Segmented Inertial Particle Separator for Turbine Engine Drag Reduction
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Solution Overview
Problem
Existing inertial particle separators in gas turbine engines are inadequate in separating smaller sand and dust particles, leading to performance losses and increased maintenance, and are not suitable for severe conditions or icing scenarios due to their bulky design and pressure drop issues.
Innovation Solution
A segmented inertial particle separator with a scroll vane and scavenge blower system that channels dirty fluid into a separate path, using a segmented angle design to fit flush against the aircraft fuselage, reducing drag and enhancing separation efficiency while maintaining engine performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If known inertial particle separator systems are used to remove sand and dust particles, then separation efficiency is improved, but inlet pressure losses increase that detrimentally affect gas turbine engine performance
Solution Approach 1:
The inertial particle separator is divided into multiple segments arranged radially around the engine inlet, with each segment containing a scroll vane and scavenge blower. This segmentation allows the system to achieve effective particle separation while maintaining a compact configuration that minimizes pressure losses. The segmented design distributes the separation function across multiple smaller units rather than requiring a single large separator.
Solution Approach 2:
The invention transitions from conventional linear or axial separator designs to a radial configuration where scroll vanes create rotational flow patterns. By utilizing rotational motion in the radial dimension, the system imparts centrifugal forces that enhance particle separation efficiency while maintaining a compact footprint that reduces inlet pressure losses.
2Reliability
If IPS systems with improved separation efficiency are used, then smaller sand and dust particles are removed more effectively, but the system requires more length and diameter than is available in contemporary helicopters
Solution Approach 1:
The separator is divided into multiple radial segments that can be arranged within the limited space available on helicopter engines. Each segment contains a scroll vane and scavenge blower, allowing the system to achieve effective separation of smaller particles without requiring excessive length or diameter. The modular segmented design adapts to compact engine installations.
Solution Approach 2:
The scroll vanes are positioned within the inlet structure itself, nesting the separation function within the existing engine geometry. The scavenge blowers are integrated into the segmented structure, allowing multiple functional elements to occupy overlapping or adjacent spaces, thereby reducing the overall system volume required.
3Reliability
If barrier filters are used to address severe sand conditions, then sand and dust removal is effective, but the filters are heavy, cause pressure drop at the inlet, and require increased maintenance
Solution Approach 1:
The invention replaces the mechanical filtration system with an inertial separation system using scroll vanes and scavenge blowers. Instead of relying on physical filters that trap particles, the system uses rotational flow patterns and centrifugal forces to separate particles from the air stream, eliminating the need for heavy filter media while maintaining effective sand and dust removal.
Solution Approach 2:
The system uses pneumatic principles by employing scavenge blowers to create negative pressure that draws particles into the scroll vanes for separation. The rotational airflow patterns generated by the scroll vanes utilize aerodynamic forces to separate particles based on their inertia, replacing mechanical filtration with a pneumatic-inertial separation mechanism that is lighter and requires less maintenance.
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 solution effectively removes sand and dust particles, reducing engine maintenance and performance losses, and allows operation in various weather conditions without causing significant pressure drops, thus enhancing engine reliability and efficiency.
Implementation Method 1
Inertial inlet particle separators work by imparting momentum and trajectory on sand and dust particles to channel such particles away from the fluid stream entering the gas turbine engine
Implementation Method 2
The system uses pneumatic principles by employing scavenge blowers to create negative pressure that draws particles into the scroll vanes for separation
Implementation Method 3
The rotational airflow patterns generated by the scroll vanes utilize aerodynamic forces to separate particles based on their inertia
Data Source
AI summary
A method for assembling a turbine engine including a compressor is disclosed. The method includes coupling an inlet including an inertial particle separator (IPS) and a first surface that is defined using a segment angle, to a gas turbine engine, and coupling the first surface substantially flush against a fuselage of an aircraft to reduce drag.