Gas Turbine Compressor Particulate Offtake System
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Gas turbine engines operating in harsh conditions face damage and efficiency reduction due to ingested particulates, such as sand or ash, which block air flow, erode components, and reduce turbine efficiency.
Innovation Solution
A gas turbine engine design incorporating a compressor with a fluidic opening and a particulate offtake system, where a controller regulates a particulate offtake valve to expel ingested particulates during specific operational phases like takeoff and landing, reducing their impact on compressor and turbine components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Duration of action of stationary object
If the gas turbine engine operates in harsh conditions with particulate ingestion, then the engine can maintain continuous operation, but the turbine components suffer from erosion and blockage reducing efficiency and lifespan
Solution Approach 1:
The patent extracts harmful particulates from the engine system by providing a dedicated extraction path through the compressor casing. The fluidic opening and associated piping system remove particulates from the compressed air stream before they reach the turbine, thereby protecting turbine components from erosion and blockage while allowing continuous engine operation.
2Device complexity
If particulates are allowed to flow through the compressor and turbine, then the engine structure remains simple, but the turbine blades and vanes suffer from coating damage and efficiency losses
Solution Approach 1:
The patent introduces an intermediary particulate removal system between the compressor and turbine. This intermediary system includes a fluidic opening in the compressor casing that provides a separate extraction path for particulates, allowing them to be removed from the main airflow without requiring fundamental changes to the compressor or turbine structures.
3Reliability
If a particulate removal system is implemented, then turbine component protection is improved, but the compressor system complexity and additional components increase
Solution Approach 1:
The patent implements a multi-functional approach where the compressor casing serves dual purposes: maintaining compression function while incorporating a fluidic opening for particulate extraction. The system integrates particulate removal into the existing compressor structure rather than adding completely separate equipment, thereby protecting turbine components while minimizing overall system complexity.
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 particulate offtake system effectively reduces the impact of ingested particulates, increasing engine operation duration and efficiency by minimizing erosion and flow path blockages, thereby extending maintenance intervals and maintaining performance.
Implementation Method 1
The compressor rotors may naturally force air and the particulates into the fluidic opening due to centrifugal forces
Implementation Method 2
the fluidic opening is configured to receive the particulate flowing through the compressor and thereby redirect the particulate to a particulate offtake
Data Source
AI summary
In general, techniques are described by which to provide a turbine engine compressor particulate offtake. A gas turbine engine comprising a compressor may perform the techniques. The compressor may comprise a plurality of compressor stages, where each compressor stage comprises a circumferential row of stator vanes and a rotor. The compressor may also include an outer circumferential casing that defines a fluidic opening within or between adjacent compressor stages. The fluidic opening may be configured to receive particulate flowing and air through the compressor and output the particulate and air outside of the gas turbine engine. The gas turbine engine also includes a combustor in series flow downstream of the compressor, and a turbine in series flow downstream of the combustor.