Ported Compressor Impeller With Swept Leading Edge for Flow Separation
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Solution Overview
Problem
Gas turbine engines experience efficiency losses due to flow separation and pressure loss at the leading edge of impellers, particularly in radial compressors, which affects the overall performance of the compressor and downstream components.
Innovation Solution
A ported compressor with a partially swept leading edge is introduced, featuring an impeller blade design that extends in a streamwise direction from the leading edge to the trailing edge, with a sweep that reduces material at the tip, improving airflow management and reducing flow separation.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Ease of manufacture
If a traditional impeller with axial entry is used, then the结构简单 (structure is simple), but flow separation occurs at the leading edge causing pressure loss and reduced efficiency
Solution Approach 1:
The leading edge of the impeller blade is given a swept-back geometry specifically at the tip region, while the root region maintains a more traditional configuration. This local modification creates different flow characteristics at different spanwise locations, reducing flow separation and pressure loss at the leading edge without requiring a complete redesign of the entire impeller structure.
2Loss of energy
If the leading edge is fully swept back, then flow separation is reduced, but the blade span is reduced which may affect the energy addition to the fluid
Solution Approach 1:
Instead of sweeping back the entire leading edge of the impeller blade, the invention applies swept-back geometry only to a portion of the blade span, specifically targeting the tip region where flow separation is most problematic. This partial application of the swept leading edge concept achieves the beneficial effect of reduced flow separation while preserving sufficient blade span for effective energy addition to the fluid.
3Productivity
If compressor efficiency is increased through design modifications, then performance improves, but device complexity increases
Solution Approach 1:
The invention modifies only the leading edge region of the impeller blade with swept-back geometry, while keeping the rest of the blade and the overall impeller structure relatively simple. This localized geometric modification achieves improved compressor efficiency (0.4% to 0.8% increase) and enhanced stall margin (1% to 7% improvement) without requiring complex redesign of the entire compressor system.
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
The partially swept leading edge enhances compressor efficiency by 0.4% to 0.8%, improves stall margin by 1% to 7%, and increases total pressure ratio by 1%, while reducing diffusion losses and improving choke flow capacity by 1% to 2%.
Implementation Method 1
The leading edge of the impeller experiences axial entry of a high flow velocity fluid, which may lead to flow separation along the impeller. The flow separation may result in pressure loss.
Data Source
AI summary
A compressor section for a gas turbine engine includes an inlet duct, a port plenum, and an impeller. The port plenum has a port inlet and a port outlet. The port inlet is in fluid communication with the inlet duct. The impeller includes a hub, a shroud, and an impeller blade. The impeller blade extends for a span that is 0% at the hub and 100% at a tip. The impeller blade has a partially swept leading edge and extends in a streamwise direction from the partially swept leading edge to a trailing edge. The partially swept leading edge of the impeller blade is in fluid communication with the inlet duct. The port outlet is defined through the shroud. The partially swept leading edge extends in the streamwise direction at the tip upstream of the port outlet for a distance.