Parallel Dual Turbo Engine System for Hydrogen Combustion
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Solution Overview
Problem
Hydrogen internal combustion engines face challenges with high lambda values and low residual gases, leading to issues with back pressure and peak cylinder pressure, which traditional turbo systems struggle to address effectively.
Innovation Solution
The implementation of a dual turbo arrangement system with individually controllable turbines and compressors, controlled by a processor device to maintain compressor map positions away from the surge line, combined with a secondary air pressure arrangement for enhanced boosting and NOx reduction.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Quantity of substance
If a traditional free floating turbo system is used to achieve high lambda value, then the lambda value is improved, but back pressure increases and residual gases problems occur
Solution Approach 1:
The patent divides the single turbo system into two separate turbo arrangements operating in parallel. Each turbo arrangement has its own turbine and compressor, allowing independent control of each compressor's operation. This segmentation enables the system to achieve high lambda values while distributing the compression workload, thereby reducing back pressure compared to a single turbo system operating at high capacity.
2Device complexity
If a single turbo arrangement is used, then the device complexity is reduced, but the ability to maintain compressor map positions away from surge line is compromised
Solution Approach 1:
The patent implements dynamic control of the dual turbo arrangements through a processor device that continuously monitors compressor map positions and adjusts each turbo arrangement's rotational speed accordingly. This dynamic adjustment capability allows the system to maintain compressors away from the surge line under varying operating conditions, significantly improving reliability compared to a static single turbo system.
Solution Approach 2:
The control system incorporates feedback mechanisms where the processor device determines the current compressor map position based on measured pressure and mass flow, compares it with the surge line position, and adjusts the turbo arrangement rotational speed to maintain an optimal safety margin. This closed-loop feedback control ensures reliable surge avoidance while managing system complexity.
3Reliability
If parallel turbo arrangements are used, then surge risk control is improved, but the device complexity increases
Solution Approach 1:
The patent employs two turbo arrangements that are fundamentally identical in structure and function, both comprising a turbine operably connected to a compressor. This universality allows the system to leverage the same proven design for surge control while distributing functionality across two units. The identical architecture simplifies manufacturing and maintenance compared to using fundamentally different system configurations, thereby managing complexity while improving reliability.
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 improves engine efficiency by reducing surge risks, achieving high lambda levels with low residual gases and potentially eliminating the need for NOx reduction catalysts, while maintaining efficient operation and reducing NOx emissions.
Implementation Method 1
a first turbo arrangement (102, 202) comprising a first turbine (106, 206) and a first compressor (110, 210) operably connected to each other
Implementation Method 2
a first pressure (p1) and a first mass flow (m1) of air pressurized by the first compressor (110, 210)
Data Source
AI summary
An engine system for a vehicle is provided. The engine system includes a first and a second turbine arrangement arranged in parallel with each other. A rotational speed of a first turbo arrangement is controlled in response to a distance between a first compressor map position and a surge line of a compressor map being below a predetermined threshold distance.