has an inlet that communicates with the diffuser outlet to receive air flowing in a radially outward direction, an outlet, and a flow path configured to redirect the air in a radially inward and axial direction through the deswirl assembly outlet at an angle toward a longitudinal axis. The curved annular plate is coupled to combustor inner and outer annular liner upstream ends to form a combustor subplenum therebetween and has a first opening and a second opening formed therein, the first opening aligned with the deswirl assembly outlet to receive air discharged therefrom.