Combined cycle method and installation of combustion turbine of burning blast furnace gas

A gas turbine and combined cycle technology, which is used in the fuel delivery and charging systems of gas turbine units and turbine/propulsion units to widen the stable operation area, improve the operating efficiency of variable working conditions, and save auxiliary systems.

Inactive Publication Date: 2008-02-13
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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Problems solved by technology

But on the other hand, some problems have been exposed in terms of structural integrity and optimization of economic effects: 1) my country has not fully mastered the design technology of heavy-duty gas turbines, and the units currently operating in large iron and steel enterprises in my country are all four major foreign companies Technically, these companies have strictly blocked us, which requires us to further improve the efficiency and operational reliability of these units, and even the units that are about to start construction, on the premise of changing the structural parameters of these units in a small range; 2 ) The unit currently operating in Jinan Iron and Steel Works, in order to increase the calorific value of the fuel gas, burns part of the coke oven gas, and the coke oven gas has a wider use in the steel plant. On the other hand, if it is not mixed with the blast furnace Gas, turbine capacity and compressor surge problems will appear again

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  • Combined cycle method and installation of combustion turbine of burning blast furnace gas

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Embodiment Construction

[0015] Using the low calorific value combustor technology of the gas turbine combustor of the Institute of Engineering Thermophysics, Chinese Academy of Sciences, the lower limit of the calorific value of the combustor is locked at 800Kcal / Nm 3 , using the nozzle burning coke oven gas [accounting for 1% of the fuel gas flow] as the on-duty flame, it greatly expands the flameout limit at low load and increases the temperature of the adiabatic flame, so that the combustion efficiency of low calorific value fuel can reach 98% at high load, and at the same time Considering the compressor surge and the passing capacity of the turbine, on the basis of the original number of combustion chambers [main combustion chambers], several combustion chambers [auxiliary combustion chambers] are added, and the gas burned in the auxiliary combustion chambers is led to the low-flow area. The centripetal turbine is connected in series with the first steam turbine formed by the dual-pressure waste h...

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Abstract

A method for unitedly circulating gas turbine utilizing furnace gas includes making cleaned furnace gas be the same pressure grade as air at last stage exit on multistage axial-flow compressor by gas compressor, using said gas as fuel to be inputted to two combustion clamber connected in parallel means and burning said gas with high pressure air provided by multistage axial-flow compressor these for providing a partial power to gas compressor through radial-inward-flow turbine, sending high temperature smoke from said turbine to double-pressure residual-heat boiler for carrying heat exchange these then providing the second partial power to gas compressor through the first steam turbine.

Description

technical field [0001] The invention relates to the technical field of steelmaking, and relates to a combined cycle method and device for burning blast furnace gas and gas turbines. Background technique [0002] The transformation of heavy-duty gas turbines that burn natural gas into blast furnace gas-fired units is now facing a major technical bottleneck. The flow matching of the compressor-combustion chamber-turbine has a structural problem that is difficult to overcome, mainly because of the heat of the fuel gas. The value has reached the minimum limit. Under the original design operating conditions, that is, under the premise of ensuring the same heat output from the combustion chamber, the fuel gas volume is increased several times, that is, the blast furnace gas volume entering the combustion chamber. The increase of these quantities almost reaches the compressor inflow one-third of the combustion chamber. If the unit does not reduce the flow rate of the compressor, t...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C6/00F02C7/236
Inventor 聂超群徐纲肖云汉黄伟光
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI
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