Axial Compressor Rotor with Splitter Blades for Hub Flowpath
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Solution Overview
Problem
Turbomachinery compressors face challenges in achieving a balance between aerodynamic and structural performance due to non-axisymmetric scalloped surface profiles, which increase rotor blade row flow area and aerodynamic loading, leading to airflow separation.
Innovation Solution
Incorporating axial-flow compressor blades with splitter blades that have reduced span and chord dimensions, positioned between compressor blades to maintain solidity and prevent flow separation, while minimizing surface area and frictional losses.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Strength
If a non-axisymmetric scalloped surface profile is used on the disk, then mechanical stresses in the disk are reduced, but the rotor blade row through flow area increases and aerodynamic loading level increases promoting airflow separation
Solution Approach 1:
The rotor blade row is segmented into compressor blades and splitter blades alternating around the disk. The splitter blades are positioned in the gaps between compressor blades to locally increase solidity and prevent airflow separation without requiring a complete increase in all blade dimensions.
Solution Approach 2:
The splitter blades are strategically positioned only in specific locations (between compressor blades) where airflow separation occurs, rather than uniformly increasing all blade surfaces. This localized approach prevents flow separation while minimizing overall aerodynamic loading increases.
2Productivity
If the number of compressor stages is reduced to achieve higher pressure ratio, then thermodynamic cycle efficiency is improved, but aerodynamic limits to maximum pressure ratio and mass flow are encountered
Solution Approach 1:
The splitter blades are designed with variable dimensions along their span, being larger near the hub and smaller toward the tip. This dynamic sizing optimizes the blade's ability to prevent flow separation across different radial positions, enabling higher pressure ratios without compromising aerodynamic stability.
Solution Approach 2:
The invention changes the geometric parameters of the splitter blades (chord dimension, span dimension) to optimize performance. By controlling these parameters, the design achieves higher pressure ratios while maintaining acceptable aerodynamic characteristics and preventing flow separation.
3Loss of energy
If splitter blades with reduced span and chord dimensions are used, then frictional losses are minimized, but the ability to prevent flow separation may be compromised
Solution Approach 1:
The splitter blades use partial action by having reduced span and chord dimensions compared to full compressor blades. This partial sizing reduces frictional losses while still providing sufficient solidity to prevent flow separation in the critical hub region, accepting that not all blade surfaces need full dimensions to achieve the desired effect.
Data Source
AI summary
A compressor apparatus includes: a rotor including: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface having an non-axisymmetric surface profile; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; and wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.