Gas Turbine Engine Heat Exchange via Turbine Casing
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Solution Overview
Problem
Conventional gas turbine engines face inefficiencies due to the need for dedicated devices like heat exchangers, which increase weight, complexity, and cost, while also causing pressure losses and noise.
Innovation Solution
A gas turbine engine design that enables heat exchange between compressed air and heated fluid flows at different temperatures within the turbine section, using a configuration with dual groups of stator channels and rotor blades to preheat the air without additional devices, maximizing commonality and reuse of components.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Use of energy by moving object
If a heat exchanger is added to improve thermal efficiency, then fuel efficiency improves, but weight increases
Solution Approach 1:
The patent merges the heat exchanger function with the turbine structure by configuring the turbine casing to include a heat exchanger section. The turbine outer casing is designed with a first section and a second section, where the heat exchanger is integrated into the casing structure itself, allowing heat transfer between the turbine workflow and compressor outlet air without requiring a separate heat exchanger component.
Solution Approach 2:
The turbine casing serves multiple functions: it contains the turbine blades and workflow passage, provides structural support, and simultaneously acts as the heat exchanger housing. The outer casing of the turbine performs both mechanical containment and thermal exchange functions, eliminating the need for dedicated heat exchanger components.
2Use of energy by moving object
If a heat exchanger is added to improve thermal efficiency, then fuel efficiency improves, but device complexity increases
Solution Approach 1:
The heat exchanger functionality is merged into the turbine casing structure. The turbine outer casing includes a heat exchanger section that utilizes the existing turbine workflow and compressor outlet air passages, eliminating the need for separate heat exchanger components and reducing overall system complexity.
Solution Approach 2:
The turbine casing is designed to perform multiple functions simultaneously: mechanical containment of turbine components, structural support, and thermal exchange. This multi-functionality reduces the number of separate components needed and simplifies the overall engine architecture.
3Use of energy by moving object
If a heat exchanger is added to improve thermal efficiency, then fuel efficiency improves, but pressure losses increase
Solution Approach 1:
The heat exchanger is positioned to receive compressor outlet air before it enters the combustion chamber, preheating the air in advance. This preliminary heating action occurs using waste heat from the turbine workflow, reducing the energy required for combustion and minimizing pressure losses in the overall system.
Solution Approach 2:
The heat exchanger acts as an intermediary between the turbine workflow and the compressor outlet air. It transfers thermal energy from the hot turbine exhaust to the cooler compressed air, enabling efficient heat recovery without creating significant pressure drops in either workflow.
4Use of energy by moving object
If a heat exchanger is added to improve thermal efficiency, then fuel efficiency improves, but cost increases
Solution Approach 1:
The heat exchanger function is combined with the turbine casing, eliminating the need for separate heat exchanger components. This integration reduces the number of parts that need to be manufactured, assembled, and maintained, thereby reducing overall manufacturing cost despite improved fuel efficiency.
Solution Approach 2:
The turbine casing serves multiple functions including structural support, mechanical containment, and thermal exchange. This multi-functionality reduces the total component count and manufacturing complexity, lowering production costs while achieving the thermal efficiency benefits of a heat exchanger.
5Use of energy by moving object
If a heat exchanger is added to improve thermal efficiency, then fuel efficiency improves, but noise increases
Solution Approach 1:
The heat exchanger is integrated into the turbine casing structure, utilizing existing engine components and workflows. This integration avoids the need for separate heat exchanger housings and associated noise-generating elements, reducing overall noise levels while maintaining thermal efficiency improvements.
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 design enhances thermal efficiency, reduces weight and maintenance costs, minimizes pressure losses, and decreases noise by integrating heat exchange within the engine, thereby improving overall performance and reducing fuel consumption.
Implementation Method 1
heat exchange between compressed air and heated fluid flows at different temperatures within the turbine section
Implementation Method 2
heat exchange between compressed air and heated fluid flows at different temperatures within the turbine section, using a configuration with dual groups of stator channels and rotor blades to preheat the air
Data Source
AI summary
A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.