Hybrid Compressor Axial-Centrifugal Stage Efficiency
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Solution Overview
Problem
Conventional gas turbine compressors face limitations in efficiency due to the nature of either axial or centrifugal designs, which can result in issues like wakes, separation, and diffusion, limiting performance gains.
Innovation Solution
A hybrid compressor design featuring a first compression stage mounted for rotation about a central axis with axial blading and a second stage mounted along the axis, featuring blades with an increasing radius to discharge air radially and then axially, supported by separate shafts, and including interstage vanes and diffusers to manage airflow effectively.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a conventional axial compressor design is used, then the compressor can compress air along a central axis with alternating stages of static and rotating assemblies, but it suffers from wakes, separation, and diffusion that limit efficiency improvements
Solution Approach 1:
The patent combines axial and centrifugal compressor designs into a hybrid system. The first compression stage uses axial-like blading for initial compression, while the second stage employs centrifugal impeller-like blades to further compress air radially outward. This merging of two different compression approaches allows the system to overcome the efficiency limitations of pure axial designs while avoiding the drawbacks of traditional centrifugal compressors.
2Loss of energy
If a conventional centrifugal compressor design is used, then the compressor can compress and discharge air in radial direction, but it lacks the efficiency improvements achievable with axial designs
Solution Approach 1:
The compressor is divided into two distinct compression stages with different functional characteristics. The first stage handles initial compression with axial-like blading, while the second stage performs radial compression with centrifugal impeller-like blades. This segmentation allows each stage to operate in its optimal efficiency range, with the axial stage handling the lower pressure ratio and the centrifugal stage handling the higher pressure ratio, thereby improving overall productivity.
3Ease of operation
If traditional radial exit design is used in centrifugal compressors, then air is discharged radially, but this limits the ability to achieve axial flow alignment for downstream components
Solution Approach 1:
The second compression stage uses centrifugal impeller-like blades that discharge air radially outward, but then incorporates a diffuser and outlet guide vanes that redirect the airflow to exit in the axial direction. This dimensional transition from radial discharge to axial exit allows the system to maintain the compression efficiency benefits of centrifugal design while achieving proper airflow alignment for downstream combustion components.
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 design enhances efficiency by managing airflow and reducing inefficiencies like wakes and separation, achieving improved performance by combining axial-like blading with a centrifugal impeller-like flow path and axial exit, rather than traditional radial exits.
Implementation Method 1
An axial compressor typically has alternating stages of static vane assemblies and rotating wheel assemblies that compress air moved along a central axis
Implementation Method 2
A centrifugal compressor typically includes a single rotor that is shaped to compress and discharge air in radial direction away from a central axis
Data Source
AI summary
A compressor for a gas turbine engine is disclosed. The compressor includes a first compression stage mounted for rotation about a central axis that includes a plurality of first-stage blades. The compressor also includes a second compression stage mounted along the central axis aft of the first compression stage to receive air compressed by the first compression stage. The second compression stage includes a plurality of second-stage blades.