SU935638A1 - System for starting gas pumping gas turbine unit - Google Patents

Description

I

The invention relates to power plant construction, in particular, to systems for starting gas turbine gas pumping units.

A gas turbine engine starting system is known, comprising a starting hydraulic motor connected through an overrunning clutch to the rotor of a turbocharger and provided with an input line to the output of an electric drive pump and collectors connected to the fuel supply line connected to the starting and working nozzles tn.

The gas turbine launching system is known, the bin pumping unit is not effective, since when it is required, the power required for spin-up compared to gas turbine engines requires special liquid working medium.

Closest to the present invention is the gas turbine gas pumping unit launch system.

A launch system comprising a starting turbo-expander connected via an overrunning clutch to the rotor of the turbocharger and connected to the outlet line to the atmosphere, and the inlet to a high-pressure gas pipeline connected to the manifolds of the starting and fuel gas of the combustion commers of the turbo-compressor 2.

However, such a launch system

10 does not provide the required level of economy and protection of the surrounding atmosphere due to the release of exhaust gas in the turbo-expander to the atmosphere, as well as due to the significant throttling of high-pressure gas before it is supplied to the collectors.

The purpose of the invention is to increase efficiency and reduce pollution of the surrounding atmosphere.

20

Claims (2)

This goal is achieved by the fact that the system is equipped with an ejector, the high-pressure nozzle of which is connected to the gas pipeline, low-pressure to the output line, and the output is connected to the collectors. The drawing shows schematically the launch system of a gas turbine gas pumping unit. The launch system contains a turbo-expander 1, connected via an overrunning clutch 2 to the rotor 3 of the turbo-compressor of the gas turbine installation, and connected to the outlet line 5 with atmosphere, and the inlet line 6 equipped with a regulated valve U to the high-pressure gas line 8 downstream of the supercharger 9 and connected to the gas pipeline 8 pipe, pipe 10 with an adjustable valve 11 collectors 12 and 13 starting and fuel gas of the combustion chamber 14 of the turbocharger. In the output line 5, a valve 15 is installed and the starting system is equipped with an ejector 16, a high-pressure nozzle 17,. which is connected to the pipeline 8 behind the valve 11, a low-pressure nozzle 1B by pipe 19 to the output line 5 of the turbo expander 1 before the valve 15 and the outlet 20 of the ejector 1 is connected to the collectors 12 and 13 by the pipe 21 with additional rear 22 and 23. The pipe 21 through the crane 24 is connected to the storage tank 25. In the initial period of the start-up of the unit, the valve 7 is opened, as a result of which high pressure gas from the pipeline 8 enters the turbine expander 1 via the inlet line 6, where it expands, completing the work in the turbocharger, and um via line 5 via valve 15 into the atmosphere. After opening the valve 7, the valve 11 is opened, the additional valves 22 and 23, and the valve 15 are closed. At the same time, the valve 2k remains in the closed position. As a result, high-pressure gas from pipeline 8 through line 10 enters ejector head high-pressure nozzle 17, ejected through a low-pressure nozzle 18 expanded gas in turbo-expander 1 through line 19 from output line 5. The mixture obtained in ejector 16 serves as a unit for fuel and start-up gas comes from exit 20 of ejector 6 through conduit 21 into collectors 12 and 13 and from them into chamber 1D of combustion. When the turbine expander 1 reaches the maximum rotational speed, the overrunning clutch 2 is switched off. At the same time close the valve 7- Then shut off the pipeline 19 and the ejector 16 switches to the zero ejection mode. At the same time, the gas leaving the ejector 16 is throttled to the required pressure of the fuel and start-up gas by an additional valve 22 or 23. To eliminate gas losses during the initial launch period (until the chamber is ignited), especially when significant, the start is started with the valve 15 closed, and the additional valve 23 is kept closed when valve 11 is opened. Valve 22 is also opened. As a result, the fuel and start-up gas flows from the ejector 16 through pipe 21 to tank 25, where it accumulates . In this case, the degree of throttling of the valve 7 in time is continuously reduced to maintain a constant expansion stage of the turboexpander 1. By the time of ignition, the combustion chamber I opens the valve 23 and the gas from the tank 25 begins to flow into the collectors 12 and 13 through conduit 21. At the same time, the pipeline 21 receives gas from the ejector 16. Under, the required pressure in the collectors 12 and 13 is provided by regulating additional valves 22 and 23 of crane 2 and valves 7 and 11. After disconnecting the turboexpander 1 and switching the ejector 16 to the zero ejection mode, the collectors 12 and 13 continue to receive gas from the ejector 16 and the tank 25. After the turboexpander 1 turns off, gregata only on gas coming from the tank 25.. The increase in profitability at start-up is achieved due to the almost complete elimination of the release of natural gas into the atmosphere, as well as by reducing the energy loss of natural gas due to its throttling to the desired pressure of the fuel and starting gas. At the same time, pollution of the surrounding atmosphere is prevented. Claims of the Invention The start-up system of a gas turbine gas pumping unit, comprising a starting turbo expander connected via an overrunning clutch to a turbocharger rotor and connected to the outlet line to the atmosphere, and an inlet to a high pressure gas pipeline connected to the manifolds of the starting and fuel gas of the combustion chamber of the comb system and the comp system. The system is equipped with an ejector, in order to increase the efficiency of the launch and reduce the pollution of the surrounding atmosphere 84, the high-pressure nozzle of which connects to the gas pipeline, low pressure to the output line, and the output connected to the collectors. Sources of information taken into account during the examination 1. Author's certificate of the USSR APP number, cl. F 02 C 9/00, 1963. 2. US patent number 2608WO, cl. 60-ЗЭ "1 published1 1952"