Gas Turbine Heat Management System with Segmented Cooling
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Geared gas turbine engines, particularly those with lean burn combustors, face challenges in managing heat generated by power gearboxes and turbomachinery bearings, leading to energy waste and potential fuel thermal degradation, while existing heat management systems are inefficient in dissipating heat without incurring fuel degradation.
Innovation Solution
A gas turbine engine with a heat management system that includes a pipe assembly for lubricant flow and both air-lubricant and fuel-lubricant heat exchangers, configured to dissipate specific proportions of heat to air and fuel, optimizing heat dissipation to minimize energy waste and ensure effective cooling under various operating conditions.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If heat is dissipated to fuel, then energy efficiency is improved, but fuel thermal degradation occurs
Solution Approach 1:
The heat dissipation function is segmented into two independent pathways: one for air cooling and one for fuel cooling. This allows selective routing of heat to appropriate sinks based on engine operating conditions, preventing fuel degradation while maintaining energy efficiency.
Solution Approach 2:
The system dynamically adjusts the distribution of heat dissipation between air and fuel sinks based on real-time operating conditions. The control system monitors parameters such as fuel temperature, engine load, and ambient conditions to optimally allocate heat removal pathways.
2Object-affected harmful factors
If heat is dissipated to air, then fuel thermal degradation is prevented, but energy efficiency deteriorates
Solution Approach 1:
The heat dissipation function is segmented into two independent pathways: one for air cooling and one for fuel cooling. This allows selective routing of heat to appropriate sinks based on engine operating conditions, preventing fuel degradation while maintaining energy efficiency.
Solution Approach 2:
The system changes operational parameters (heat dissipation distribution) based on engine conditions. During ground operations or low-speed flight where fuel degradation risk is high, more heat is routed to air. During high-speed cruise where fuel is actively consuming, more heat is routed to fuel to improve efficiency.
3Temperature
If heat dissipation capacity is increased, then cooling effectiveness is improved, but device complexity increases
Solution Approach 1:
The lubricant cooling system serves multiple functions: it cools the gearbox, lubricates bearings, and acts as a heat transport medium to two different sinks. This multi-functionality reduces the need for separate cooling systems for each component, thereby limiting complexity increase.
Solution Approach 2:
The lubricant acts as an intermediary heat transport medium between the heat sources (gearbox, bearings) and the two heat sinks (air and fuel). This intermediary approach allows flexible heat routing without requiring direct thermal coupling between all components, simplifying the overall system architecture.
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 system effectively minimizes energy waste, improves Specific Fuel Consumption (SFC), and provides adequate cooling to engine components, maintaining efficient operation across all conditions without fuel degradation.
Implementation Method 1
at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink
Implementation Method 2
at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink
Data Source
AI summary
A gas turbine engine for an aircraft includes: an engine core including a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor, wherein the core shaft has a core shaft maximum take-off speed in the range of 5500 rpm to 9500 rpm, preferably in the range of 5500 rpm to 8500 rpm; a fan; turbomachinery bearings; a power gearbox adapted to drive the fan at a lower rotation speed than the turbine; and a heat management system configured to provide lubrication and cooling to the gearbox and turbomachinery bearings, and including a pipe assembly adapted to provide a lubricant flow to the gearbox and turbomachinery bearings, at least one air-lubricant heat exchanger to dissipate a first amount of heat to a first heat sink, and at least one fuel-lubricant heat exchanger to dissipate a second amount of heat to a second heat sink.