Reverse Flow Gas Turbine Core with Radial Mixing Lobes
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Solution Overview
Problem
Conventional gas turbine engines face limitations in optimizing thrust and propulsion efficiency due to the traditional alignment of components, which can restrict the mixing of combustion products with bypass airflow, leading to suboptimal propulsion performance.
Innovation Solution
A reverse flow core engine configuration is introduced, where air flows through a turbine section, combustor, and compressor in series, with a turning exhaust duct radially mixing combustion products with bypass air through circumferentially spaced mixing lobe outlets, allowing for additional propulsion via a selectively opening door that diverts core airflow for enhanced thrust.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Productivity
If traditional component alignment is used (fan, compressor, combustor, turbine in sequence), then structural simplicity is maintained, but propulsion efficiency and thrust optimization are limited due to restricted mixing of combustion products with bypass airflow
Solution Approach 1:
The patent inverts the traditional component arrangement by placing the turbine section upstream of the combustor and compressor, creating a reverse flow path. This inversion allows combustion products to mix with bypass airflow more effectively, improving propulsion efficiency while accepting increased structural complexity
Solution Approach 2:
The patent introduces radial mixing lobes that extend circumferentially from the core engine, adding a radial dimension to the flow mixing process. This dimensional change enables 360-degree mixing of combustion products with bypass air, significantly enhancing thrust optimization
2Productivity
If reverse flow configuration with radial mixing lobes is implemented, then mixing of combustion products with bypass air is enhanced over 360 degrees, but device complexity increases
Solution Approach 1:
The mixing structure is segmented into multiple discrete radial mixing lobes that are circumferentially spaced around the core engine. Each lobe independently facilitates mixing at different angular positions, achieving comprehensive 360-degree mixing while allowing modular construction and 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
This configuration enhances propulsion efficiency by effectively mixing combustion products with bypass air over 360 degrees, providing additional thrust while balancing the impact on core engine airflow, thus optimizing thrust and propulsion performance.
Implementation Method 1
An exhaust turning duct communicates products of combustion from a downstream portion of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets, to mix with the bypass air in the bypass duct
Data Source
AI summary
A gas turbine engine has a fan rotor for delivering air into a bypass duct and into a core airflow duct. Air in the core flow duct passes axially downstream from the fan and past a reverse core engine including a turbine section, a combustor section, and a compressor section. The core airflow duct reaches a turning duct which turns the airflow radially inwardly to communicate with an inlet for the compressor section. Air in the compressor section passes to the combustor section. Products of the combustion pass downstream across a turbine rotor. An exhaust turning duct communicates products of the combustion from a full cylindrical portion downstream of the turbine rotor through a plurality of circumferentially separated mixing lobe outlets to mix with the bypass air in the bypass duct. The bypass duct extends past the mixing lobe outlets, and is defined circumferentially intermediate the mixing lobe outlets.