Dual-Compressor Fuel Supply System for Gas Turbine Startup
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Solution Overview
Problem
Gas turbine systems face challenges in achieving sufficient fuel pressure during startup due to low shaft speed, leading to inadequate fuel supply to the combustor, which can hinder the initiation of the gas turbine operation.
Innovation Solution
A dual-compressor fuel supply system where a motor-driven fuel gas compressor and a shaft-driven fuel gas compressor are serially connected to ensure a consistent and elevated fuel pressure is maintained, with the motor-driven compressor taking over during startup and the shaft-driven compressor supplementing once the gas turbine reaches operational speed.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Device complexity
If a single shaft-driven fuel gas compressor is used, then the device complexity is reduced, but the fuel pressure is insufficient during startup due to low shaft speed
Solution Approach 1:
The fuel gas compression system is segmented into two independent compressors: a motor-driven fuel gas compressor and a shaft-driven fuel gas compressor. This segmentation allows each compressor to operate independently, with the motor-driven compressor providing sufficient fuel pressure during startup when shaft speed is low, and the shaft-driven compressor taking over or supplementing when the gas turbine reaches operational speed, thus resolving the contradiction between device complexity and fuel pressure sufficiency
Solution Approach 2:
The motor-driven fuel gas compressor acts as an intermediary device that provides the necessary fuel pressure during the startup phase when the shaft-driven compressor cannot provide sufficient pressure due to low shaft speed. This intermediary compressor bridges the gap between the unavailable shaft power during startup and the required fuel pressure for combustor operation
2Stress or pressure
If a motor-driven fuel gas compressor is added to ensure sufficient fuel pressure during startup, then the fuel pressure is improved, but the device complexity increases
Solution Approach 1:
The system dynamically transitions between different compressor configurations: during startup, the motor-driven compressor operates independently to provide sufficient fuel pressure; once the gas turbine reaches operational speed, the shaft-driven compressor supplements or takes over the fuel compression duty. This dynamic operation allows the system to adapt to varying operational conditions, providing sufficient fuel pressure when needed while minimizing the perceived complexity through coordinated operation
Solution Approach 2:
The dual-compressor system provides multi-functionality: the motor-driven compressor serves as the primary fuel pressure source during startup and can also operate in conjunction with the shaft-driven compressor during normal operation. This universal capability of the system to handle both startup and steady-state operations with adequate fuel pressure justifies the added complexity by delivering superior operational flexibility and 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 ensures reliable and elevated fuel pressure to the combustor, facilitating smooth startup and operation of the gas turbine system by leveraging the high-speed capability of the motor-driven compressor and the operational capacity of the shaft-driven compressor.
Implementation Method 1
a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system. The first fuel gas compressor and the second fuel gas compressor are configured to supply a pressurized fuel flow to a combustor
Implementation Method 2
a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system. The first fuel gas compressor and the second fuel gas compressor are configured to supply a pressurized fuel flow to a combustor
Data Source
AI summary
A fuel supply system is provided having a first fuel gas compressor configured to be driven by a motor and a second fuel gas compressor configured to be driven by a shaft of a gas turbine system. The first fuel gas compressor and the second fuel gas compressor are configured to supply a pressurized fuel flow to a combustor of the gas turbine system, and the first fuel gas compressor and the second fuel gas compressor are coupled to one another in series.