Variable Cycle Gas Turbine Intercooling Bypass
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Solution Overview
Problem
Variable cycle gas turbine engines face challenges in achieving high specific thrust and low fuel consumption across a range of operating conditions, particularly in optimizing fuel efficiency for cruise and loiter conditions while maintaining high thrust during high-energy maneuvers.
Innovation Solution
The design incorporates a variable cycle gas turbine engine with intercooling turbine sections and bypass paths that allow selective bypassing of core flow, enabling adjustments in bypass ratio to match operating conditions, thereby optimizing performance and efficiency.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If the bypass ratio is increased to optimize fuel efficiency for cruise conditions, then fuel consumption decreases, but the specific thrust and high-energy maneuver capability deteriorate
Solution Approach 1:
The engine employs variable cycle capability with adjustable bypass ratios through movable bypass doors and variable stator vanes, allowing the system to dynamically transition between high bypass ratio for fuel-efficient cruise and low bypass ratio for high-thrust maneuvers, resolving the contradiction between fuel efficiency and power output
Solution Approach 2:
The engine changes operational parameters including bypass ratio, compressor inlet temperature, and pressure ratio to optimize performance for different flight conditions, using intercooling turbine sections to control compressor inlet temperature and achieve optimal fuel efficiency across varying thrust requirements
2Use of energy by moving object
If the bypass ratio is increased to reduce fuel consumption during cruise, then fuel efficiency improves, but the device complexity increases due to additional bypass paths and control mechanisms
Solution Approach 1:
The bypass system serves multiple functions: it provides fuel-efficient cruise operation through high bypass ratio, enables high-thrust maneuvers through low bypass ratio, and contributes to intercooling of compressor inlet air. This multi-functionality justifies the added complexity by delivering multiple performance benefits from the same structural additions
Solution Approach 2:
The bypass system is divided into multiple independent bypass paths with individual control doors, allowing selective activation and optimization of different bypass routes for various operational conditions, which manages complexity through modular control while maintaining fuel efficiency benefits
3Use of energy by moving object
If intercooling turbine sections are added to increase pressure ratio and improve fuel efficiency, then thermodynamic efficiency improves, but the device complexity and manufacturing difficulty increase
Solution Approach 1:
The intercooling turbine sections are integrated within the existing engine core structure, with turbine blades nested within the compressor inlet ducting. This nesting approach allows the intercooling function to be added without requiring completely separate external systems, reducing manufacturing complexity while achieving improved thermodynamic efficiency
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 approach enhances thermodynamic efficiency and fuel efficiency during cruise conditions, increasing the pressure ratio and temperature ratio in compressor sections, leading to improved overall engine performance and reduced fuel consumption.
Implementation Method 1
a first intercooling turbine section upstream of said combustor section to receive said core flow along said core flow path
Implementation Method 2
a first intercooling turbine section bypass to selectively bypass at least a portion of said core flow through a first intercooling turbine section bypass path around said first intercooling turbine section
Implementation Method 3
increasing the pressure ratio and temperature ratio in compressor sections
Data Source
AI summary
A gas turbine engine includes an intercooling turbine section to selectively cool the core flow. An intercooling turbine section bypass is also included to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section.