Translating Inlet Adjusting Airflow Distortion Gas Turbine
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Solution Overview
Problem
Gas turbine engines face airflow distortion issues upstream of the compressor section, leading to potential stall conditions due to uneven airflow, which can reduce engine efficiency and operability.
Innovation Solution
A translating inlet assembly is integrated into the gas turbine engine's core casing, allowing for real-time adjustment of airflow by varying the inlet area and airflow speed through the compressor section based on distortion conditions, using pressure sensing devices to assess and control airflow distortion.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If variable guide vanes are closed to maintain stall margin, then compressor stall conditions are prevented, but overall engine efficiency decreases
Solution Approach 1:
The inlet assembly is made dynamically adjustable between fixed and translated positions, allowing the system to adapt its configuration based on operating conditions. This enables the inlet area to be optimized for each flight regime, preventing the need to permanently restrict flow via closed guide vanes.
Solution Approach 2:
The physical position of the inlet assembly is changed to alter the inlet flow area parameter. By translating the inlet assembly axially, the effective inlet area is modified to match required airflow conditions, thereby maintaining optimal compressor inlet parameters without energy loss from restricted guide vanes.
2Reliability
If inlet area is reduced to prevent stall, then compressor operability is improved, but airflow distortion increases
Solution Approach 1:
The translating inlet assembly can be positioned to provide locally optimized flow areas at different axial locations. This allows differential flow management across the inlet, addressing distortion in specific regions while maintaining overall compressor operability.
Solution Approach 2:
The inlet configuration is dynamically adjusted based on real-time distortion conditions, allowing the system to respond to changing airflow patterns and maintain uniform distribution across the compressor face under varying flight conditions.
3Device complexity
If fixed inlet configuration is used, then device complexity is reduced, but adaptability to different flight conditions deteriorates
Solution Approach 1:
The inlet assembly transitions from a fixed to a movable configuration, enabling adaptation to different flight conditions. The translating mechanism allows the inlet to reposition axially based on distortion sensor feedback, providing versatility without requiring multiple discrete inlet components.
Solution Approach 2:
The system uses onboard distortion sensors and control logic to automatically adjust the inlet position based on measured airflow conditions, enabling self-regulation and adaptation without external intervention or complex manual control systems.
Data Source
AI summary
Systems and methods for adjusting airflow distortion in a gas turbine engine using a translating inlet assembly are provided. In one embodiment, a core engine of a gas turbine engine can include a compressor section, a combustion section, and a turbine section in series flow and defining at least in part an engine airflow path. The compressor section can include an inner flowpath surface. A core casing can enclose the core engine. A forward end of the core casing can include a translating inlet assembly moveable between a first position and a second position. The translating inlet assembly and the inner flowpath surface can together define an inlet to an engine airflow path. A translating inlet assembly can define a first inlet area in the first position and a second inlet area in the second position, the first inlet area being greater than the second inlet area.