Turbine Engine Assembly With Isochoric-Isobaric Combustion Staging
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Existing turbomachines face challenges in reducing specific fuel consumption and component mass while minimizing increases in mass and aerodynamic drag, which are partly due to suboptimal thermodynamic cycles.
Innovation Solution
Incorporating an isochoric combustion chamber with an intake and discharge valve system, an isobaric combustion chamber, and a turbine configuration that allows for combustion at constant volume, enhancing combustion efficiency and thermal efficiency by controlling fluid flow and fuel injection within the turbomachine.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If combustion is performed at constant pressure in an isobaric combustion chamber, then the combustion process is simple and continuous, but the thermal efficiency is lower compared to isochoric combustion
Solution Approach 1:
The combustion process is divided into two distinct stages: first isochoric combustion in a closed chamber with valves to achieve high thermal efficiency, then isobaric combustion in a separate chamber for continuous operation. This segmentation allows each combustion type to optimize its own efficiency while maintaining overall system performance.
Solution Approach 2:
The isochoric combustion chamber operates periodically with intake and discharge valves that open and close in sequence, allowing the system to alternate between constant-volume combustion (for efficiency) and constant-pressure combustion (for continuity). This periodic valve operation enables the turbomachine to achieve high thermal efficiency while maintaining steady power output.
2Loss of energy
If the fan pressure ratio is lowered to improve propulsive efficiency, then the propulsive efficiency increases, but the compression ratio decreases and more compression stages are needed
Solution Approach 1:
The invention changes the thermodynamic parameters of the combustion process by implementing isochoric combustion with controlled valve timing. This allows optimization of the compression ratio and combustion temperature independently, enabling the fan pressure ratio to be lowered for improved propulsive efficiency without compromising overall compression requirements.
Solution Approach 2:
Different parts of the combustion system are optimized for different functions: the isochoric chamber optimizes thermal efficiency through constant-volume combustion, while the isobaric chamber maintains continuous flow. This local optimization allows the fan stage to operate at lower pressure ratios for improved propulsive efficiency while the combustion system compensates to maintain overall performance.
3Loss of energy
If the compression ratio is increased to improve thermal efficiency, then the thermal efficiency increases, but the mass of the compressor increases
Solution Approach 1:
The system dynamically switches between isochoric and isobaric combustion modes using controllable valves. The isochoric mode provides high thermal efficiency with a smaller effective compression ratio, reducing compressor mass requirements. The system adapts the combustion process to achieve high efficiency without requiring excessive compression hardware.
Solution Approach 2:
The isochoric combustion chamber performs preliminary combustion at constant volume before the main isobaric combustion stage. This preliminary action achieves a portion of the required temperature rise efficiently, reducing the workload on the compressor and allowing for lighter compressor design while maintaining high thermal 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
The solution reduces specific fuel consumption and improves thermal efficiency by optimizing combustion processes, leading to a more efficient and lighter turbomachine design.
Implementation Method 1
an isochoric combustion chamber configured to receive a fluid from the compressor, the isochoric combustion chamber being the seat of a combustion at constant volume
Implementation Method 2
an isobaric combustion chamber configured to receive a fluid discharged from the isochoric combustion chamber
Implementation Method 3
a turbine configured to receive fluid from the isobaric combustion chamber
Data Source
Figure 1~2
Figure 3
Figure 4
AI summary
The present invention relates to an assembly for a turbomachine (1) comprising: a compressor (30), an isochoric combustion chamber (7), an isobaric combustion chamber (40), and a turbine (50).